ESDU AZ Index: AAE
 Considerations With All Engines Operating or After Engine Failure, 85029
 Detailed Example Calculation Procedure and Results for Typical Transport Aircraft
 definition of segments and their end points, 87018
 influence of airworthiness requirements on, 87018
 taking account of all factors affecting applied forces and moments, 87018
 Prediction of Aircraft Stopping Distance on Wet Runway
 from statistical analysis of aircraft stopping distance data, 99015
 from statistical analysis of friction groundtest machine, 99015
 Reaction Times
 sequence and values for typical transport aircraft, 85029
 Acoustic
 Effect of Water on Dimensions of Polymers and Thermosets, 87007
 Spectroscopy Used for Temperature Measurement
 Thermal
 see also
 Abandoned Takeoff
 Balanced Field Length
 Definition of Distance, 87018
 Determination of acceleration from analysis of flight test data, 15001
 Effect on Climb Rate

 see
 Rate of Climb
 Effect on Pressure Lag in Flight Instrumentation, 83029, 85011
 Estimation for Aircraft in Climbing, Diving, Level and/or Turning Flight
 aircraft performance program, ESDUperf, 13006
 program using known drag and thrust characteristics, 00031, 00032, 00033, 00034, 00035, 00036, 00037, 00038, 00039, 13006
 Lateral and Vertical Acceleration of Aircraft

 see
 Fatigue Loading
 Basic Equations for Behaviour and Transfer Functions, 85026
 Determination of angle of attack using accelerometer, 17013
 Use in Analysis of FlightMeasured Performance Data, 15001, 17013, 79018, 88025
 bodymounted and inertial system, 79018
 relationship between reading and load factor, 79018
 Use With Rate Gyros to Determine Aircraft Motion Characteristics
 using Euler attitude angles or quaternion representation, 98024
 see also
 Heat Pipes
 Density
 pressure and temperature variation for saturated gas and liquid, 80017
 Dynamic Viscosity
 pressure and temperature variation for saturated gas and liquid, 80017
 Specific Heat Capacity
 pressure and temperature variation for saturated liquid, 80017
 Specific Latent Heat of Vaporisation
 pressure and temperature variation at saturation, 80017
 Surface Tension
 pressure and temperature variation at saturation, 80017
 Thermal Conductivity
 pressure and temperature variation for saturated liquid, 80017
 Vapour Pressure
 pressure and temperature variation at saturation, 80017
 see also
 Acoustic Loading
 Box Structures
 Composite Structures
 Curved Rectangular Plates
 Curved Sandwich Panels (Cores of Negligible Flexural Stiffness)
 Curved Speciallyorthotropic Rectangular Plates
 Damping
 Flat Panels in General
 Flat Rectangular Plates
 Flat Sandwich Panels (Cores of Negligible Flexural Stiffness)
 Flat Speciallyorthotropic Rectangular Plates
 Flat Speciallyorthotropic Square Plates
 Flat Square Plates
 Integrallymachined Panels
 Response of Lightweight Structures
 Skinrib Joints in Aluminium Alloys
 Skinrib Joints in Composite Structures
 Skinrib Joints in Titanium Alloys
 Vibration and Acoustic Fatigue Series
 Definitions of Terms, 66013
 Factors of Importance in Design Against, 74037
 General Considerations in Testing Endurance of Structural Elements Using Simulated Loading
 definition of failure and likely locations, 93027
 design of clamps, 93027
 design of elements to represent features of fullsize structure, 93027
 dimensions of elements and tuning response, 93027
 excitation and clipping, 93027
 response behaviour and settling, 93027
 simultaneous multielement testing, 93027
 Introduction to Design Information, 74037
 Sources (Both Aerodynamic and Noise), 86025
 Structural Considerations in Design Against
 composite and metallic materials, and equipment fixings, 86025
 Testing of Structures at High Sound Frequencies, 15011
