Chapter 5 Directional static stability and control - 2 Lecture 17 Topics
|
|
- Dominic Flynn
- 6 years ago
- Views:
Transcription
1 hapter 5 Directional static stability and control - Lecture 17 Topics 5.5 ontribution of power to nβ 5.6 ontribution of ertical tail to nβ Influence of wing-body combination on contribution of ertical tail ( nβ ) 5.6. Expression for ( nβ ) 5.7 Directional static stability Pedal-fixed static directional stability 5.7. Weather cock effect Pedal-free static directional stability Desirable leel of nβ Example Directional control Aderse yaw and its control 5.8. ontrol in cross wind take-off and landing 5.5 ontribution of power to nβ Figure 5.5 shows a tractor propeller in sideslip. It produces a side force Y p and yawing moment Y p l p. Since, the moment depends on angle of sideslip, there is a direct contribution to nβ. It is denoted by nβp. It is seen that the contribution is negatie and hence, destabilizing. If the airplane has a pusher propeller, then the contribution is positie and stabilizing. A jet engine in sideslip will also produce nβp whose alue will depend on the engine location. A propeller also has an indirect contribution to nβ. The slipstream of a propeller in sideslip would be asymmetric (Fig.5.6). It is obsered that for a positie alue of β, the left wing will hae a larger region influenced by the Dept. of Aerospace Engg., IIT Madras 1
2 propeller slipstream than the right wing. Since, the dynamic pressure in the slipstream is higher than the free stream dynamic pressure, the left wing, with larger region influenced by slip stream, will hae higher drag than the right wing. This would result a slight destabilizing contribution to nβ. Fig.5.5 Propeller and ertical tail in sideslip Dept. of Aerospace Engg., IIT Madras
3 Fig.5.6 Slip stream of a propeller in sideslip Remark: An accurate estimate of nβp is difficult due to the influence of arious factors.it is generally small and ignored during initial estimate of nβ. 5.6 ontribution of ertical tail In subsection.4.4. it is shown that the horizontal tail at an angle of attack produces lift L t and a pitching moment M cgt. Similarly, a ertical tail at an angle of attack (α ) would produce a side force (Y ) and a yawing moment (N ) (See Fig.5.5).The side force Y is perpendicular to the elocity V t as shown in Fig.5.5. Howeer, the angle α is small and Y is taken perpendicular to FRL. Now, Y = - 1 ρ V S Lα t (5.13) Note that as per conention Y is positie in the direction of y-axis. Hence, positie β gies negatie Y. The yawing moment due to ertical tail is gien as: 1 N = ρ V S Lα t l (5.14) Dept. of Aerospace Engg., IIT Madras 3
4 and = n 1 ρ V S 1 ρ V S b Lα t l Influence of wing-body combination on contribution of ertical tail The wing body combination has the following influences. (5.14a) (a) The angle of attack (α ) at ertical tail is different from and (b) The dynamic pressure (½ ρv t) experienced by it (ertical tail) is different from (½ ρv ) (Figs.5.5, 5.7). The angle of attack is modified as: α = β + σ ; (5.15) where, σ is called side wash. The dynamic pressure experienced by tail is expressed as: ½ ρv t = η (½ ρv ) (5.16) Fig.5.7 Side wash on ertical tail Dept. of Aerospace Engg., IIT Madras 4
5 5.6. Expression for nβv Taking into account the interference effects Eq.(5.14a) becomes: 1 (β+σ) ρ V S = n Lα t 1 ρ V Sb =V η Lα (β+σ) (5.17) where, 1 ρv S l t V = and η = ; S b 1 ρv Differentiating Eq.(5.17) by β gies : nβ = V η Lα (1+ ) dβ (5.18) (5.19) As mentioned earlier, the wing and fuselage influence σ and η (Fig.5.7). Based on Ref.., the following empirical formula gies the influence of wing-body combination. S zw η (1+ ) = S Aw dβ 1+cos Λc/4w d (5.0) where z w is the distance, parallel to z-axis, between wing root quarter chord point and the FRL ; d is the maximum depth of the fuselage; and cos c /4w is sweep of wing quarter chord line. Remark: The slope of lift cure of the ertical tail ( Lα ) can be calculated by knowing its effectie aspect ratio (A eff ) and using methods similar to those for estimation of the slope of lift cure of the wing. The aspect ratio of the ertical tail (A ) is b / S, where b is generally the height of ertical tail aboe the centre line of the portion of the fuselage where the ertical tail is located and S is the area of the ertical tail aboe the aforesaid centre line. The effectie aspect ratio Dept. of Aerospace Engg., IIT Madras 5
6 (A eff ) of the ertical tail is much higher than A and depends on the interference effect due to fuselage and horizontal tail. For details see appendix, and Ref.1.8b, Ref.1.1, chapter 3 and Ref. 1.7, chapter Directional static stability Haing obtained the contributions of arious components to nβ, arious aspects of directional static stability are discussed below Pedal-fixed static stability As regards the action of pilot to effect the moement of control surfaces, the following may be pointed out. (a) The eleator is moed by the forward or backward moement of the control stick. (b) The ailerons are operated by the sideward moement of the control stick. (c) The rudder is moed by pushing the pedals. In longitudinal static stability analysis the stick-fixed and stick-free cases were considered. These deal with the eleator-fixed and eleator-free cases respectiely. Similarly, in directional static stability, rudder-fixed and rudder-free stability is considered. These cases are also referred to as pedal-fixed and pedalfree stability analyses. In the analysis of directional static stability carried out so far the contributions of wing, fuselage, nacelle, power