Tabulated Pressure Measurements of a NASA Supercritical-Wing Research Airplane Model with and Without Fuselage Area-Rule Additions at Mach 0.25 to 1.00
Tabulated Pressure Measurements of a NASA Supercritical-Wing Research Airplane Model with and Without Fuselage Area-Rule Additions at Mach 0.25 to 1.00
- New search for: C. D. Harris
- New search for: D. W. Bartlett
- New search for: C. D. Harris
- New search for: D. W. Bartlett
Basic pressure measurements were made on a 0.087-scale model of a supercritical wing research airplane in the Langley 8 foot transonic pressure tunnel at Mach numbers from 0.25 to 1.00 to determine the effects on the local aerodynamic loads over the wing and rear fuselage of area-rule additions to the sides of the fuselage. In addition, pressure measurements over the surface of the area-rule additions themselves were obtained at angles of sideslip of approximately - 5 deg, 0 deg, and 5 deg to aid in the structural design of the additions. Except for representative figures, results are presented in tabular form without analysis.
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Tabulated Pressure Measurements of a NASA Supercritical-Wing Research Airplane Model with and Without Fuselage Area-Rule Additions at Mach 0.25 to 1.00
1972
263 pages
Report
No indication
English