Tests were conducted in Langley Unitary Plan wind tunnel to determine stability characteristics of 0.10-scale model of second and third stages of 3-stage rocket vehicle; 2 fin sizes and planforms, delta and clipped delta, were tested at Mach 3.96 and 4.65 at about 10× 106 Re based on model length; test results are compared with calculated data.
Static longitudinal stability of rocket vehicle having rear-facing step ahead of stabilizing fins
NASA -- Tech Notes
1961
22 pages
Report
Englisch
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