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Aerodynamic characteristics of swept wing configuration with progressive series of leading and trailing edge modifications
An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory.
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Wind tunnel tests on sonic boom with models of three wing-fuselage combinations
Time-dependent aerodynamic forces with application to a wing deforming harmonically according to a general polynomial equation
Aerodynamic characteristics of lateral control with rotatable airfoils and sweptback wing
Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61
Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure
Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores
Static longitudinal and lateral aerodynamic characteristics of V/STOL aircraft with variable sweep wing
Aerodynamic center shifts of rigid wing-body combinations at increased Mach numbers
Wind tunnel tests to determine longitudinal aerodynamic characteristics of large scale semispan V/STOL tilt-wing configuration with single propeller
Longitudinal aerodynamic characteristics of large scale semispan V/STOL tilt-wing configuration having single propeller
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Explore the source record for details and available documents.
Explore the source record for details and available documents.
Explore the source record for details and available documents.