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Subsonic lift-dependent drag due to boundary layer of plane, symmetrical section wings. Introductory sheet on subcritical lift-dependent drag of wings. Lift-curve slope of swept and tapered wings. Pitching moment of low-aspect-ratio cropped-delta wings up to high angles of attack at subsonic speeds. (With Appendix A: effect of plain flaps.) Normal force of low-aspect-ratio cropped-delta wings up to high angles of attack at subsonic speeds.Ĭomputer program for estimation of spanwise loading of wings with camber and twist in subsonic attached flow. Program for calculation of maximum lift coefficient of plain aerofoils and wings at subsonic speeds. Normal force and pitching moment of low aspect ratio cropped-delta wings up to high angles of attack at supersonic speeds. The maximum lift coefficient of plain wings at subsonic speeds. Wing angle of attack for zero lift at subcritical Mach numbers.īoundaries of linear characteristics of cambered and twisted wings at subcritical Mach numbers. Wing pitching moment at zero lift at subcritical Mach numbers. Method for the rapid estimation of spanwise loading of wings with camber and twist in subsonic attached flow. Low-speed normal force and pitching moment of slender wings in ground effect Low-speed longitudinal aerodynamic characteristics of slender wings.
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Lift-curve slope and aerodynamic centre position of wings in inviscid supersonic flow. Lift-curve slope and aerodynamic centre position of wings in inviscid subsonic flow.ĮSDU TECHNICAL MEMORANDUM Wing lift-curve slope in inviscid subsonic flow: Improvements to the Helmbold-Diederich equation and comparison with data from ESDU 70011 Inviscid supersonic flow past cones at zero incidence: (iv) Mach number in the conical flow field. Inviscid supersonic flow past cones at zero incidence: (iii) flow deflection in the conical flow field. Inviscid supersonic flow past cones at zero incidence: (ii) surface pressure coefficient and shock angle for circular cones. Inviscid supersonic flow past cones at zero incidence: (i) shock angle.
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Solutions to the Prandtl-Meyer expansion relations for a range of specific heat ratios: pressure coefficient and maximum flow deflection angle. Solutions to the oblique shock wave relations for a range of specific heat ratios: pressure coefficient and detachment angle. Pitot and static tubes in supersonic flow.Ĭonditions for shock wave detachment and for subsonic flow behind nose shock waves on cones at zero incidence and on wedges.Ĭonditions behind normal shock waves in air in dissociation equilibrium.Ĭonditions behind oblique shock waves for air in dissociation equilibrium.Ĭonditions behind normal shock waves in a perfect gas for various values of γ. Introductory sheet on isentropic flow and shock waves.Īpproximate calculation of the pressure changes in two-dimensional supersonic flow.