The investigations of pressure distributions are presented for aeroloads analysis at Mach numbers from 1.55 through 2.5. Angles of attack and sideslip varied from -6 to +6 degrees. Photographs of wind tunnel models are shown. (Author)
Results of a Pressure Loads Investigation on a 0.030-Scale Model (47-Ots) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 9 by 7 Foot Leg of the Unitary Plan Wind Tunnel (Ia81b), Volume 1
1975
983 pages
Report
Keine Angabe
Englisch