Tests made at Mach 0.60 to 1.20; Reynolds number, based on mean geometric chord, varied from about 2.2×106 to 5.7×106; comparisons are made with data from NASA -- Tech Note D-655 to show effects on longitudinal stability and performance of blunting model nose, leading edge, and ridge line.
Static longitudinal aerodynamic characteristics at transonic speeds of blunted right triangular pyramidal lifting reentry configuration for angles of attack up to 110°
NASA -- Tech Note
1961
38 pages
Report
English
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