 Test Methods Used in Specific SkinRib Joint Endurance Experiments
 description of test methods and details of specimens, 10011, 72015, 84027
 truncation of loads, 10011, 72015, 84027
 Estimation for Fibrous Materials, 74003
 Estimation for Perforated Sheet, 74004
 Ground
 effective flow resistivity and inverse effective surface depth values, various surfaces, 94035, 94036
 in terms of effective flow resistivity and inverse effective surface depth, 94035, 94036
 Introduction to Concept, 02020
 Use in Estimating Sound Power Attenuation in Lined Annular or Rectangular Straight Ducts
 including effect of subsonic flow and boundary layer, 00024
 Use in Estimating Sound Power Attenuation in Lined Circular Straight Ducts
 including effect of subsonic flow and boundary layer, 00012
 Introduction to Method of Noise Absorption by Local or Extended Reaction, 02020
 see
 Acoustic Absorption Coefficient
 Acoustic Impedance
 Acoustic Linings
 Acoustic Loading
 Acoustic Test Methods
 Aircraft Noise Series
 Airframe Noise (Aeroplanes Not Propeller Powered)
 Atmospheric Effects on Sound
 Boundary Layer
 Cavities
 Crossflow Heat Exchangers
 Fan Noise
 Ground Reflection Effect on Noise
 Helicopter Noise
 Jet Noise
 Lateral Noise Attenuation
 Noise
 Noise in Airconditioning Duct Systems
 Noise Prediction for Aerospace Sources
 Noise/sound Propagation
 Propeller Noise
 Shellandtube Heat Exchangers
 Turbomachinery Noise
 see
 Cavities
 see also
 Indicial Aerodynamics
 Use to Alleviate Buffeting, 87012
 Results for Axial Variation of Various Quantities Across Propeller Disc
 axial velocity, static pressure and streamtube diameter, 85015
 see
 Preentry Drag
 Intakes, 66028
 Compressible SinglePhase Flow Equations and Curves
 Stress Concentration Due to Biaxial Loading
 two circular and optimised shape holes in large plates, 15005
 Stress Concentration Due to Biaxial or Uniaxial Loading With or Without Shear
 two equal diameter holes in a wide flat plate, 67023
 Stress Concentration Due to Shear
 two equal or unequal diameter holes in a wide flat plate, 75007
 Stress Concentration Due to Uniaxial Tension
 two equal diameter holes across a strip, 85045
 two equal or unequal diameter holes in a wide flat plate, 75007
 see
 Antennas
 Aerofoils
 in inviscid subcritical flow, 72024
 in subsonic flow, AERO A.08.01.05
 program to predict for lowdrag GUNACAseries, 99003
 program to predict for subcritical speeds, 06020
 Biconvex and DoubleWedge Aerofoils, AERO W.S.00.03.04
 Definition, 70011
 Position for MissileType WingBody Combination (Truncated Rear Body)
 effect of wing height at low incidence in subsonic or supersonic flow, 95009
 midwing configuration at low incidence in subsonic or supersonic flow, 92024
 Position for Transport Aircraft Type WingBody Combination (Smoothly Tapered Rear Fuselage)
 effect of fuselage geometry and wing sweep, 76015
 effect of rearfuselage nacelle geometry and position, 78013
 effect of underwing nacelle geometry and position, 77012
 program for wingbodynacelle combinations, 13009
 SharpEdged Delta, Cropped Delta or Rectangular Wings of Low Aspect Ratio
 supersonic flow to high angles of attack, 90013
 Spanwise Distribution
 subsonic flow, TD MEMO 6309
 Wings
 subsonic flow, 70011
 supersonic flow, 70012
 see
 Derivatives
 Equilibrium Temperature Under Forced Convection and Radiation
 laminar and turbulent boundary layers, 69012, 69015
 Introduction to Calculation, 69009
 Local and Mean Stanton Numbers on Cones, Plates and Wedges
 forced convection with laminar boundary layer, 69010
 forced convection with turbulent boundary layer, 69011
 Temperature and Stress Distribution Due to
 laminated cylinders and shells, 89027
 plates, 89023, 89024, 89025, 89026
 see also
 Pressure Distribution
