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EFFECTS OF CONE ANGLE, MACH NUMBER, AND NOSE BLUNTING ON TRANSITION AT SUPERSONIC SPEEDS [NASA TN D-634] : National aeronautics and Space Administration

By: Czarnecki, K. R.

Contributor(s): Jackson, Mary W.

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BookSeries: NASA Technical Note ; NASA TN D 631-640. Publisher: Washington, D.C. National aeronautics and Space Administration 1961Description: 31p.Subject(s): Supersonic speeds

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Item type	Current location	Collection	Call number	Vol info	Status	Date due	Barcode	Item holds
Technical Report	PK Kelkar Library, IIT Kanpur	COMPACT STORAGE (BASEMENT)		NASA TN D 631-640	Not for loan		TR012763 [D634]

Total holds: 0

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Previous	Voltage breakdown in a low-temperature cesium-vapor diode [NASA TN D-5852]	A LONGITUDINAL CONTROL FEEL SYSTEM FOR IN-FLIGHT RESEARCH ON RESPONSE FEEL [NASA TN D632]	AN ANALYSIS OF THE FLAPWISE BENDING FREQUENCIES MODE SHAPES OF ROTOR BLADES HAVING TWO FLAPPING HINGES TO REDUCE VIBRATION LEVELS [NASA TN D-633]	EFFECTS OF CONE ANGLE, MACH NUMBER, AND NOSE BLUNTING ON TRANSITION AT SUPERSONIC SPEEDS [NASA TN D-634]	FATIGUE INVESTIGATION OF FULL-SCALE WING PANELS OF 7075 ALUMINUM ALLOY [NASA TN D-635]	A WIND-TUNNEL INVESTIGATION OF A TRANSONIC-TRANSPORT CONFIGURATION UTILIZING DRAG-REDUCING DEVICES AT MACH NUMBERS FROM 0.20 TO 1.03 [NASA TN D-636]	WIND-TUNNEL INVESTIGATION OF THE EFFECTS OF WING BODIES, FENCES, FLAPS AND A FUSELAGE ADDITION ON THE WING BUFFET RESPONSE OF A TRANSONIC TRANSPORT MODEL [NASA TN D-637]	Next

Bound vol. contains with NASA TN D 631-640

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