and ertical tail to nβ hae been considered. Noting that for the pedal-fixed stability, the rudder deflection is constant, ( nβ ) pedal-fixed is gien by adding these indiidual contributions i.e. nβ = ( nβ) w + ( nβ) f,n,p + V V η Lα (1+ ) (5.1) dβ 5.7. Weathercock effect Wheneer an airplane, originally flying with zero sideslip, deelops a sideslip (β), the ertical tail tends to bring it back to the original position of zero sideslip. This effect is similar to that of the ane attached to the weathercock which is used to indicate the direction of wind and is located on top of buildings in meteorological departments and near airports (Fig.5.8). When the ane is at an angle of attack, it produces lift on itself and consequently a moment about its hinge. This moment becomes zero only when the ane is aligned with the wind Dept. of Aerospace Engg., IIT Madras 6
7 direction. Hence, the ane is always directed in a way that the arrow points in the direction opposite to that of the wind. The action of ertical tail on the airplane is also similar to that of the ane and helps in aligning the airplane axis with wind direction. Hence, the directional stability is also called weathercock stability. Fig.5.8 Weathercock or weather ane (Source: ) Pedal-free static directional stability: As noted in section 3.1 the hinge moment on the eleator is made zero by suitable deflection of the eleator tab. Similarly, the hinge moment of the rudder is also brought to zero by suitable deflection of the rudder tab. The analysis of static stability when rudder is left free to moe is called rudder-free or pedal-free stability. The equation for hinge moment about rudder hinge ( hr ) can be expressed as: hr = hα + hδrδ r + hδrtab δ rt (5.) Where, δ r is the rudder deflection and δ rt is the deflection of the rudder tab. The floating angle of rudder, δ rfree is obtained when hr is zero i.e. Dept. of Aerospace Engg., IIT Madras 7
8 (hα α + hδrtab δ rt ) δ rfree = - hδr dδ dα = - = - (1+ ) dβ dβ dβ rfree hα hα Hence, Remarks: hδr i) onention for rudder deflection hδr (5.3) (5.4) A rudder deflection to left is taken as positie. It is a general conention that a positie control deflection produces negatie moment. This is consistent with the conention that rotation is taken positie clockwise when looking along the axis about which the rotation takes place. ii) hα and hδr and leel of static direction stability with rudder free Noting the conention for β, and with the help of pressure distribution shown in Fig.3.3, it is obsered that a positie alue of β would produce a negatie force on the rudder and hence a positie hinge moment. onsequently, hα is positie. In a similar manner it is obsered that a positie rudder deflection would produce a positie side force and hence, negatie hinge moment. Thus, hδr is negatie. Hence, from Eq.(5.4), (dδ r ) free / dβ is negatie. Thus, when a disturbance produces positie β, the rudder will take such a position that the rudder deflection is negatie. The result is a negatie change in yawing moment or reduced static stability. Thus, the leel of static directional stability will be reduced when the pedal is free Desirable leel of nβ In longitudinal static stability, the shift of c.g. has a profound effect on the leel of stability ( ) as the contribution of wing to m m depends directly on (x cg - x ac ). Thus, the shift in the position of c.g, during flight, almost decides the area of the horizontal tail. Howeer, a shift of c.g. does not cause a significant change in nβ because such a change may only hae a secondary effect by way of slightly affecting l. Hence, to arrie at the area of the ertical tail, a criterion to prescribe a desirable alue of nβ is needed. Reference 1.7, hapter 8 gies: W 1 ( nβ) desirable = ( ) deg b -1 (5.5) Dept. of Aerospace Engg., IIT Madras 8
9 where, W is the weight of the airplane in lbs and b is the wing span in feet. Reference 1.1, Appendix B gies characteristics of seen airplanes. It is obsered that for the subsonic airplanes nβ lies between to deg -1. Howeer, the final alue of nβ is decided after the dynamic stability analysis. From lateral dynamic stability analysis (chapter 9) it will be obsered that a large alue of nβ leads to some unacceptable response of the airplane to the disturbance. Example 5. A model of an airplane is tested in a wind tunnel without the ertical tail. ontributions of arious components gie nβ = deg -1. If the ertical tail is to be positioned at a point on the aft end of the fuselage giing a tail length of 4.8 m, How much ertical tail area is required to gie an oerall ηβ = deg -1? Assume that the ertical tail would hae an effectie aspect ratio of, the wing area is 18 m, wing span is 10.6 m and the wing is set at the middle of the fuselage. Solution: nβ = ( nβ ) w + ( nβ ) f,n,p + ( nβ ) t Gien: ( nβ ) w + ( nβ ) f,n,p = ( nβ ) required = Hence, ( ηβ ) t = ( ) = From Eq.(5.19), ( nβ ) = V η Lα (1+ ) dβ I) Estimation of Lα : A eff =. The expression for Lα is (Ref.1.8b): πa Lα = in rad A βm (1+tan Λ c/) + +4 K β where, β M = (1-M ) 1/, K = lift cure slope of airfoil / π. Λ c/ = sweep of mid chord line -1 Dept. of Aerospace Engg., IIT Madras 9
10 As Mach number is low subsonic β M 1. Let K =1, onsequently, = L + A +4 Veff πa Lα + +4 Λ c = 0 w 4 π For A of.0, = =.60 rad = deg 10.6 A w = = Remark: Reference 1.7, Fig.8.8 gies Lα =0.044 deg -1 for A eff of.0. II) Estimation of η (1+ ) dβ The expression for η (1+ ) dβ as gien by Eq.(5.0) depends on S / S but S / S is not known at this stage. Hence, as a first approximation it is assumed that S / S = 0.1. The quantity z w /d can be taken as zero for the mid wing configuration. 0.1 Hence, η (1+ ) = ( ) = dβ 1+1 onsequently, the first estimation of V is: = V or V = Noting that, V =, gies S = =.18 m S l 10.6 S b 4.8 To improe the estimation of S,its alue in the preious step is substituted in the expression for η (1+ ) dβ i.e..18 / 18 η (1+ ) = ( ) = dβ 1+1 The second estimation of V is: Dept. of Aerospace Engg., IIT Madras 10