 Bodies of Revolution
 oscillating in bending, heave or pitch, 83010
 Calculation of High Frequency Response of Lightweight Structures to
 Complete Flexible Aircraft From Component Contributions Due to Incidence and Pitch Rate
 use to calculate deformation of wing and tailplane using orthogonal modes, 97032
 use to calculate deformation using normal modes, 99033
 Complete Rigid Aircraft From Component Contributions Due to Incidence and Pitch Rate
 equations for lift and moment due to wing/fuselage/nacelle, 94009
 sources of data required, 94009
 Effect on Their Loading Distribution of Tailplane and Wing Static Deformation, 96037
 Effects of Inboard or Outboard on Benefits of Adding Winglets to Existing Wing, 98013
 In Steady Level Asymmetric Flight (Sideslipping, Turning or With Failed Engine)
 on fin, fuselage, tailplane and wing, 01010
 Rectangular Planform Cavity With Closed Flow
 end walls in subsonic or supersonic flow, 00006
 Use to Obtain Forces and Moments in Rigid Airframe Structure Due to Incidence and Pitch Rate
 bending moment and shear force in fuselage, 94045
 bending moment, shear force and torque in wing of medium to high aspect ratio, 94045
 Wings With Camber and Twist
 program for spanwise distribution in subsonic flow, 95010
 spanwise distribution by graphical method in subsonic flow, 83040
 Wings With Camber and Twist and With Plain Leading and/or TrailingEdge Flaps Deflected
 program for spanwise distribution in subsonic flow, 95010
 Wings With Symmetric Sections
 spanwise distribution due to change of angle of attack, TD MEMO 6403
 see also
 Geometric Mean Chord
 Standard Mean Chord
 see also
 Transonic Aerodynamics Series
 Data for Thirteen Sections on Disc, 96029
 Families Designed for Given DragRise Mach Number, 71020
 Program for Geometry of LowDrag GUNACASeries, 99003
 Sources of (Catalogue 4), TD MEMO 6407
 see also
 Aerofoil Coordinates
 Aerofoils with Rooftop Pressure Distribution
 Aerofoils with Supercritical Pressure Distribution
 Biconvex Aerofoils
 Boundary Layer
 Centre of Pressure
 Doublewedge Sections
 Excrescences
 Indicial Aerodynamics
 Magnification of Excrescence Drag By Pressure Gradient
 Normal Force
 Pressure Distribution
 Pressure Drag
 Windtunnel Corrections for Aerofoils
 Wings
 Aerodynamic Centre
 in inviscid subcritical flow, 72024
 in subsonic flow, AERO A.08.01.05
 program to predict for lowdrag GUNACAseries, 99003
 program to predict for subcritical speeds, 06020
 Angle of Attack for Maximum Lift
 program to predict, 99031
 with or without leading and/or trailingedge highlift devices deployed, 96003
 Angle of Attack for Zero Lift
 correction factor for compressibility and viscosity to apply to inviscid value, 98011
 in subcritical attached flow, 98011
 Pankhurst's method in inviscid subcritical flow, 72024, 98011
 program to predict for lowdrag GUNACAseries, 99003
 Base Pressure, AERO W.S.02.03.07
 Boundary Layer Characteristics
 estimation in subcritical flow, 76002
 Buffeting Behaviour
 variation with angle of attack and Mach number, 87012
 Comparisons Against RAE 5225 Aerofoil for Program in 2D Mode, 13013
 Construction of Lift Curve From Zero to Maximum Lift
 program to predict, 99031
 with or without leading and/or trailingedge highlift devices deployed, 96003
 Critical Mach Number
 prediction from incompressible, inviscid pressure distribution, 74008
 variation with thickness/chord ratio, AERO W.00.03.01
 Design of Optimum Section Geometry (Multivariate Gradient Search Using CFD Codes)
 varying camber line shape and highlift device deflections (two design points), 99021
 varying camber line shape or highlift device deflections (single design point), 99020
 varying highlift device deflections on combat aircraft section (single design point), 00022, 00023
