ESDU AZ Index: DDIG
 Use in Calculation of Forces and Internal Stresses in Accelerated Motion, 94009
 see
 Crack Length
 To Control Duct Noise
 Use to Improve Aircraft Lateral Control
 see also
 Damping Ratio
 Acoustic Radiation Damping
 beams and plates, TM 183
 Aircraft
 wings, fuselages, TM 183
 Buildings and Structures
 discussion of sources and effect of amplitude, 83009
 methods of measuring, 77032, 83009
 methods of supplementing, 77032, 83009
 methods of supplementing to reduce response of cylinders, 79025
 model tests to determine, 83009
 representation in response equations, 77032
 Compendium of Vibration Damping Data for Aerospace Structures, TM 183
 Discussion of Sources in Structures
 acoustic (fluid), 91012
 material (hysteretic), 91012
 structural, 91012
 Effect on Sound Power Radiation
 from dynamically excited rectangular plate, 00002
 FibreReinforced Laminated Composite Plates
 damping of composites, TM 183
 program for damping, 85012
 Linearised Coefficients for Hydrodynamic Axial Groove Journal Bearings
 database, 95023
 Materials Used to Increase Structural
 effects of frequency and temperature on loss factor and modulus, 91012, 92001
 values of specific damping capacity, 85012
 variation of loss factor and modulus with frequency and temperature for specific, 92001
 Measures for Linear Systems
 conversion between, 67038
 conversion between for small damping, 73011, 91012
 definitions, 22001, 67038, 73011, 77032, 83009, 91012
 Methods of Increasing Structural
 general discussion, 91012
 materials available for treatment, 91012, 92001
 use of additional constrained or free layers, 91012
 use of tuned dampers, 91012
 Prediction of Damping
 composite plates and honeycomb panels, TM 183
 Relationship of Aerodynamic to Airforce Coefficients (Flutter Derivatives), 82020
 Satellites
 satellite launch vehicles, spacecraft, TM 183
 Tube Bundles in ShellandTube Heat Exchangers
 in gas or liquid flows, 87019
 Use of Layered Treatments to Increase Structural
 damping treatments, TM 183
 estimation of increase due to free layers, 91012, 91013
 estimation of increase due to multiple constrained layers, 91012, 91013
 estimation of increase due to single constrained layer, 91012, 91013
 loss factor and modulus of specific layer materials, 92001
 Use of Tuned Dampers to Increase Structural, 91012
 Values of Acoustic
 for suppression of resonance in crossflow through tube banks, 88028
 Definition for Linear System, 67038
 Linear System

 see also
 Critical Damping Coefficient
 definition, 22001
 Definition for Linear System, 67038
 Aerodynamic Contribution
 buildings and structures, 83009, 87035, 88019, 89049
 Foundation Contribution
 brief discussion of soil/structure interaction, 83009
 Linear System
 definition, 22001, 67038, 73011, 77032, 83009, 91012
 Relationship With Loss Factor Used in Statistical Energy Analysis, 99009
 Structural Contribution
 approximate data, 77032, 87035, 88019, 91001, 96031
 estimation for first translational mode of tall buildings, 83009, 91001
 estimation for torsional and secondorder translational modes of tall buildings, 91001
 Typical Values
 composite panels, 91012, TM 183
 honeycomb sandwich panels, 73011, 91012, TM 183
 stiffened panels, 73011, 91012, 99009, TM 183
 Use as Parameter Defining Dynamical Similarity, 77032
 inclusion in stability parameter, 79025
 Variation With Frequency
 curved or flat riveted skinstringer panels, 73011
 honeycomb sandwich panels, 73011, TM 183
 integrallymachined panels, 73011
 Representation by Describing Functions in Analysis of NonLinear System, 84009
 see
 Parachutes
 ShellandTube Heat Exchanger Network Design Using Process Integration
 optimisation of costs and utility consumption, 00043
 Criterion for Prediction in Composite Plates From Interlaminar Stresses at Free Edges, 95028
 comparison with experimental data for specific cases, 95028
 Criterion for Prediction Under ThroughThickness Stresses, 94019
 Detection by NonDestructive Examination
 selection of method and minimum detectable flaw, 91027
 In Laminated Plates Tapered in Thickness by Ply DropOff
 program to predict uniaxial load for, 91003