11 0.004 V = = Or S =.176 m Since, the two estimates are close to each other, the iteration is terminated and S =.176 m is taken as the answer. 5.8 Directional ontrol ontrol of rotation of the airplane about the z-axis is proided by the rudder. The critical conditions for design of rudder are: (a) Aderse yaw, (b) ross wind take-off and landing, (c) Asymmetric power for multi- engined airplanes and (d) Spin Aderse yaw and its control When an airplane is rolled to the right, the rate of roll produces a yawing moment tending to turn the airplane to the left. Similarly, a roll to left produces yaw to right. Hence, the yawing moment produced as a result of the rate of roll is called aderse yaw. To explain the production of aderse yaw, consider an airplane rolled to right, i.e. right wing down. Let, the rate of roll be p. The rate of roll produces the following two effects. a) A roll to right implies less lift on the right wing and more lift on the left wing. This is brought about by aileron deflection in the present case an up aileron on the right wing and a down aileron on the left wing. Since, L on the right wing is less than L on the left wing, the induced drag coefficient ( Di ) on the right wing is less than Di on left wing. This results in a yawing moment causing the airplane to yaw to left. b) Due to the rolling elocity (p) a section on the down going wing at a distance y from the FRL experiences a relatie upward wind of magnitude py. At the same time a section on the up going wing at a distance y from FRL experiences a relatie downward elocity of magnitude py. This results in the change of Dept. of Aerospace Engg., IIT Madras 11
12 direction of the resultant elocity on the two wing hales (Fig.5.9). Now, the lift ector, being perpendicular to the resultant elocity, is bent forward on the down going wing and bent backwards on the up going wing.onsequently, the horizontal components of the lift on the two wing hales produce a moment tending to yaw the airplane to left. An approximate estimate of the effect of aderse yaw is (Ref.1.1, chapter 3): L ( n) aderseyaw - 8 V pb (5.7) where, p = rate of roll in radians per second; b = wing span and V = flight elocity. Fig.5.9 Effect of rate of roll An airplane is generally designed for a specific alue of (pb/v). For example, Ref.1.7 hapter 9 prescribes that up to 80% of V max the airplane should hae: pb / V = 0.07 for cargo/ bomber pb / V = 0.09 for fighter Hence, one of the criteria for rudder design is that it must be powerful enough to counter the aderse yaw at prescribed rate of roll ontrol in cross wind take-off and landing An Airplane sometimes encounters side winds during take-off and landing. As regards control during this eentuality, the following three points may be noted. (1) When an airplane flying at a elocity V, encounters a side wind of elocity, the resultant elocity ector makes an angle Δβ to the plane of symmetry; Δβ = /V. Dept. of Aerospace Engg., IIT Madras 1
13 ()The tendency of an airplane possessing directional static stability, is to align itself with the wind direction (weather cock effect). (3) During take-off and landing the pilot has to keep the airplane along the runway. Hence, when a cross wind is present the airplane is side-slipping with angle Δβ. Thus, another criterion for the design of the rudder is required. It must be able to counteract the yawing moment due to sideslip produced by the cross wind ( nβ x Δβ). This criterion becomes more critical at lower speeds because (a) the effectieness of the rudder, being proportional to V, is less at lower flight speeds and (b) Δβ being proportional to 1/V, is high at low flight speeds. According to Ref.1.1, chapter the rudder must be able to oercome = 51 ft / s or 15 m/s at the minimum speed for the airplane. It may be pointed out that on a rainy day, with heay cross winds, the landing on the airport may be refused if the cross wind is more than that permitted for the airplane. Dept. of Aerospace Engg., IIT Madras 13
Chapter 5 Wing design - selection of wing parameters - 4 Lecture 22 Topics
Chapter 5 Wing design - selection of wing parameters - Lecture Topics 5.3.9 Ailerons 5.3.0 Other aspects of wing design Example 5. 5.3.9 Ailerons The main purpose of the ailerons is to create rolling moment
More informationChapter 5 Wing design - selection of wing parameters - 3 Lecture 21 Topics
Chapter 5 Wing design - selection of wing parameters - 3 Lecture 21 Topics 5.3.2 Choice of sweep ( ) 5.3.3 Choice of taper ratio ( λ ) 5.3.4 Choice of twist ( ε ) 5.3.5 Wing incidence(i w ) 5.3.6 Choice
More informationAerodynamics Principles
Aerodynamics Principles Stage 1 Ground Lesson 3 Chapter 3 / Pages 2-18 3:00 Hrs Harold E. Calderon AGI, CFI, CFII, and MEI Lesson Objectives Become familiar with the four forces of flight, aerodynamic
More informationAero Club. Introduction to Flight
Aero Club Presents Introduction to RC Modeling Module 1 Introduction to Flight Centre For Innovation IIT Madras Page2 Table of Contents Introduction:... 3 How planes fly How is lift generated?... 3 Forces
More information11-1. Horizontal tailplane sizing according to control requirement