 varying surface geometry and highlift device deflections (two design points), 01024
 Design of Section Geometry
 considerations to achieve lowdrag characteristics over a range of lift coefficient, 99003
 to obtain desirable pressure distribution features in transonic flow, 97017
 Design of Section Geometry to Provide Specified UpperSurface Pressure Distribution
 description of program extension made to create VGKD for this use, 99032
 discussion of changes required to achieve required lift coefficient, 99032
 example results illustrating features of method, 99032
 explanation of features to be used to define pressure distribution, 99032
 in transonic flow with or without weak shock, 99032
 resulting drag, lift, and pitching moment coefficients, 99032
 starting from specified thickness distribution, incidence and flow conditions, 99032
 Discussion and Illustration of Transonic Flow Features and Effect on Aerodynamic Characteristics
 effect of increasing angle of attack at constant freestream Mach number, 90008
 effect of increasing freestream Mach number at constant angle of attack, 90008
 Discussion of Behaviour With Fixed Transition of LiftDrag Polar at Subsonic Speeds
 existence of constant drag coefficient over range of lift coefficient, 00027
 DragCreep
 supercritical, TD MEMO 6407
 Drag Estimation at Supersonic Speeds, AERO W.S.00.03.03, AERO W.S.00.03.05
 Drag Estimation at Transonic Speeds Near Separation Using ViscousCoupled Calculation Method, 92008
 Drag Estimation in Viscous Subsonic or Transonic Flow Using VGK, 96028, 96029
 comparison of results with experimental and other theoretical results, 96028
 effect of leading or trailingedge sealed control or flap deflection, 96028, 96029
 influence of values of variable parameters in program on results, 96028
 DragRise Mach Number
 estimation, TD MEMO 6407
 relationship with that of wingbody combination, 78009
 Elliptical Section
 centre of pressure position, 79026
 critical Mach number, AERO W.00.03.01
 lift, 79026
 profile drag, 79026
 Experimental Data
 sources of (Tables 1 and 2), TD MEMO 6407
 GUNACA Design for Low Drag Over a Range of Lift Coefficient
 comparison of geometric and inviscid flow characteristics with those of NACA 6series, 99003
 program for geometric and inviscid flow characteristics, 99003
 Introduction to Data Items on Effect of HighLift Devices on Lift, 94026
 Inverse Design (Multivariate Gradient Search Using CFD Codes)
 to obtain complete or partial target pressure distribution, 01025
 LeadingEdge Suction
 correction of thinleadingedge value to provide attainable value, 95025
 Lift at Zero Angle of Attack, 72024, 97020, 98011
 effect of doubleslotted flaps, alone or with leadingedge devices, 94027, 94031
 effect of leadingedge highlift devices alone, 94027
 effect of plain flaps, alone or with leadingedge devices, 94027, 94028
 effect of singleslotted flaps, alone or with leadingedge devices, 94027, 94030
 effect of split flaps, alone or with leadingedge devices, 94027, 94029
 effect of tripleslotted flaps, alone or with leadingedge devices, 94027, 94031
 introduction to Data Items on effect of highlift devices on, 94026
 LiftCurve Slope
 in inviscid subcritical flow, 72024
 in subcritical compressible flow, 97020
 program to predict for lowdrag GUNACAseries, 99003
 LiftCurve Slope From Zero to Maximum Lift
 behaviour when leading and/or trailingedge highlift devices are deployed, 94026
 program to predict, 99031
 with or without leading and/or trailingedge highlift devices deployed, 96003
 Lift Estimation at Supersonic Speeds, AERO W.S.00.03.03, AERO W.S.00.03.05
 Lift Estimation in Viscous Subsonic or Transonic Flow Using VGK, 96028, 96029
 comparison of results with experimental results, with or without control deflection, 96028
