A 2.25% scale model of the space shuttle external tank and solid rocket boosters was tested in the NASA/Ames Unitary 11 x 11 foot transonic and 9 x 7 foot supersonic tunnels to obtain base pressure data with firing solid propellant exhaust plumes. Data system difficulties prevented the acquisition of any useful data in the 9 x 7 tunnel. However, 28 successful rocket test firings were made in the 11 x 11 tunnel, providing base pressure data at Mach numbers of 0.5, 0.9, 1.05, 1.2, and 1.3 and at plume pressure ratios ranging from 11 to 89.
Results of the NASA/Msfc FA-23 Plume Technology Test Program Performed in the NASA/Ames Unitary Wind Tunnels
1977
83 pages
Report
Keine Angabe
Englisch
PIV IN NASA AMES UNITARY WIND TUNNELS
British Library Conference Proceedings | 2011
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AIAA | 2011
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