A testing technique for obtaining the static aerodynamic characteristics of twin-fuselage configurations at hypersonic speeds by using a conventional single-balance installation has been evaluated. Data from a triple-fuselage model and a single-fuselage model were summed and then halved to obtain the characteristics for a twin-fuselage model of the same scale. The three related models were evaluated experimentally at Mach 20.3 in helium and Mach 6 in air for an angle-of-attack range from minus 6 deg to 50 deg. The Reynolds numbers, based on model length, were 1.88 million for the Mach 20.3 tests and 2.55 million for the Mach 6 tests.
Aerodynamic testing technique for twin fuselage models at hypersonic speeds
1975-03-01
Report
No indication
English
Some Aerodynamic Decelerators for Hypersonic Speeds
NTIS | 1969
|Free-flight wind tunnel for aerodynamic testing at hypersonic speeds
Engineering Index Backfile | 1955
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