11-1 11 Empennage izing In ection Empennage General Design, the areas of the horizontal and vertical tailplanes were calculated merely with the aid of tail volume coefficients. The tail lever arms were
More informationII.E. Airplane Flight Controls
References: FAA-H-8083-3; FAA-8083-3-25 Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop knowledge of the elements related to
More informationStability and Flight Controls
Stability and Flight Controls Three Axes of Flight Longitudinal (green) Nose to tail Lateral (blue) Wing tip to Wing tip Vertical (red) Top to bottom Arm Moment Force Controls The Flight Controls Pitch
More informationAircraft Stability and Control Prof. A. K. Ghosh Department of Aerospace Engineering Indian Institute of Technology-Kanpur. Lecture- 25 Revision
Aircraft Stability and Control Prof. A. K. Ghosh Department of Aerospace Engineering Indian Institute of Technology-Kanpur Lecture- 25 Revision Yes, dear friends, this is the mann ki baat session for lateral
More informationPrinciples of glider flight
Principles of glider flight [ Lecture 2: Control and stability ] Richard Lancaster Email: Richard@RJPLancaster.net Twitter: @RJPLancaster ASK-21 illustrations Copyright 1983 Alexander Schleicher GmbH &
More informationPEMP ACD2501. M.S. Ramaiah School of Advanced Studies, Bengaluru
Aircraft Performance, Stability and Control Session delivered by: Mr. Ramjan Pathan 1 Session Objectives Aircraft Performance: Basicsof performance (t (steadystateand tt d accelerated) Performance characteristics
More informationPreliminary Design Review (PDR) Aerodynamics #2 AAE-451 Aircraft Design
Preliminary Design Review (PDR) Aerodynamics #2 AAE-451 Aircraft Design Aircraft Geometry (highlight any significant revisions since Aerodynamics PDR #1) Airfoil section for wing, vertical and horizontal
More informationAERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING
ICAS 2002 CONGRESS AERODYNAMIC CHARACTERISTICS OF SPIN PHENOMENON FOR DELTA WING Yoshiaki NAKAMURA (nakamura@nuae.nagoya-u.ac.jp) Takafumi YAMADA (yamada@nuae.nagoya-u.ac.jp) Department of Aerospace Engineering,
More informationA103 AERODYNAMIC PRINCIPLES
A103 AERODYNAMIC PRINCIPLES References: FAA-H-8083-25A, Pilot s Handbook of Aeronautical Knowledge, Chapter 3 (pgs 4-10) and Chapter 4 (pgs 1-39) OBJECTIVE: Students will understand the fundamental aerodynamic
More informationNo Description Direction Source 1. Thrust
AERODYNAMICS FORCES 1. WORKING TOGETHER Actually Lift Force is not the only force working on the aircraft, during aircraft moving through the air. There are several aerodynamics forces working together
More informationC-130 Reduction in Directional Stability at Low Dynamic Pressure and High Power Settings
C-130 Reduction in Directional Stability at Low Dynamic Pressure and High Power Settings The C-130 experiences a marked reduction of directional stability at low dynamic pressures, high power settings,
More informationLift for a Finite Wing. all real wings are finite in span (airfoils are considered as infinite in the span)
Lift for a Finite Wing all real wings are finite in span (airfoils are considered as infinite in the span) The lift coefficient differs from that of an airfoil because there are strong vortices produced
More informationThe effect of back spin on a table tennis ball moving in a viscous fluid.
How can planes fly? The phenomenon of lift can be produced in an ideal (non-viscous) fluid by the addition of a free vortex (circulation) around a cylinder in a rectilinear flow stream. This is known as
More informationPhysics 1 HW #8: Chapter 3
Phsics 1 HW #8: Chapter 3 Problems 6-9, 31, 3, 49, 54. For EVERY one of the problems, draw ector diagrams, labeling the ectors and write out the ector equation! Hae fun! 3.6 We use the following notation:
More informationIt should be noted that the symmetrical airfoil at zero lift has no pitching moment about the aerodynamic center because the upper and
NAVWEPS -81-8 and high power, the dynamic pressure in the shaded area can be much greater than the free stream and this causes considerably greater lift than at zero thrust. At high power conditions the
More informationWinnipeg Headingley Aero Modellers. Things About Airplanes.
Winnipeg Headingley Aero Modellers Things About Airplanes. Table of Contents Introduction...2 The Airplane...2 How the Airplane is Controlled...3 How the Airplane Flies...6 Lift...6 Weight...8 Thrust...9
More informationAerodynamic Terms. Angle of attack is the angle between the relative wind and the wing chord line. [Figure 2-2] Leading edge. Upper camber.
Chapters 2 and 3 of the Pilot s Handbook of Aeronautical Knowledge (FAA-H-8083-25) apply to powered parachutes and are a prerequisite to reading this book. This chapter will focus on the aerodynamic fundamentals
More informationPRIMARY FLIGHT CONTROLS. AILERONS Ailerons control roll about the longitudinal axis. The ailerons are attached to the outboard trailing edge of
Aircraft flight control systems are classified as primary and secondary. The primary control systems consist of those that are required to safely control an airplane during flight. These include the ailerons,
More informationLow-Speed Wind-Tunnel Investigation of the Stability and Control Characteristics of a Series of Flying Wings With Sweep Angles of 50
NASA Technical Memorandum 464 Low-Speed Wind-Tunnel Investigation of the Stability and Control Characteristics of a Series of Flying Wings With Sweep Angles of 5 Scott P. Fears Lockheed Engineering & Sciences
More informationAE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability.
