... separation of the boundary layer due to shock wave formulation at high subsonic speeds well above the critical Mach number. A highly cambered trailing edge section improves overall airfoil lifting efficiency. Significant NASA Inventions - Page 40by United States. National Aeronautics and Space Administration - 1975Full view
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Aeronautics - 1976
...US-Patent-Class-244-35R. US-Patent-Class-244-40R) Avail. US Patent Office CSCL OÍA An airfoil is examined that has an upper surface shaped to control flow accelerations...and pressure distribution over the upper surface and to prevent separation of the boundary layer due to shock wave formulation at high subsonic speeds well...