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10-Foot Tunnel Aeronautics and Space aft of nose aft of x/c airfoil angle of attack boundary layer coefficients from 0.20 compressibility drag constant angle Continued drag coefficient Effect of horizontal Effect of nacelles executive jet Figure 21 Figure 9 forward and weakened forward portion fuselage given Mach number glove design glove region horizontal tail increment in drag jet to examine Langley High-Speed Langley Research Center leading edge longitudinal aerodynamic characteristics loss in lift Lower surface x/c z/c x/c z/c mean aerodynamic chord model longitudinal aerodynamic NACA nacelles caused nacelles on wing nacelles-on configurations nacelles—on NASA National Aeronautics negative pressure coefficients number and angle numbers from 0.40 outboard panel was modified partial—chord photographs of effect pressure orifice installation range of Mach Space Administration suction tail on wing Tests were conducted transonic U.S. Customary Units Wind Tunnels Wing Glove Wing oil—flow photographs wing panel wing pressure distributions