ESDU A-Z Index: SHI-SOK

A B C D E F G H I J K L M N O P Q R S T U V W X Y Z

Shielding

Estimation of Attenuation of Sound Pressure Levels

see: Barriers

Estimation of Jet-by-Jet

see: Jet Noise

From Wind or Other Fluid Flows by Structures

see: Boundary Walls and Fences; Normal Force; Profile Drag; Response of Buildings and Structures; Sideforce

Shock-Associated or Shock Cell Noise

Description of Origins in Gas Turbine Exhaust and Typical Spectrum, 02020

Shock Detachment Conditions

Cones: effect of cone angle and Mach number, 70008, 70009, 70010, AERO S.00.03.16
Wedges: effect of wedge angle and Mach number, AERO S.00.03.16; effect of wedge angle, specific heat capacity and Mach number, AERO 00.03.30

Shock-Expansion Theory

Description, AERO W.S.00.03.03

Shock Wave/boundary Layer Interaction

see: Aerofoils; Flow Separation; Vane Vortex Generators; Wings

Shock Waves

see also: Airframe Noise (Aeroplanes Not Propeller Powered); Cavities; Jet Noise

Buffeting at Transonic Speeds Caused by Oscillation and Induced Separation on Aerofoils, 87012

Conical

detachment conditions, 70008, 70009, 70010, AERO S.00.03.16

flow deflection in conical flow field, 70009

inclination to upstream flow direction, 70008, AERO S.00.03.13

Mach number in conical flow field, 70010

Normal

air in dissociation equilibrium, AERO S.00.03.22

downstream Mach number and downstream static pressure, 69026

downstream stagnation pressure, 69026, 82018

ratio of static to total pressure behind in hypersonic flow, 93020

various specific heat capacity ratios, AERO 00.03.28

Oblique

air in dissociation equilibrium, AERO S.00.03.23

detachment conditions, AERO 00.03.30, AERO S.00.03.16

downstream Mach number, AERO S.00.03.09, AERO W.S.00.03.05

downstream static pressure, AERO 00.03.30, AERO S.00.03.09, AERO S.00.03.14, AERO W.S.00.03.05

downstream total pressure, AERO S.00.03.09

inclination to flow direction, AERO S.00.03.09

On Aerofoils at High Subsonic Freestream Mach Numbers

behaviour with varying Mach number and angle of attack, 90008

On Swept Wings

design considerations to minimise drag rise in transonic flow, 97017

typical patterns at transonic speeds, 90008

Separation Induced by

see: Aerofoils; Wings

Short Cracks

see: Aluminium Alloy Bars and Plates; Aluminium Alloy Sheets; Aluminium-Lithium Alloy Bars; Aluminium-Lithium Alloy Plates and Sheets; Austenitic Stainless Steels; High Tensile Low Alloy Steels; Low Tensile Low Alloy Steels; Titanium Alloy (Ti-6Al-2Sn-4Zr-6Mo); Titanium Alloy (Ti-6Al-4V); Titanium Alloy (Ti-6Al-5Zr-0.5Mo-0.25Si); Titanium Alloys

Short-Period Oscillation

Aircraft Longitudinal Stability and Response: desirable characteristics for good aircraft handling qualities, 92006; discussion of origin and characteristics, 86021; influence of aircraft flexibility on, 96037; requirements for damping and frequency for military aircraft, 92006

Shot Peening

see also: Wear Resistant Surface Coatings and Treatments

Consideration of Resulting Surface Finish and Effect on Fatigue Strength, 19004

Effect on Fatigue Strength

see also: Aluminium Alloys; Steels; Titanium Alloy (Ti-6Al-4V); Welded Transverse Joints in Aluminium Alloys; Welded Transverse Joints in Steels Under Axial Loading

comparison with effect of other surface treatments, 89031

discussion of advantages and limitations, 89031

helical springs, 83002

splined steel shaft assemblies, 73002

Effect on Fatigue Strength of Helical Steel Springs, 19003

Effect on Fretting Fatigue of Aluminium Alloys, 89004

Effect on Fretting Fatigue of Titanium Alloys, 88027

Need to Consider Use of Treatment at Design Stage, 19004

Parameters Affecting Depth of Plastically Deformed Material, 19004

Use of Almen Strip to Assess Intensity, 19004

Shrink Fits

see: Shafts with Interference-Fit Collars

Sideforce

see also: Aircraft Tyres; Sideforce Due To Rolling (Y_p or C_yp); Sideforce Due To Rudder Deflection (Y_ζ or C_{y Δr}); Sideforce Due To Sideslip (Y_v or C_{y β}); Sideforce Due To Yawing (Y_v or C_yr)