 use of fracture mechanics to predict, 91003
 In SpeciallyOrthotropic Corner Section
 program to predict bending moment, radial shear and tangential direct load for, 94019
 Contribution to Airframe Noise, 90023
 Rolling Moment Due to Rollingat Supersonic Speeds
 effect of interference from cylindrical body, AERO A.S.06.03.02
 used in three or fourwing arrangements, AERO A.S.06.03.01, AERO A.S.06.03.03
 SharpEdged Cropped or Uncropped of Low Aspect Ratio
 centre of pressure in subsonic flow, 95022
 normal force and pitching moment in supersonic flow, 90013
 normal force in subsonic flow, 93034
 see also
 Air
 Description of Characteristics and Formation in Atmosphere, 87034
 see also
 Hinge Moment
 Axes Transformation, 67004, 86041
 Comparison of Alternative Definitions and Notation, 86021
 Concept and Definition, 67003, 77032, 86021
 Force Variation With Incidence
 beam sections, bridge decks and buildings, 93013
 LiftCurve Slope (Z sub w, C sub L alpha or C sub z alpha)

 see
 LiftCurve Slope
 Longitudinal
 calculation from force and moment coefficients, 86021
 Notation, 67001, 67002, 67003, 86021
 Pitching Moment Due to Acceleration in Heave (M sub w dot or C sub m alpha dot)
 forebodycylinders, low incidence/supersonic speeds, with or without boattailing and fins, 91004
 Pitching Moment Due to Heave (M sub w or C sub m alpha)
 forebodycylinders with boattailing at Mach Numbers up to 5, 87033, 89008
 forebodycylinders without boattailing at Mach Numbers up to 5, 89008
 Pitching Moment Due to Rate of Pitch (M sub q or C sub mq)
 accuracy of prediction for wing/body/tail combination, 90010
 contribution due to body at subsonic speeds, 90010
 contribution due to tailplane and wing at subsonic speeds, 90010
 contribution due to wing at supersonic speeds, AERO W.S.08.03.02
 effect of wing/body interference at subsonic speeds, 90010
 forebodycylinders, low incidence/supersonic speeds, with or without boattailing and fins, 91004
 Rolling Moment Due to Aileron Deflection (L sub xi or C sub l delta a)
 estimation at low speeds, 88013, 88040
 Rolling Moment Due to Rate of Roll (L sub p or C sub lp), AERO A.06.01.00
 contribution due to dihedral, 85006
 contribution due to single fin/tailplane combination, 83006
 contribution due to wing, AERO A.06.01.01
 contribution due to wing at supersonic speeds, AERO A.S.06.03.01
 effect of interference on wing from cylindrical body at supersonic speeds, AERO A.S.06.03.02
 example of calculation for complete aircraft, 85010
 three or fourwing arrangements on cylindrical body, AERO A.S.06.03.01, AERO A.S.06.03.03
 use of component contributions in prediction for complete aircraft, 85010
 Rolling Moment Due to Rate of Yaw (L sub r or C sub lr), AERO A.06.01.00
 bibliography on contribution due to wing in separated flow, 72021
 contribution due to fin, 82017
 contribution due to flaps, 72021
 contribution due to wing in attached flow, 72021
 example of calculation for complete aircraft, 84002
 use of component contributions in prediction for complete aircraft, 84002
 Rolling Moment Due to Rudder Deflection (L sub zeta or C sub l delta r)
 estimation at low speeds, 87008
 Rolling Moment Due to Sideslip (L sub v or C sub l beta), AERO A.06.01.00
 accuracy of prediction for complete aircraft, 81032
 comparison of experimental and predicted variation with incidence, 81032
 contribution due to body, 00025, 73006
 contribution due to flaps, 00025, 80034
 contribution due to fullspan dihedral, 00025, AERO A.06.01.03
 contribution due to nacelles (on wing for propeller driven aircraft), 00025, TM 178
 contribution due to nacelles (turbine engine rearfuselage mounted), 73006
 contribution due to nacelles (turbine engine underwing), 00025, 73006
 contribution due to partspan dihedral, 00025, AERO A.06.01.09
 contribution due to single fin (fuselage height/width near unity), 00025, 82010
 contribution due to single fin merging into fuselage, AERO C.01.01.01
 contribution due to single or twin fins (range of fuselage height/width), 93007
 contribution due to tailplanemounted twin fins, 92007
 contribution due to wing in attached flow, 00025, 80033
 effect of propellers, 06012
