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106 per foot 2.40 and Reynolds Aerodynamic aft cowl aft lips base pressure friction boundary-layer survey civil transport HSCT corrected for base decrease dimensions are given diverter wedge half-angle drag characteristics drag coefficient drag measurements effect of diverter Effect of Reynolds filler plate flat plate flat-plate boundary layer flat-plate surface flow field given in inches half-angle and nacelle instrumentation cavity interference drag internal flow drag Langley Research Center Langley Unitary Plan leading edge linear dimensions linearly with increasing Mach number nacelle and diverter nacelle fore cowl nacelle internal nacelle lip height NASA numbers of 1.50 oblique shock pallet lip pressure pallet skin Plan Wind Tunnel plate and pallet pressure and skin pressure drag pressures or internal ranging from 2.00 reference area refs relative drag shock wave shown in figure skin friction skin-friction drag strain-gauge balance Supersonic Speeds Test Conditions tests were conducted uncertainty in measured Unitary Plan Wind Welge