Results are presented of a wind tunnel test on the directional stability of space shuttle booster configurations. The test was conducted at the 14-inch trisonic tunnel starting 6en1 December 1971 and continued through 11 December 1971 for a total of 66 occupancy hours. Configurations tested included a cylindrical body with two axisymmetrical noses, one with and without canopy, one delta wing, located in two positions, five vertical tails (including a V tail), two having split rudders, ventral fins, two sets of chines, three airbreathing engine pods, and rocket engine shrouds. The model scale was 0.003366. (Author)
Forebody and Vertical Stabilizer Effects on Directional Stability of a Reusable LOX/RP (061) Booster AR 12161-2
1972
273 pages
Report
No indication
English
Aerodynamic Properties of Vertical Stabilizer Placement for a Reusable Booster System
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