 comparison of results with other theoretical results, 96028
 effect of leading or trailingedge sealed control or flap deflection, 96028, 96029
 LowDrag Design by CFD Techniques
 using multivariate gradient search optimisation, 00022, 00023, 01024, 99019, 99020, 99021
 LowDrag Design by Maintaining Favourable Pressure Gradient on Forward Upper and Lower Surfaces
 characteristics of NACA 6 and 6Aseries and GUNACAseries, 99003
 comparison of geometric and inviscid flow characteristics of NACA 6 and GUNACAseries, 99003
 discussion of theoretical methods for inviscid flow, 99003
 program for geometric and inviscid flow characteristics of GUNACAseries, 99003
 Maximum Lift Coefficient at Mach Number 0.6 to 0.75, AERO W.01.01.07
 Maximum Lift Coefficient in LowSpeed Flow, 84026, 93015
 effect of doubleslotted flaps, alone or with leadingedge devices, 94027, 94031
 effect of leadingedge highlift devices alone, 94027
 effect of leadingedge roughness, 84026, 93015
 effect of plain flaps, alone or with leadingedge devices, 94027, 94028
 effect of singleslotted flaps, alone or with leadingedge devices, 94027, 94030
 effect of split flaps, alone or with leadingedge devices, 94027, 94029
 effect of tripleslotted flaps, alone or with leadingedge devices, 94027, 94031
 introduction to Data Items on effect of highlift devices on, 94026
 NACA 6 and 6ASeries for Low Drag Over a Range of Lift Coefficient
 comparison of geometric and inviscid flow characteristics with those of GUNACAseries, 99003
 Normal Pressure Drag in Sonic Freestream, 69013
 Optimisation for Minimum Drag (Multivariate Gradient Search Using CFD Codes)
 introduction to method, 99019
 varying camber line shape and highlift device deflections (two design points), 99021
 varying camber line shape or highlift device deflections (single design point), 99020
 varying highlift device deflections on combat aircraft section (single design point), 00022, 00023
 varying surface geometry and highlift device deflections (two design points), 01024
 Oscillating in Heave or Pitch or With an Oscillating Control
 introduction to calculation methods in subsonic or supersonic flow, 82020
 lift and pitching moment in subsonic flow, 81034
 lift and pitching moment in supersonic flow, 82005
 pressure distribution in subsonic flow, 81034
 pressure distribution in supersonic flow, 82005
 Pitching Moment at Angle of Attack
 all highlift devices, 03017
 Pitching Moment at Zero Angle of Attack
 effect of doubleslotted flaps, alone or with leadingedge highlift devices, 01013, 99014
 effect of leadingedge highlift devices, alone or with trailingedge flaps, 00029, 01013
 effect of plain flaps, alone or with leadingedge highlift devices, 01013, 98017
 effect of singleslotted flaps, alone or with leadingedge highlift divices, 01013, 99004
 effect of split flaps, alone or with leadingedge highlift devices, 01013, 98009
 effect of tripleslotted flaps, alone or with leadingedge highlift devices, 01013, 99014
 Pitching Moment at Zero Lift
 in inviscid subcritical flow, 72024
 program to predict for lowdrag GUNACAseries, 99003
 Pitching Moment Estimation in Viscous Subsonic or Transonic Flow Using VGK, 96028, 96029
 comparison of results with experimental results, 96028
 effect of leading or trailingedge sealed control or flap deflection, 96028, 96029
 Pressure Distribution
 comparison of experimental with calculated by viscouscoupled method, 92008
 condition for equivalent streamwise distribution on swept wing, 78009
 for given dragrise Mach number, 71020
 program to predict for lowdrag GUNACAseries, 99003
 section design to provide specified uppersurface values in transonic flow, 99032
 supersonic flow, AERO W.S.00.03.03, AERO W.S.00.03.05
