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10-ft Transonic 22-ft Subsonic Tunnel accurate prediction aerodynamic aft end angles of attack axis system boom boundary-layer canopy coefficient Daniel David F Dryden Flight Research dynamic pressure Erickson F-18 High Alpha F/A-18 aircraft F/A-18 configuration Figure 17 fineness ratio fixed forebody fixed transition Flight Research Center flight results flight tests forebody flow field forebody vortices full-scale flight Grit pattern ground-to-flight correlation High Alpha Research high angles high-angle-of-attack characteristics high-angle-of-attack conditions High-Angle-of-Attack Technology Conference higher Reynolds number interactions Langley Research Center lateral-directional stability leading-edge flap deflection LEX vortices lift coefficient Mach number maximum lift MD/Navy NASA Dryden Flight NASA Langley Research noseboom number effects off-surface flow visualization on-surface flow pattern O Nosering pressure ports Re-C shown in figure significant Station 142 suction peaks surface pressure distribution Tail Buffet tunnel and flight twin strips visualization of NASA visualization was obtained voided regions Vortex footprint vortical flow wind tunnel wing flow