Angle-Section Beams, 82007: effect of incidence, yaw and velocity profile, 82007; effect of interference when used in X- or T-configuration, 82007
Channel-Section Beams, 82007: effect of incidence, yaw and velocity profile, 82007; effect of interference when used in H-configuration, 82007
Elliptical-Section Cylinders Normal to Flow: effect of incidence and section aspect ratio, 79026; effect of turbulent shear flow for surface-mounted, 79026
Forebody-Cylinders at Mach Numbers Below 1.2 and Incidences Above 20?: discussion of sources, 89014; effect of Mach number and Reynolds number, 89014; effect of nose blunting, 89014; envelope of overall maximum with crossflow Mach number, 89014; typical axial distributions, 89014
Frameworks of Flat-Sided and/or Tubular Members, 81027: effect of gusset plates and ancillary components, 81027; effect of incidence and yaw, turbulence and velocity profile, 81027; effect of roughness, taper and solidity, 81027
H-Section Beams, 82007: effect of incidence, yaw and velocity profile, 82007
Information on the use of Data Items on yawing moment and sideforce derivatives of an aircraft, AERO A.07.01.00
In-Plane of Single or Contra-Rotating Propellers at Low Forward Speeds: due to local angle of sideslip, 89047
I-Section Beams, 82007: effect of incidence, yaw and velocity profile, 82007
Lattice Towers of Flat-Sided and/or Tubular Members, 81028: effect of chord member arrangement, 81028; effect of gusset plates and ancillary components, 81028; effect of incidence, turbulence and velocity profile, 81028; effect of roughness and solidity, 81028
Multi-Sided Section Cylinders Due to Vortex Shedding: rms value obtained from two-dimensional mean drag, 90036
Pair of Circular-Section Cylinders Normal to Flow on Axis Inclined to Sub- or Supercritical Flow: effect of axis inclination, 84015; effect of roughness and spacing, 84015; on downstream or upstream cylinder, 84015
Pair of Circular-Section Cylinders Normal to Flow on Axis Normal to Flow: effect of spacing in subcritical flow, 84015
Paraboloidal Antennas: discussion of hysteresis effect, 82031; effect of focal length and incidence, 82031; effect of perforated or slatted surface, 82031; effect of shear flow, 82031
Rectangular-Section Cylinders Normal to Flow: blockage effects in duct, 71016, 80024; effect of edge rounding, 71016, 80003; effect of section aspect ratio and turbulence in uniform flow, 71016; effect of section aspect ratio, incidence and turbulence in shear flow, 80003; effect of turbulent shear flow for surface-mounted, 80003
Square-Section Cylinders Normal to Flow: blockage effects in duct, 71016, 80024; effect of edge rounding for various incidences, 71016, 80003; effect of incidence and turbulence in shear flow, 80003; effect of incidence and turbulence in uniform flow, 71016; effect of turbulent shear flow for surface-mounted, 80003
Surface-Mounted Circular-Section Cylinders: effect of isolated spanwise protuberances, 81017
T-Section Beams, 82007: effect of incidence, yaw and velocity profile, 82007
Two-Dimensional Circular-Section Cylinders Inclined to Flow: distributed roughness effects, 80025; turbulence effects, 80025
Two-Dimensional Circular-Section Cylinders Normal to Flow: effect of isolated spanwise protuberances, 80025; effect of nearby flat surface, 80025
Two-Dimensional Rectangular-Section Cylinders Normal to Flow: effect of edge rounding, 71016; effect of section aspect ratio and turbulence, 71016
Two-Dimensional Square-Section Cylinders Normal to Flow: effect of edge rounding for various incidences, 71016; effect of incidence and turbulence, 71016
Two-Dimensional Stranded Cables Inclined to Flow, 80025
X-Section Beams, 82007: effect of incidence, yaw and velocity profile, 82007

Sideforce Due To Rolling (Y_p or C_yp)

Contribution Due to Fin/Tailplane Combination: subsonic attached flow, 83006
Contribution Due to Wing (Zero Camber and Twist) in Attached Flow: discussion of edge forces, 81014; effect of compressibility, 81014; effect of dihedral, 85006
Use for Complete Aircraft of Data Items on Component Contributions: accuracy, 85010; comparison of experimental and predicted variation with incidence, 85010; example, 85010