 use of rooftop to inhibit transition and give low drag, 99003
 windtunnel blockage effects in viscous transonic flow, 81019
 Pressure Distribution Estimation in Inviscid Subsonic Flow, 72025, 79009
 Pressure Distribution Estimation in Inviscid Transonic Flow, 79009
 Pressure Distribution Estimation in Sonic Free Stream, 69013, TD MEMO 6511
 Pressure Distribution Estimation in Viscous Subcritical Flow by FirstOrder Method, 76002
 Pressure Distribution Estimation in Viscous Subsonic or Transonic Flow Using VGK, 96028, 96029
 comparison of results with experimental results, with or without control deflection, 96028
 comparison of results with other theoretical results, 96028
 effect of leading or trailingedge sealed control or flap deflection, 96028, 96029
 influence of grid size on results, 96028
 influence of values of variable parameters in program on results, 96028
 program user manual, 96029
 use in prediction of shockinduced separation, 97030
 Pressure Distribution Estimation in Viscous Transonic Flow, 81019
 Profile Drag, AERO W.02.04.00, AERO W.02.04.02, AERO W.02.04.03, AERO W.S.02.04.13
 estimation of minimum for cambered or uncambered with fixed transition, 00027
 increment due to deployment of singleslotted flap, 87005
 variation of minimum with Mach number below drag rise, 00027
 Separation Characteristics
 discussion and illustration of shockinduced separation types, 90008
 effect at low speed on behaviour of lift curve, 66034
 limits to control of shockinduced by vortex generators, 93024, 93025
 reattachment point on upper surface, 91021
 shock/boundary layer interaction length, 90008
 shockinduced separation bubble length, 90008, 91021
 types of separation at low and transonic speeds, 87012
 upstream Mach number for flow breakdown at transonic speeds, 90008, 91021
 Separation Prediction at Subcritical Speeds
 method for leading or trailingedge separation, 88030
 Separation Prediction at Transonic Speeds
 application of VGK for, 97030
 boundary layer criteria for shockinduced separation on uppersurface, 81020
 bubble length and reattachment point, 91021
 comparison of results obtained using VGK with experimental data, 97030
 criteria for shockinduced flow breakdown, 91021
 flow breakdown boundary from pressure distribution and boundary layer characteristics, 91021
 separation boundary from computed pressure distribution/boundary layer, 81020, 97030
 separation boundary obtained directly from computed pressure distribution, 92008
 Shock Waves on
 behaviour with varying Mach number or angle of attack at transonic speeds, 90008
 oscillation at transonic speeds, 87012
 Similarity Laws Applied to Lift, Pitching Moment, Pressure and Pressure Drag Coefficients
 in subsonic, supersonic and transonic flows, 97025
 Skin friction drag
 in presence of pressure field, 06001
 Supersonic Flow, AERO W.S.00.03.03, AERO W.S.00.03.05
 Surface Finish
 effect of roughness on transition, AERO W.02.04.09
 effect of waviness on transition, AERO W.02.04.11
 Velocity Distribution
 program to predict for lowdrag GUNACAseries, 99003
 Wakes

 see
 Wakes
 WindTunnel Corrections
 openjet or perforated, slotted or solidwalled tunnels, 76028
 Charts of DragRise Mach Number, 71019
 adaptation to threedimensions, 72027
 Design of GUNACASeries for Low Drag Over a Range of Lift Coefficient
 geometric and inviscid flow characteristics, 99003
 Designs for Given DragRise Mach Number, 71020
 influence of design parameters, 71020
 profile drag at design condition, 67011
 NACA 6 and GUNACASeries for Low Drag Over a Range of Lift Coefficient
 comparison of geometric and inviscid flow characteristics, 99003
 Charts of DragRise Mach Number, 78010
 see
 Derivatives
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