Aerodynamics: Introduction Aerodynamics deals with the motion of objects in air. These objects can be airplanes, missiles or road vehicles. The Table below summarizes the aspects of vehicle performance
More informationCHAPTER 1 - PRINCIPLES OF FLIGHT
CHAPTER 1 - PRINCIPLES OF FLIGHT Reilly Burke 2005 INTRODUCTION There are certain laws of nature or physics that apply to any object that is lifted from the Earth and moved through the air. To analyze
More informationAircraft Stability and Control Prof. A.K.Ghosh Department of Aerospace Engineering Indian Institute of Technology-Kanpur. Lecture-01 Introduction
Aircraft Stability and Control Prof. A.K.Ghosh Department of Aerospace Engineering Indian Institute of Technology-Kanpur Lecture-01 Introduction Wish you all very, very happy New Year. We are on the tarmac
More informationDetailed study 3.4 Topic Test Investigations: Flight
Name: Billanook College Detailed study 3.4 Topic Test Investigations: Flight Ivanhoe Girls Grammar School Questions 1 and 2 relate to the information shown in the diagram in Figure 1. z Question 1 y Figure
More informationFront Cover Picture Mark Rasmussen - Fotolia.com
Flight Maneuvers And Stick and Rudder Skills A complete learn to fly handbook by one of aviation s most knowledgeable and experienced flight instructors Front Cover Picture Mark Rasmussen - Fotolia.com
More informationPILOT S HANDBOOK of Aeronautical Knowledge AC61-23C
PILOT S HANDBOOK of Aeronautical Knowledge AC61-23C Revised 1997 Chapter 1 Excerpt Compliments of... www.alphatrainer.com Toll Free: (877) 542-1112 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION
More informationLAPL(A)/PPL(A) question bank FCL.215, FCL.120 Rev PRINCIPLES OF FLIGHT 080
PRINCIPLES OF FLIGHT 080 1 Density: Is unaffected by temperature change. Increases with altitude increase. Reduces with temperature reduction. Reduces with altitude increase. 2 The air pressure that acts
More informationROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool)
Unit D-1: Aerodynamics of 3-D Wings Page 1 of 5 AE301 Aerodynamics I UNIT D: Applied Aerodynamics ROAD MAP... D-1: Aerodynamics of 3-D Wings D-: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics
More informationJet Propulsion. Lecture-17. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati
Lecture-17 Prepared under QIP-CD Cell Project Jet Propulsion Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1 Lift: is used to support the weight of
More informationThe Fly Higher Tutorial IV
The Fly Higher Tutorial IV THE SCIENCE OF FLIGHT In order for an aircraft to fly we must have two things: 1) Thrust 2) Lift Aerodynamics The Basics Representation of the balance of forces These act against
More informationWelcome to Aerospace Engineering
Welcome to Aerospace Engineering DESIGN-CENTERED INTRODUCTION TO AEROSPACE ENGINEERING Notes 4 Topics 1. Course Organization 2. Today's Dreams in Various Speed Ranges 3. Designing a Flight Vehicle: Route
More informationChapter 3: Aircraft Construction
Chapter 3: Aircraft Construction p. 1-3 1. Aircraft Design, Certification, and Airworthiness 1.1. Replace the letters A, B, C, and D by the appropriate name of aircraft component A: B: C: D: E: A = Empennage,
More informationFUSELAGE-MOUNTED FINS ON THE STATIC DIRECTIONAL STABILITY. By M. Leroy Spearman, Ross B. Robinson, and Cornelius Driver
RESEARCH MEMORANDUM THE EFFECTS OF THE ADDITION OF SMALL FUSELAGE-MOUNTED FINS ON THE STATIC DIRECTIONAL STABILITY CHARACTERISTICS OF A MODEL OF A 45' SWEPT-WING AIRPLANE AT ANGLES OF ATTACK UP TO 15.3?
More informationAIRCRAFT PRIMARY CONTROLS A I R C R A F T G E N E R A L K N O W L E D G E
1.02.02 AIRCRAFT PRIMARY CONTROLS 1. 0 2 A I R C R A F T G E N E R A L K N O W L E D G E CONTROLLING AIRCRAFT AIRCRAFT CONTROL SYSTEM In general, we use control inputs of the following devices in cabin:
More informationFlight Control Systems Introduction
Flight Control Systems Introduction Dr Slide 1 Flight Control System A Flight Control System (FCS) consists of the flight control surfaces, the respective cockpit controls, connecting linkage, and necessary
More informationDIRECCION DE PERSONAL AERONAUTICO DPTO. DE INSTRUCCION PREGUNTAS Y OPCIONES POR TEMA
MT DIREION DE PERSONL ERONUTIO DPTO. DE INSTRUION PREGUNTS Y OPIONES POR TEM 1 TEM: 0292 FLT/DSP - (HP. 03) ERODYNMIS OD_PREG: PREG20084823 (8324) PREGUNT: When are inboard ailerons normally used? Low-speed
More informationLAPL/PPL question bank FCL.215, FCL.120 Rev PRINCIPLES OF FLIGHT 080
LAPL/PPL question bank FCL.215, FCL.120 Rev. 1.7 11.10.2018 PRINCIPLES OF FLIGHT 080 1 Density: Reduces with temperature reduction. Increases with altitude increase. Reduces with altitude increase. Is
More informationVIII.A. Straight and Level Flight
VIII.A. Straight and Level Flight References: FAA-H-8083-3; FAA-H-8083-25 Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop the
More informationAircraft Stability and Performance 2nd Year, Aerospace Engineering. Dr. M. Turner
Aircraft Stability and Performance 2nd Year, Aerospace Engineering Dr. M. Turner Basic Info Timetable 15.00-16.00 Monday Physics LTA 16.00-17.00 Monday Physics LTA Exam 2 1 2 hour exam 6 questions 2 from
More informationXI.B. Power-On Stalls
XI.B. Power-On Stalls References: AC 61-67; FAA-H-8083-3; POH/AFM Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop knowledge
More informationPRINCIPLES OF FLIGHT
CHAPTER 3 PRINCIPLES OF FLIGHT INTRODUCTION Man has always wanted to fly. Legends from the very earliest times bear witness to this wish. Perhaps the most famous of these legends is the Greek myth about
More information1. A tendency to roll or heel when turning (a known and typically constant disturbance) 2. Motion induced by surface waves of certain frequencies.