Sideforce Due To Rudder Deflection (Y_ζ or C_{y Δr})

Estimation at Low Speeds: from geometry of rear fuselage and empennage, 87008

Sideforce Due To Sideslip (Y_v or C_{y β})

End Plate Effect: fins on tailplane, 92007; tailplane on fin, 00025, 82010, AERO C.01.01.01
Estimation for Wing-Body Combination, 00025, 79006
Fin Contribution: single fin (fuselage height/width near one), 00025, 82010; single fin merging into fuselage including tailplane effects, AERO C.01.01.01; single or twin fins at supersonic speeds, 91031; single or twin fins (range of fuselage height/width), 93007; tailplane-mounted twin fins, 92007
Flap Contribution, 00025, 81013
Nacelle Contribution (Propeller Type) on Wing, 00025, TM 178
Nacelle Contribution (Turbine Engine Type): rear-fuselage mounted/empennage interference, 73006; underwing mounted, 00025, 73006
Program to Calculate for Complete Aircraft, 00025
Tailplane Effects, 00025, 81032, 82010, 93007
Use for Complete Aircraft of Data Items on Component Contributions: accuracy, 82011; examples, 00025, 82011
Ventral Fin Contribution: single or twin at subsonic or supersonic speeds, 92029

Sideforce Due To Yawing (Y_v or C_yr)

Body Contribution, 83026
Fin Contribution: single fin merging into fuselage including tailplane effects, AERO C.01.01.01; single fin mounted on fuselage including tailplane effects, 82010; single or twin fins at supersonic speeds, 91031; tailplane-mounted twin fins, 92007
Simplified Method of Estimation, 84002
Use for Complete Aircraft of Data Items on Component Contributions: accuracy, 84002; comparison of experimental and predicted variation with incidence, 84002; example, 84002

Sideslip

see: Asymmetric Flight; Nacelle; Propellers; Rolling Moment Due To Sideslip (L_v or C_{l β}); Sideforce Due To Sideslip (Y_v or C_{y β}); Sideslipping Flight; Yawing Moment Due To Sideslip (N_v or C_nβ)

Derivation of Angle of Sideslip from Flight Test Data, TM 190
Determination of angle of sideslip using INS/GPS method, 17013, TM 185

Sideslipping Flight

Steady Level With or Without Failed Engine: calculation of aileron and rudder deflections and their order of magnitude, 01010; equations of motion, 01010; loading on fin, fuselage, tailplane and wing, 01010

Sidespillage

Rectangular External-Compression Double- or Single-Ramp Intakes: effect of sidewall shape on mass flow, 75005

Sidewash

Influence on sensor location, 17013

Silencers

In Air-Conditioning Duct Systems

see: Noise in Air-Conditioning Duct Systems

Silicate Esters

see: Lubricants

Silicones

see: Lubricants

Similarity Laws

Application to Fan Performance, 79037
Application to Pump Performance, 80030
Derivation in Subsonic or Supersonic Two- or Three-Dimensional or Axisymmetric Flow: for pressure coefficient from linearised equation, 97025
Derivation in Transonic Two- or Three-Dimensional Flow: for pressure coefficient from non-linear equation, 97025
Example of Use in Correlating Experimental Results: base pressure on conical afterbodies in subsonic, transonic and supersonic flow, 98026; drag of wedge in subsonic and supersonic flow, 97025
Hypersonic, AERO B.S.02.03.01, AERO B.S.05.03.01
Supersonic-Hypersonic, AERO B.S.02.03.01
Transonic: use in correlation of pressure correction data for static pressure sensor, 95024
Use of Laws Applied to Pressure Coefficient: for correlating data on drag, lift and pitching moment coefficients, 97025

Similarity Parameters

see: Dynamical Similarity

Simple-Wave Flow

Air in Dissociation Equilibrium: solution using Mollier chart, AERO S.00.03.27
Description, AERO W.S.00.03.03
Downstream Mach Number: low Mach numbers, AERO S.00.03.08, AERO W.S.00.03.05
Downstream Static Pressure: low Mach numbers, AERO W.S.00.03.05; Mach numbers from 1 to 20, AERO 00.03.31
Flow Deflection Angle: low Mach numbers, AERO S.00.03.08; Mach numbers from 1 to 20, AERO 00.03.31
Introduction to Simple-Wave Flow or Prandtl-Meyer Expansion, AERO S.00.03.06

