 ... 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 - About this book
 | Aeronautics - 1976 - 744 pages
...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... | |
 | United States. National Aeronautics and Space Administration - Inventions - 1973 - 274 pages
...Counsel Mail Code: 456 Langley Station Hampton, VA 23665 USA / Corresponding US Paten (-Application Pending] This invention relates to an airfoil for...section improves overall airfoil lifting efficiency. WEAK SHOCK SUPERSONIC FLOW SUPERSONIC FLOW 36 SONIC LINE WATER PURIFICATION MEMBRANES AND METHOD OF... | |
 | United States. National Aeronautics and Space Administration - Inventions - 1978 - 432 pages
...23665 USA Corresponding to US Patent No. 3,952,971 (Supercritical Wing) Filed 11-9-71 Issued 4-27-78 This invention relates to an airfoil for an aircraft...section improves overall airfoil lifting efficiency. This airfoil is known as the supercritical wing. SONIC LINE WEAK SHOCK SUPERSONIC FLOW SUPERSONIC FLOW... | |
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