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FLOW FIELD ANALYSIS OF AIRCRAFT CONFIGURATION USING A NUMERICAL SOLUTION TO THE THREE-DIMENSIONAL UNIFIED SUPERSONIC/HYPERSONIC SMALL-DISTURBENCE EQUATIONS

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BookPublisher: Nasa, Washington, D.C. 1972Description: 114.DDC classification: NASA | CR-1926

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Item type	Current location	Collection	Call number	Status	Date due	Barcode	Item holds
Technical Report	PK Kelkar Library, IIT Kanpur	General Stacks	NASA CR-1926 (Browse shelf)	Not for loan		TR8346

Total holds: 0

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Previous	NASA CR-1922 - INVESTIGATION OF HIGH-POWER PROBLEMS IN SPACE SHUTTLE ANTENNA DESIGNS	NASA CR-1924 CALCULATION OF TURBULENT BOUNDARY LAYERS WITH HEAT TRANSFER AND PRESSURE GRADIENT UTILIZING A COMPRESSIBILITY TRANSFORMATION	NASA CR-1925 CALCULATION OF TURBULENT BOUNDARY LAYERS WITH HEAT TRANSFER AND PRESSURE GRADIENT UTILIZING A COMPRESSIBILITY TRANSFORMATION	NASA CR-1926 FLOW FIELD ANALYSIS OF AIRCRAFT CONFIGURATION USING A NUMERICAL SOLUTION TO THE THREE-DIMENSIONAL UNIFIED SUPERSONIC/HYPERSONIC SMALL-DISTURBENCE EQUATIONS	NASA CR-1927 FLOW FIELD ANALYSIS OF AIRCRAFT CONFIGURATION USING A NUMERICAL SOLUTION TO THE THREE-DIMENSIONAL UNIFIED SUPERSONIC/HYPERSONIC SMALL-DISTURBENCE EQUATIONS	NASA CR-1928 - PRELIMINARY DESIGN OF AN AUXILIARY POWER UNIT FOR THE SPACE SHUTTLE-COMPONENT AND SYSTEM CONFIGURATION SCREENING ANALYSIS	NASA CR-1933 MOTION EFFECTS ON AN IFR HOVERING TASK--ANALYTICAL PREDICTIONS AND EXPERIMENTAL RESULTS.	Next

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