Analytical and experimental evaluation of performance prediction methods applicable to exhaust nozzles
Author:
Affiliation:
1. LOCKHEED-CALIFORNIA CO., BURBANK, CALIF.),@EVERLING, P. C.@GLASGOW, E. R.@LAUGHREY, J. A. (USAF, FLIGHT DYNAMICS LAB., WRIGHT-PATTERSON AFB, OHIO
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1971-719
Reference28 articles.
1. Miller, L. D. "Predicting Compressible Turbulent Boundary Layers with Strong Pressure Gradient," Lockheed Report 20701, 1967.
2. Smith, A.M.O. and Pierce, J. "Exact Solution of the Neumann Problem. Calculation of Non-circulatory Plane and Axially Symmetric Flows About or Within Arbitrary Boundaries," Douglas Report ES-26988, April 1958.
3. Glasgow, E. R. and Fox, R. A. "Development of a Computer Program for Subsonic and Transonic Boattail Drag of,Isolated Nozzle Aftbodes," Lockheed Report 23361, 1970.
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