Effect of Sideslip on the Flow over a 65-deg Delta Wing
DELFT UNIV OF TECHNOLOGY (NETHERLANDS)DEPT OF AEROSPACE ENGINEERING
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Flow-visualization tests, surface-pressure measurements and balance tests were conducted on a model of a flat-plate 65-deg swept delta wing in a low-speed wind tunnel. The model was tested at a fixed angle of attack of 30 deg and at angles of sideslip up to 20 deg. The tests generated data that were used to study the effect of sideslip on the flow over the delta wing.
- Attack and Fighter Aircraft