Department of Mechanical Engineering Massachusetts Institute of Technology 2.14 Analysis and Design of Feedback Control Systems Fall 2004 October 21, 2004 Case Study on Ship Roll Control Problem Statement:
More informationDIRECCION DE PERSONAL AERONAUTICO DPTO. DE INSTRUCCION PREGUNTAS Y OPCIONES POR TEMA
MT DIREION DE PERSONL ERONUTIO DPTO. DE INSTRUION PREGUNTS Y OPIONES POR TEM 1 TEM: 0114 TP - (HP. 03) ERODYNMIS OD_PREG: PREG20078023 (8358) PREGUNT: What is the safest and most efficient takeoff and
More informationAERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK SUPREETH NARASIMHAMURTHY GRADUATE STUDENT 1327291 Table of Contents 1) Introduction...1 2) Methodology.3 3) Results...5
More informationHomework Exercise to prepare for Class #2.
Homework Exercise to prepare for Class #2. Answer these on notebook paper then correct or improve your answers (using another color) by referring to the answer sheet. 1. Identify the major components depicted
More informationTHE AIRCRAFT IN FLIGHT Issue /07/12
1 INTRODUCTION This series of tutorials for the CIX VFR Club are based on real world training. Each document focuses on a small part only of the necessary skills required to fly a light aircraft, and by
More informationSUBPART C - STRUCTURE
SUBPART C - STRUCTURE GENERAL CS 23.301 Loads (a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by
More informationV mca (and the conditions that affect it)
V mca (and the conditions that affect it) V mca, the minimum airspeed at which an airborne multiengine airplane is controllable with an inoperative engine under a standard set of conditions, is arguably
More informationJ. Szantyr Lecture No. 21 Aerodynamics of the lifting foils Lifting foils are important parts of many products of contemporary technology.
J. Szantyr Lecture No. 21 Aerodynamics of the lifting foils Lifting foils are important parts of many products of contemporary technology. < Helicopters Aircraft Gliders Sails > < Keels and rudders Hydrofoils
More informationWHAT IS GLIDER? A light engineless aircraft designed to glide after being towed aloft or launched from a catapult.
GLIDER BASICS WHAT IS GLIDER? A light engineless aircraft designed to glide after being towed aloft or launched from a catapult. 2 PARTS OF GLIDER A glider can be divided into three main parts: a)fuselage
More informationGleim Private Pilot Flight Maneuvers Seventh Edition, 1st Printing Updates February 2018
Page 1 of 11 Gleim Private Pilot Flight Maneuvers Seventh Edition, 1st Printing Updates February 2018 If you are tested on any content not represented in our materials or this update, please share this
More informationAERODYNAMICS VECTORS
AERODYNAMICS The challenge in explaining aerodynamics for glider pilots is to provide the information needed to fly safely and efficiently without overloading the student with complex theories. Meeting
More informationPRE-TEST Module 2 The Principles of Flight Units /60 points
PRE-TEST Module 2 The Principles of Flight Units 1-2-3.../60 points 1 Answer the following questions. (20 p.) moving the plane (4) upward / forward. Opposed to that is 1. What are the names of the four
More informationVIII.A. Straight and Level Flight
VIII.A. Straight and Level Flight References: FAA-H-8083-3; FAA-H-8083-25 Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop the
More informationXI.C. Power-Off Stalls
References: FAA-H-8083-3; POH/AFM Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop knowledge of stalls regarding aerodynamics,
More informationChapter 3 Lecture 9. Drag polar 4. Topics. Chapter-3
Chapter 3 Lecture 9 Drag polar 4 Topics 3..11 Presentation of aerodynamic characteristics of airfoils 3..1 Geometric characteristics of airfoils 3..13 Airfoil nomenclature\designation 3..14 Induced drag
More informationRESEARCH MEMORANDUM. WASHINGTON December 3, AERODYNl$MIC CHARACTERISTICS OF A MODEL? OF AN ESCAPE ...,
.". -.%. ;& RESEARCH MEMORANDUM AERODYNl$MIC CHARACTERISTICS OF A MODEL? OF AN ESCAPE 1 \ < :. By John G. Presnell, Jr. w'..., '.., 3... This material contains information affecting the National Bfense
More informationV 00 = freestream velocity vector
Design of High-Lift Airfoils for Low Aspect Ratio Wings with Endplates Ashok Gopalarathnam* and Michael S. Seligt Department of Aeronautical and Astronautical Engineering Uniersity of Illinois at Urbana-Champaign
More informationUncontrolled copy not subject to amendment. Principles of Flight
