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EFFECTS OF SHOCK-WAVE IMPINGEMENT ON THE HEAT TRANFER ON A CYLINDRICAL LEADING EDGE.

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BookPublisher: Nasa, Washington, D.C. 1967Description: 48.DDC classification: NASA | TN D-3859

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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 TN D-3859 (Browse shelf)	Not for loan		TR15816

Total holds: 0

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Previous	NASA TN D-3856 WIIND-TUNNEL INVESTIGATION OF THE STATIC AERODYNAMIC CHRACTERISTICS OF AN 18-FOOT(5.49-METER) ALL-FLEXIBLE PARAWING.	NASA TN D-3857 A NEW LIE SERIES METHOD FOR THE NUMERICAL INTEGERATION OF ORDINARY AN APPLICATION TO THE RESTICTED OROBLE OF THREE BODIES.	NASA TN D-3858 EXPERIMENTAL INVESTIGATION OF THE TURBULENT BOUNDARY LAYER AT A MACH NUMBER OF 6 WITH HEAT TRANSFER AT HIGH REYNOLDS NUMBERS.	NASA TN D-3859 EFFECTS OF SHOCK-WAVE IMPINGEMENT ON THE HEAT TRANFER ON A CYLINDRICAL LEADING EDGE.	NASA TN D-3860 CONENTRATION MEASUREMENTS OF AN INJECTED GAS IN A SUPERSONIC STREAM	NASA TN D-3864 - POSSIBLE RELATION OF FRICTION OF COPPER-ALUMINUM ALLOYS WITH DECREASING STACKING-FAULT ENERGY	NASA TN D-3867 STATIC CALIBRATION OF AN EJECTOR UNIT FOR SIMULATION OF JET ENGINES IN SMALL-SCALE WIND-TUNNEL MODELS	Next

Bound With Nasa Tn D-3851-3858.3860.

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