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AN APPROXIMATE SOLUTION FOR AXIALLY SYMMETRIC FLOW OVER A CONE WITH AN ATTACHED SHOCK WAVE

Material type: materialTypeLabel

BookPublisher: Naca, Washington 1955Description: 32.DDC classification: NACA | TN 3485

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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	NACA TN 3485 (Browse shelf)	Not for loan		TR13309

Total holds: 0

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Previous	NACA TN 3482 SUPPLEMENTARY CHARTS FOR ESTIMATING PERFORMANCE OF HIGH-PERFORMANCE HELICOPTERS	NACA TN 3483 AN ANALYSIS OF ACCELERATION, AIRSPEED, AND GUST-VELOCITY DATA FROM A FOUR-ENGINE TRANSPORT AIRPLANE IN OPERATIONS ON AN EASTERN UNITED STATES ROUTE	NACA TN 3484 ON SPECTRAL ANALYSIS OF RUNWAY ROUGHNESS AND LOADS DEVELOPED DURING TAXIING	NACA TN 3485 AN APPROXIMATE SOLUTION FOR AXIALLY SYMMETRIC FLOW OVER A CONE WITH AN ATTACHED SHOCK WAVE	NACA TN 3486 MEASUREMENTS OF TURBULENT SKIN FRICTION ON A FLAT PLATE AT TRANSONIC SPEEDS	NACA TN 3487 ACOUSTIC RADIATION FROM TWO-DIMENSIONAL RECTANGULAR CUTOUTS IN AERODYNAMIC SURFACES	NACA TN 3488 SOME MEASUREMENTS OF FLOW IN A RECTANGULAR CUTOUT	Next

Bound With Naca Tn 3480-84,3486-89

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