Uncontrolled copy not subject to amendment Principles of Flight Principles of Flight Learning Outcome 2: Understand how the stability of an aeroplane is maintained in flight and how manoeuvrability is
More informationHydrodynamics for Ocean Engineers Prof. A.H. Techet
13.012 Hydrodynamics for Ocean Engineers Prof. A.H. Techet Archimedes s Principle and tatic tability I. Archimedes s Principle: The force on a body due to pressure alone (in the absence of iscous forces)
More informationAPPLICATION OF ESTOL FLIGHT CONTROL TECHNOLOGY TO UCAV DESIGN
ICAS22 CONGRESS APPLICATION OF ESTOL FLIGHT CONTROL TECHNOLOGY TO UCA DESIGN A. Knoll, B. Fischer EADS Military Aircraft Keywords: flight control, ESTOL, control laws Abstract During the X-31 ector program
More informationAerodynamics. A study guide on aerodynamics for the Piper Archer
Aerodynamics A study guide on aerodynamics for the Piper Archer Aerodynamics The purpose of this pilot briefing is to discuss the simple and complex aerodynamics of the Piper Archer. Please use the following
More informationRelated Careers: Aircraft Instrument Repairer Aircraft Designer Aircraft Engineer Aircraft Electronics Specialist Aircraft Mechanic Pilot US Military
Airplane Design and Flight Fascination with Flight Objective: 1. You will be able to define the basic terms related to airplane flight. 2. You will test fly your airplane and make adjustments to improve
More informationExploration Series. AIRPLANE Interactive Physics Simulation Page 01
AIRPLANE ------- Interactive Physics Simulation ------- Page 01 What makes an airplane "stall"? An airplane changes its state of motion thanks to an imbalance in the four main forces acting on it: lift,
More informationSTUDY OF VARIOUS NACA SERIES AEROFOIL SECTIONS AND WING CONTOUR GENERATION USING CATIA V5
STUDY OF VARIOUS NACA SERIES AEROFOIL SECTIONS AND WING CONTOUR GENERATION USING CATIA V5 Pawan Kumar Department of Aeronautical Engineering, Desh Bhagat University, Punjab, India ABSTRACT Aerofoil is
More informationAerodynamic Analysis of a Symmetric Aerofoil
214 IJEDR Volume 2, Issue 4 ISSN: 2321-9939 Aerodynamic Analysis of a Symmetric Aerofoil Narayan U Rathod Department of Mechanical Engineering, BMS college of Engineering, Bangalore, India Abstract - The
More informationAIRCRAFT STRUCTURAL DESIGN & ANALYSIS K. RAMAJEYATHILAGAM
AIRCRAFT STRUCTURAL DESIGN & ANALYSIS K. RAMAJEYATHILAGAM To invent an airplane is nothing To build one is something But to fly is everything Lilienthal DAY 1 WHAT IS AN AIRCRAFT? An aircraft is a vehicle,
More informationII.D. Principles of Flight
II.D. Principles of Flight References: FAA-H-8083-3; FAA-H-8083-25 Objectives Key Elements Elements Schedule Equipment IP s Actions SP s Actions Completion Standards The student should develop knowledge
More informationA COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES A COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE Jung-Hyun Kim*, Kyu-Hong
More informationFighter aircraft design. Aerospace Design Project G. Dimitriadis
Fighter aircraft design Aerospace Design Project 2017-2018 G. Dimitriadis General configuration The elements of the general configuration are the following: Wing Wing placement Airfoil Number of engines
More informationFirst Flight Glossary
First Flight Glossary (for secondary grades) aeronautics The study of flight and the science of building and operating an aircraft. aircraft A machine used for flying. Airplanes, helicopters, blimps and
More informationPOWERED FLIGHT HOVERING FLIGHT
Once a helicopter leaves the ground, it is acted upon by the four aerodynamic forces. In this chapter, we will examine these forces as they relate to flight maneuvers. POWERED FLIGHT In powered flight
More informationRESEARCH MEMORANDUM FOR AERONAUTICS HAVING A TRZANGULAR WING OF ASPECT WETI0 3. Moffett Field, Calif. WASHINGTON. Ames Aeronautical Laboratory
RESEARCH MEMORANDUM THE EFFECTS OF TRAILINGEDGE FLAPS ON THE SUBSONIC AERODYNAMIC CHARACTERISTICS OF AN AIRPLANE MODEL HAVING A TRZANGULAR WING OF ASPECT WETI0 3 By Bruce E. Tinling and A. V. I I Ames
More informationEXAMPLE MICROLIGHT AIRCRAFT LOADING CALCULATIONS
1. Introduction This example loads report is intended to be read in conjunction with BCAR Section S and CS-VLA both of which can be downloaded from the LAA webpage, and the excellent book Light Aircraft
More informationAerobatic Trimming Chart
Aerobatic Trimming Chart From RCU - Chip Hyde addresses his view of Engine/Motor thrust. I run almost no right thrust in my planes and use the thottle to rudd mix at 2% left rudd. to throttle at idle.