 effect of wingbody geometry and wing position, 00025, 73006
 examples of calculation for complete aircraft, 00025, 81032
 program to calculate for complete aircraft, 00025
 tailplane effects, 00025, 81032, 82010, 93007
 use of component contributions in prediction for complete aircraft, 00025, 81032
 Rolling Moment Due to Spoiler Deflection

 see
 Spoilers
 Sideforce Due to Rate of Roll (Y sub p or C sub yp), AERO A.07.01.00
 contribution due to dihedral, 85006
 contribution due to single fin/tailplane combination, 83006
 contribution due to wing (zero camber, dihedral and twist), 81014
 example of calculation for complete aircraft, 85010
 use of component contributions in prediction for complete aircraft, 85010
 Sideforce Due to Rate of Yaw (Y sub r or C sub yr), AERO A.07.01.00
 contribution due to body, 83026
 contribution due to fin, 82017
 example of calculation for complete aircraft, 84002
 use of component contributions in prediction for complete aircraft, 84002
 Sideforce Due to Rudder Deflection (Y sub zeta or C sub y delta r)
 estimation at low speeds, 87008
 Sideforce Due to Sideslip (Y sub v or C sub y beta), AERO A.07.01.00
 accuracy of prediction for complete aircraft, 82011
 contribution due to flaps, 00025, 81013
 contribution due to nacelles (on wing for propeller driven aircraft), 00025
 contribution due to nacelles (turbine engine rearfuselage mounted), 79006
 contribution due to nacelles (turbine engine underwing), 00025, 79006
 contribution due to single fin (fuselage height/width near one), 00025, 82010
 contribution due to single fin merging into fuselage, AERO C.01.01.01
 contribution due to single or twin fins at supersonic speeds, 91031
 contribution due to single or twin fins (range of fuselage height/width), 93007
 contribution due to single or twin ventral fins at subsonic or supersonic speeds, 92029
 contribution due to tailplanemounted twin fins, 92007
 discussion of contribution due to tailplane, 82011
 effect of wingbodytailplane interference on fin contribution at supersonic speeds, 91031
 estimation for wingbody combination, 00025, 79006
 examples of calculation for complete aircraft, 00025, 82011
 program to calculate for complete aircraft, 00025
 tailplane effects, 00025, 81032, 82010, 93007
 use of component contributions in prediction for complete aircraft, 00025, 82011
 Yawing Moment Due to Aileron Deflection (N sub xi or C sub n delta a)
 estimation at low speeds, 88029, 88040
 Yawing Moment Due to Rate of Roll (N sub p or C sub np), AERO A.07.01.00
 contribution due to dihedral, 85006
 contribution due to single fin/tailplane combination, 83006
 contribution due to wing (zero camber, dihedral and twist), 81014
 example of calculation for complete aircraft, 85010
 use of component contributions in prediction for complete aircraft, 85010
 Yawing Moment Due to Rate of Yaw (N sub r or C sub nr), AERO A.07.01.00
 bibliography on contribution due to wing in separated flow, 71017
 contribution due to body, 83026
 contribution due to fin, 82017
 contribution due to flaps, 71017
 contribution due to wing in attached flow, 71017
 example of calculation for complete aircraft, 84002
 use of component contributions in prediction for complete aircraft, 84002
 Yawing Moment Due to Rudder Deflection (N sub zeta or C sub n delta r)
 estimation at low speeds, 87008
 Yawing Moment Due to Sideslip (N sub v or C sub n beta), AERO A.07.01.00
 accuracy of prediction for complete aircraft, 82011
 contribution due to flaps, 00025, 81013
 contribution due to nacelles (on wing for propeller driven aircraft), 00025
 contribution due to nacelles (turbine engine rearfuselage mounted), 79006
 contribution due to nacelles (turbine engine underwing), 00025, 79006
 contribution due to single fin (fuselage height/width near one), 00025, 82010
 contribution due to single fin merging into fuselage, AERO C.01.01.01
 contribution due to single or twin fins at supersonic speeds, 91031
 contribution due to single or twin fins (range of fuselage height/width), 93007
 contribution due to single or twin ventral fins at subsonic or supersonic speeds, 92029
