Drag Measurements of an Axisymmetric Nacelle Mounted on a Flat Plate at Supersonic SpeedsNational Aeronautics and Space Administration, Langley Research Center, 1995 - Aerodynamics, Supersonic - 32 pages |
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... the following URL address : http://techreports.larc.nasa.gov/ltrs/ltrs.html Abstract. Drag Measurements of an Axisymmetric Nacelle Mounted on a Flat Plate at Supersonic Speeds ( a ) Photograph of boundary - layer rake .
... the following URL address : http://techreports.larc.nasa.gov/ltrs/ltrs.html Abstract. Drag Measurements of an Axisymmetric Nacelle Mounted on a Flat Plate at Supersonic Speeds ( a ) Photograph of boundary - layer rake .
Page 1
... speed civil transport ( HSCT ) configurations with extended supersonic range has spurred investigations into aircraft drag reduction at supersonic cruise conditions . Mutual aerodynamic inter- ference between the engine nacelles and ...
... speed civil transport ( HSCT ) configurations with extended supersonic range has spurred investigations into aircraft drag reduction at supersonic cruise conditions . Mutual aerodynamic inter- ference between the engine nacelles and ...
Page 15
... Supersonic Aircraft . NASA TN D - 3390 , 1966 . 2. Sigalla , Armand ; and ... Speeds . NASA TP - 2742 , 1987 . 13. Jackson , Charlie M. , Jr .; Corlett ... Supersonic Speeds . NASA TP - 1027 , 1977 . 17. Wilcox , Floyd J. , Jr ...
... Supersonic Aircraft . NASA TN D - 3390 , 1966 . 2. Sigalla , Armand ; and ... Speeds . NASA TP - 2742 , 1987 . 13. Jackson , Charlie M. , Jr .; Corlett ... Supersonic Speeds . NASA TP - 1027 , 1977 . 17. Wilcox , Floyd J. , Jr ...
Common terms and phrases
106 per foot 2.40 and Reynolds Aerodynamic aft cowl aft lips boundary-layer profiles boundary-layer survey corrected for base dimensions are given diverter wedge half-angle drag characteristics drag coefficient drag force drag measurements effect of diverter effect of nacelle Effect of Reynolds filler plate flat plate flat-plate boundary layer flat-plate surface flow field foam seal ft² given in inches half-angle and nacelle instrumentation cavity interference drag internal flow drag Langley Research Center lb/ft² leading edge linearly with increasing lowest hd Mach number nacelle and diverter nacelle drag nacelle fore cowl nacelle lip height nacelle/diverter base pressure NASA numbers of 1.50 oblique shock pallet lip pressures pallet skin friction Plan Wind Tunnel plate and pallet pressure and skin pressure drag ranging from 2.00 reference area refs relative drag shock wave shown in figure skin-friction drag strain-gauge balance Supersonic Speeds Test Conditions uncertainty in CD uncertainty in measured Unitary Plan Wind Welge