More informationATPL Principles of Flight - deel 2
ATPL Principles of Flight - deel 2 1. If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less then wing span) A decrease B remain
More informationBugatti 100P Longitudinal Stick Forces Revision A
Bugatti 1P Longitudinal Stick Forces Revision A Stick-free static longitudinal stability (stick force-per-knot) and stick-free longitudinal maneuvering stability (stick force-per-g) were computed for the
More informationOttawa Remote Control Club Wings Program
+ Ottawa Remote Control Club Wings Program Guide line By Shahram Ghorashi Chief Flying Instructor Table of Contents Rule and regulation Quiz 3 Purpose of the program 4 Theory of flight Thrust 4 Drag 4
More informationThe Metric Glider. By Steven A. Bachmeyer. Aerospace Technology Education Series
The Metric Glider By Steven A. Bachmeyer Aerospace Technology Education Series 10002 Photographs and Illustrations The author wishes to acknowledge the following individuals and organizations for the photographs
More informationC-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory
ROAD MAP... AE301 Aerodynamics I UNIT C: 2-D Airfoils C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory AE301 Aerodynamics I : List of Subjects
More informationAviation Merit Badge Knowledge Check
Aviation Merit Badge Knowledge Check Name: Troop: Location: Test Score: Total: Each question is worth 2.5 points. 70% is passing Dan Beard Council Aviation Knowledge Check 1 Question 1: The upward acting
More informationAdvanced Aerobatic Airplane Guidelines
Note: The following information might upset career aerodynamicists because it does not also include explanations of Mean Aerodynamic Center, Decalage, Neutral Point, and more when describing how to achieve
More information"Aircraft setup is a constant process really. Every
The R/C Aircraft Proving Grounds - Aerobatics Setup Set Up for Success by: Douglas Cronkhite "Aircraft setup is a constant process really. Every time something is changed, there is the chance it will affect
More informationAircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, Figures
Aircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 2012 Chapter 5 Wing Design Figures 1 Identify and prioritize wing design requirements (Performance, stability, producibility, operational
More informationSnowboard Course: The Optimization of the Halfpipe Shape. Abstract. Team # 10061
Snowboard Course: 1 / 16 The Optimization of the Halfpipe Shape Abstract We determine the shape of the snowboard course, also known as halfpipe, to get the production of the maximum ertical air and the
More informationOUTLINE SHEET BASIC THEORY. 2.1 DEFINE scalar, in a classroom, in accordance with Naval Aviation Fundamentals, NAVAVSCOLSCOM-SG-200
Sheet 1 of 7 OUTLINE SHEET 2-1-1 BASIC THEORY A. INTRODUCTION This lesson is a basic introduction to the theory of aerodynamics. It provides a knowledge base in aerodynamic mathematics, air properties,
More informationDrag Divergence and Wave Shock. A Path to Supersonic Flight Barriers
Drag Divergence and Wave Shock A Path to Supersonic Flight Barriers Mach Effects on Coefficient of Drag The Critical Mach Number is the velocity on the airfoil at which sonic flow is first acquired If
More informationAN INVESTIGATION ON VERTICAL TAILPLANE DESIGN
AN INVESTIGATION ON VERTICAL TAILPLANE DESIGN Fabrizio Nicolosi Pierluigi Della Vecchia Danilo Ciliberti Dep. of Aerospace Engineering University of Naples Federico II Dep. of Aerospace Engineering University
More informationIMPACT OF FUSELAGE CROSS SECTION ON THE STABILITY OF A GENERIC FIGHTER
IMPACT OF FUSELAGE CROSS SECTION ON THE STABILITY OF A GENERIC FIGHTER Robert M. Hall NASA Langley Research Center Hampton, Virginia ABSTRACT Many traditional data bases, which involved smooth-sided forebodies,
More informationAnna University Regional office Tirunelveli
Effect of Tubercle Leading Edge Control Surface on the Performance of the Double Delta Wing Fighter Aircraft P Sharmila 1, S Rajakumar 2 1 P.G. Scholar, 2 Assistant Professor, Mechanical Department Anna
More informationFlight Controls. Chapter 5. Introduction
Chapter 5 Flight Controls Introduction This chapter focuses on the flight control systems a pilot uses to control the forces of flight, and the aircraft s direction and attitude. It should be noted that
More informationLearning Objectives 081 Principles of Flight
Learning Objectives 081 Principles of Flight Conventions for questions in subject 081. 1. The following standard conventions are used for certain mathematical symbols: * multiplication. > = greater than
More informationBRONZE LECTURES. Slides on bayriver.co.uk/gliding
BRONZE LECTURES 2014 Slides on bayriver.co.uk/gliding 1 STUDY Lectures only meant to be a stimulus and provide an opportunity for questions EXAM paper is multi-choice with x sections. 2 READING BOOKS?
More informationCASE STUDY FOR USE WITH SECTION B
GCE A level 135/01-B PHYSICS ASSESSMENT UNIT PH5 A.M. THURSDAY, 0 June 013 CASE STUDY FOR USE WITH SECTION B Examination copy To be given out at the start of the examination. The pre-release copy must
More informationCHAPTER 5 WING DESIGN
HAPTER 5 WING DESIGN Mohammad Sadraey Daniel Webster ollege Table of ontents hapter 5... 1 Wing Design... 1 5.1. Introduction... 1 5.. Number of Wings... 4 5.3. Wing Vertical Location... 5 5.3.1. High
More informationLesson: Turning Flight. Prerequisites: Airspeed Control
2/16/2016 Turning Flight Page 1 Lesson: Turning Flight Prerequisites: Airspeed Control Objectives: o Knowledge o An understanding of the aerodynamics related to directional (yaw) stability o A basic understanding
More informationSTUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS
ICAS 2000 CONGRESS STUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS Kenichi RINOIE Department of Aeronautics and Astronautics, University of Tokyo, Tokyo, 113-8656, JAPAN Keywords: vortex flap,
More information