 contribution due to tailplanemounted twin fins, 92007
 effect of wingbodytailplane interference on fin contribution at supersonic speeds, 91031
 estimation for wingbody combination, 00025, 79006
 examples of calculation for complete aircraft, 00025, 82011
 program to calculate for complete aircraft, 00025
 tailplane effects, 00025, 81032, 82010, 93007
 use of component contributions in prediction for complete aircraft, 00025, 82011
 Yawing Moment Due to Spoiler Deflection

 see
 Spoilers
 ZForce Due to Rate of Pitch (Z sub q or C sub zq)
 contribution due to tailplane and wing at subsonic speeds, 90010
 contribution due to wing at supersonic speeds, AERO W.S.08.03.02
 effect of wing/body interference at subsonic speeds, 90010
 see
 Diesel Fuels
 Aerofoil Optimisation Examples (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
 Aerofoils for Low Drag Over a Range of Lift Coefficient
 by maintaining favourable pressure gradient on forward upper and lower surfaces, 99003
 Aerofoils to Provide Specified UpperSurface Pressure Distribution in Transonic Flow, 99032
 Allowable Stresses
 Concept and Preliminary Design Examples of Applying Rapid Aerodynamic Analysis Tools to Three Classic Historical Configurations Designed to Similar Requirements, TM 207
 Control Systems

 see
 Control Systems
 Estimation of Loads, SS1
 Guidance on the selection of aerodynamic methods to use at different stages of civil aircraft design, 21001
 Guide to Aerodynamic Considerations for Wings in Transonic Flow, 97017
 Guide to Use of Data Items on Analysis and Design of Cam/Follower Mechanisms, 01002, 94017
 Guide to Use of Winglets on Wings
 as additions to existing designs or incorporated at wing design initiation, 98013
 In Relation to Acoustic Fatigue
 aircraft structures, 20005, 86025
 detail aspects, 86025
 In Relation to Fatigue
 aircraft structures, 70018
 design to fatigue limit, 75022
 general principles, 71009
 Inverse Aerofoil Examples (Multivariate Gradient Search Using CFD Codes)
 to obtain complete or partial target pressure distribution, 01025
 Need to Take Into Account Effects of Using Shot Peening, 19004
 Need to Take Into Account Requirements for NonDestructive Examination Methods, 91027
 Safety Factors

 see
 Safety Factors
 Use of Stress Analysis Items, SS1
 see
 Atmosphere
 see
 Plates
 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
 Incorporation in Process Plant as Heat and Power Source Using Process Integration Techniques, 89001
 see
 Lubricants
 see also
 Linear Systems
 Pressure Drop Across, 66030
 Design Recommendations for Methods of Improving Performance
 axial or tangential blowing or boundary layer suction, 87015
 guidance on selection of appropriate method, 87015
 guide vanes or splitters, 87015
 hybrid diffusers, 87015
 roughness or transverse ribs, 87015
 screens or perforated plates, 87015
 vortex generators, 87015
 Discussion of Performance Measures and Their Presentation, 76027
 Effectiveness
 definition, 76027
 Effect of Various Flow Parameters on Performance
 inlet swirl, 76027
 Mach number and Reynolds number, 76027
 turbulence, 76027
 various upstream velocity profiles, 76027
 Effect of Various Geometry Changes on Performance
 addition of tailpipe, 76027
 bibliography on centre line curvature, 76027
 cross section shape and its variation along diffuser, 76027
 internal obstructions, 87015
 moving walls, 87015
 truncation, 76027, 87015, TM 19
 wall curvature, 76027, 87015
 Efficiency
 definition, 76027
 Ideal Pressure Recovery
 definition, 76027
 Interference From Adjacent Components, 76027
 Review of Calculation Methods, 76027
 Static Pressure Recovery in Compressible Flow
 definition of coefficients, 90025
 Static Pressure Recovery in Incompressible Flow
 definition of coefficients, 73024, 74015, 75026, 76027, 87015
 relative effects of inefficient and insufficient diffusion, 76027, TM 19
 Total Pressure Loss in Compressible Flow
 approximate derivation from static pressure recovery, 90025
 Total Pressure Loss in Incompressible Flow
 definition of coefficient, 73024, 74015, 75026, 76027, 87015
 relation with static pressure recovery, 73024, 74015, 75026, 76027, 87015
 Stress Analysis