Simple Wave Theory

Description, AERO W.S.00.03.03

Sintered Bearings

see: Dry Rubbing Bearings; Self-Contained Bearing Assemblies

SI Units

Conversion Factors

see: Conversion Factors

Size

see also: Screw Threads; Welded Joints in Steels

Effect on Fatigue Strength of Components: explanation using fracture mechanics, 87016; with or without a stress raiser, 87016

Skewness

Statistics: definition, 74030, 92040

Skew Panels

see: Flat Parallelogram Panels

Skew Plates

see: Flat Parallelogram Plates

Ski-Jump Performance

Vectored-Jet-Thrust Aircraft: calculation of launch trajectory, 87037; end-speed limits imposed by ramp, 87037; height drop and relationship with launch speed, 87037; launch speed margins and comparison with those for flat deck, 87037; minimum launch speeds, 87037; non-dimensional parameters appropriate and their derivation, 87037; safety margins, 87037

Skin Friction Drag

Aerofoils

computation using VGK in subsonic or transonic flow, 96028, 96029

prediction in presence of pressure field, 06001

program to predict minimum for subcritical speeds, 06020

Bodies

brief discussion, AERO B.S.02.03.01

Definition, AERO W.S.00.03.03, AERO W.S.02.04.13

Discussion of Effect of Surface Finish, AERO W.02.04.00

Due to Impingement on Airframe of Tyre Sidespray for Runway Contaminated With Slush/Water

see: Impingement Drag

Flat Plates at Zero Incidence in Subsonic or Supersonic Flow

applied to circular-section cylinders at zero incidence in subsonic flow, 68019, 68020, 73016

applied to circular-section cylinders at zero incidence in supersonic flow, 68019, 68020, 73016

applied to cones at zero incidence in supersonic flow, 68019, 68020, 73016

applied to wedges in supersonic flow, 68019, 68020, 73016

equation for local for turbulent boundary layer on smooth surfaces, 94044

equation for mean for turbulent boundary layer on smooth surfaces, 78019, 94044

graph of local for laminar boundary layer on smooth surfaces, 68019

graph of local for turbulent boundary layer on smooth surfaces, 68020, TM 213

graph of mean for laminar boundary layer on smooth surfaces, 68019

graph of mean for turbulent boundary layer on rough surfaces, 73016

graph of mean for turbulent boundary layer on smooth surfaces, 68020, TM 213

graph of mean for varying transition position on smooth surfaces, 78019

Use of Form Factors to Calculate Profile Drag, 97016

aerofoils, 00027, 00027, AERO W.02.04.00

Skin-Rib Joints in Aluminium Alloys

see also: Fretting Fatigue; Skin-Rib Joints in General

Fatigue Strength Under Acoustic Loading: attachment method effects, 72015; cladding effects, 72015; design of test specimens and test techniques under simulated loading, 93027; endurance of integral or riveted skin-rib attachment (skin excited), 72015; endurance of riveted rib-flange (rib excited), 72015; location of failures, 72015; low temperature effects, 72015; material specification and jointing compound effects, 72015; mean stress effects, 72015; skin thickness effects, 72015; test frequency effects, 72015

Skin-Rib Joints in Composite Structures

Fatigue Strength Under Acoustic Loading of Bonded, Co-cured or Riveted: aluminium-glass fibre epoxy (GLARE) stiffener and skin, 84027; boron- or carbon-epoxy or titanium rib, 84027; boron- or carbon-epoxy or titanium rib with carbon-epoxy or titanium doubler, 84027
Fatigue Testing Under Acoustic Loading: design of test specimens and test techniques for simulated conditions, 93027

Skin-Rib Joints in General

see also: Skin-Rib Joints in Aluminium Alloys; Skin-Rib Joints in Composite Structures; Skin-Rib Joints in Titanium Alloys

Effect of Bonding or Rivets on Local, Overall, Torsional or Torsional-Flexural Buckling: in panels under uniaxial compression, 98016; in panels under uniaxial compression, taking account of plasticity, 01001

Skin-Rib Joints in Titanium Alloys

see also: Fretting Fatigue; Skin-Rib Joints in General

Fatigue Strength Under Acoustic Loading: attachment method effects, 10011; design of test specimens and test techniques under simulated loading, 93027; endurance of plain specimens, 10011; endurance of riveted or spot-welded skin-rib attachment (skin excited), 10011; high temperature effects, 10011; location of failures, 10011; material specification effects, 10011; skin thickness effects, 10011; test frequency effects, 10011

