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A NONLINEAR THEORY FOR PREDICTING THE EFFECTS OF UNSTEADY LAMINAR, TURBULENT, OR TRANSITIONAL BOUNDARY LAYERS ON THE ATTENUATION OF SHOCK WAVES IN A SHOCK TUBE WITH EXPERIMENTAL COMPARISON

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Material type: Text

TextPublication details: Nasa, Washington, D.C. 1961Description: 55DDC classification:

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Holdings
Item type	Current library	Collection	Call number	Status	Date due	Barcode	Item holds
Technical Report	PK Kelkar Library, IIT Kanpur	General Stacks	NASA TR R-85 (Browse shelf(Opens below))	Not for loan		TR14358

Total holds: 0

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Previous	NASA TR R-82 TURBULENT SKIN FRICTION AT HIGH MACH NUMBERS AND RENOLDS NUMBERS IN AIR AND HELIUM	NASA TR R-83 A THEORETICAL STUDY OF THE ANGULAR MOTIONS OF SPINNING BODIES IN SPACE	NASA TR R-84 ORDINATES AND THEORETICAL PRESSURE-DISTRIBUTION DATA FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS WITH THICKNESSES FROM 2 TO 21 AND FROM 2 TO 15 PERCENT CHORD, RESPECTIVELY	NASA TR R-85 A NONLINEAR THEORY FOR PREDICTING THE EFFECTS OF UNSTEADY LAMINAR, TURBULENT, OR TRANSITIONAL BOUNDARY LAYERS ON THE ATTENUATION OF SHOCK WAVES IN A SHOCK TUBE WITH EXPERIMENTAL COMPARISON	NASA TR R-86 THE DRAG COEFFICIENT OF PARABOLIC BODIES OF REVOLUTION OPERATING AT ZERO CAVITATION NUMBER AND ZERO ANGLE OF YAW	NASA TR R-87 A STUDY OF THE POSITIONS AND VELOSCITIES OF A SPACE STATION AND A FERRY VEHICLE DURING RENDEZVOUS AND RETURN	NASA TR R-88 THEORETICAL PRESSURE DISTRIBUTIONS ON WINGS OF FINITE SPAN AT ZERO INCIDENCE FOR MACH NUMBERS NEAR 1	Next

Bound With Nasa Tr R-81-84,86-90

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