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- W1497001098 abstract "Abstract : To determine general effects of fluid injection into a turbulent boundary layer on missile drag and stabilizing forces at angle of attack, an exploratory investigation was made at Mach 1.63 and 2.2. The test model was a body of revolution 10-cal long with a 3-cal tangent ogive nose and stabilizing fins. The mass injection was simulated by nitrogen and injected into the boundary layer from a porous section just aft of the nose body junction. The porous section was varied in length from 0.5 to 1.5 cal. Angle of attack range varied from -3.5 deg to +19 deg." @default.
- W1497001098 created "2016-06-24" @default.
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- W1497001098 date "1976-11-01" @default.
- W1497001098 modified "2023-09-24" @default.
- W1497001098 title "An Exploratory Investigation on Reducing Supersonic Missile Drag by Fluid Injection into a Turbulent Boundary Layer" @default.
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