Slagging

see: Fouling in Combustion Plant

Slats

see: Leading-Edge High-Lift Devices

Slender Wings

Aerodynamic Centre, Centre of Pressure and Pitching Moment, 71006
Axial Force and Lift Dependent Drag, 71006
Increments in Normal Force and Pitching Moment Due to Ground Effect, 71007
Normal Force and Normal-Force-Curve Slope, 71006

Slider-Crank Mechanisms

see also: Balancing of Linkages; Force Balancing of Linkages; Linkages; Moment Balancing of Linkages

Analysis, 76005, 81033, ME1
Coupler Maximum End-Load and Corresponding Crank Angle, 76005, 81033, ME1
Crank Angle Between Dead Centres, 76005, ME1
Crank Maximum Inertia Torque and Corresponding Crank Angle, 76005, 81033, ME1
Design Practical Considerations, 76005, ME1
Extension, 76005, 81033, ME1
Extreme Transmission Angles, 76005, 81033, ME1
Offset Swinging Block, 76005, 81033, ME1
Performance Curves for One Complete Crank Rotation: connecting-rod acceleration, angle of swing and velocity, 81033; crank inertia torque, 81033; force on connecting rod, 81033; rocker angle of swing, 81033; slider acceleration and velocity, 81033; transmission angle, 81033
Pin Forces: equations for forces at all joints by kinetostatic method, 90022; equations for forces at coupler joints using simple idealisations, 76005, 81033, ME1
Return Ratio, 76005, ME1
Slider Maximum Velocity and Corresponding Crank Angle, 76005, 81033, ME1
Slider Stroke, 76005, 81033, ME1
Synthesis, 76005, ME1

Slideways

Machine Tools: guidance on typical behaviour of friction coefficient, 89044

Slip Ratio

Braked Tyre: definition and mechanism for existence, 16008; effect on friction coefficient, 16008

Slipstream

Interference With Airframe: discussion of thrust/drag accounting, 85015, 85017; effect on airframe drag, 85015, 85017; effect on propeller thrust, 85015, 85017; effect on rolling moment in sideslip, 06012; estimation of drag/thrust of propeller/body combination, 86017; estimation of lift on wing/flap/nacelle combination, 88031; estimation of longitudinal force on wing/flap/nacelle combination, 88031; modelling in incidence and sideslip, 06013

Slots in Bars or Strips

Axial Loading: stress concentration data, 09014

Slotted Flaps

see also: Downwash; Flaps; Interference; Jet/flap Interference

Contribution to Airframe Noise, 90023
Introduction to Data Items on Effect of High-Lift Devices on Drag, Lift and Pitching Moment, 97002
Lift Increment Due to Deployment on Aerofoils at Zero Angle of Attack: double- or triple-element alone or with leading-edge high-lift devices, 94026, 94027, 94031; single-element alone or with leading-edge high-lift devices, 94026, 94027, 94030
Lift Increment Due to Deployment on Wings at Zero Angle of Attack: double- or triple-element alone or with leading-edge high-lift devices, 95021, 96032, 97002; single-element alone or with leading-edge high-lift devices, 93019, 96032, 97002
Maximum Lift Increment Due to Deployment on Aerofoils: double- or triple-element alone or with leading-edge high-lift devices, 94026, 94027, 94031; single-element alone or with leading-edge high-lift devices, 94026, 94027, 94030
Maximum Lift Increment Due to Deployment on Wings: single- or multi-element, 91014; single- or multi-element with leading-edge high-lift devices, 92031
Normal Force on: single-element, AERO F.05.01.01
Pitching Moment Due to Deployment on Aerofoils and Wings: double- or triple-element, alone or with leading-edge high-lift devices, 01013, 03017, 99014; single-element, alone or with leading-edge high-lift devices, 01013, 03017, 99004
Profile Drag Increment Due to Deployment on Wings: single-element of NACA and Handley Page type, AERO F.02.01.06, AERO F.02.01.06; single-element of optimum geometry on aerofoils, 87005; single-element of optimum geometry on wings, 08013
Trailing Vortex Drag Increment Due to Deployment on Cambered and Twisted or Plane Wings: program for estimation for any flap and wing geometry, 01007; tabulated values for selected flap and wing geometries, 01007