Design Guide for Pitch-up Evaluation and Investigation at High Subsonic Speeds of Possible Limitations Due to Wing-aspect-ratio Variations
National Aeronautics and Space Administration, 1959 - Airplanes - 37 pages
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10-foot tunnel Aerodynamic Characteristics angle of attack aspect ratio base pressure drag Boundary related C0NFIDENTIAL cd H Pi Complete Model curve labeled Delta Wing design guide presented effects of wing-aspect-ratio figure 3(b following the initial fuselage geometric given in figure guide with respect H P cd high lift range High Subsonic Speeds highly tapered wings horizontal tail horizontal-tail position increase in stability increased tail-off stability increasing lift initial stall Jaquet Jet-Boundary Corrections Kenneth Langley Field Langley high-speed lift coefficient Longitudinal Stability Mach number range Maggin mean aerodynamic chord mean test NASA pitch-up are minimized Pitching Moments pitching-moment linearity pitching-moment nonlinearity pressure drag coefficient ratio and sweep region show decreased tail-off significant Spreemann stability with increasing stabilizer deflection stall before pitching Static Stability Supersedes NACA RM sweep angle tail contribution tail position taper ratio tions transonic speed range wing aspect wing plan forms wing-aspect-ratio variations wing-fuselage combination