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AN ANALYSIS OF THE DELTA-WING HYPERSONIC STABILITY AND CONTROL BEHAVIOR AT ANGLES OF ATTACK BETWEEN 30DEGREE AND 90DEGREE.

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BookPublisher: Nasa, Washington, D.C. 1963Description: 58.DDC classification: NASA | TN D-1602

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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-1602 (Browse shelf)	Not for loan		TR11974

Total holds: 0

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Previous	NASA TN D-1598 - DESIGN,OPERATION,AND TESTING CAPABILITIES OF THE LANGLEY 11-INCH CERAMIC-HEATED TUNNEL	NASA TN D-1599 - A METHOD FOR COMPUTING THE EFFECT OF AN ADDITIONAL OBSERVATION ON A PREVIOUS LEAST-SQUARES ESTIMATE	NASA TN D-1600 - EXPERIMENTAL PANEL FLUTTER RESULT FOR SOME FLAT AND CURVED TITANIUM SKIN PANEL AT SUPERSONIC SPEEDS	NASA TN D-1602 AN ANALYSIS OF THE DELTA-WING HYPERSONIC STABILITY AND CONTROL BEHAVIOR AT ANGLES OF ATTACK BETWEEN 30DEGREE AND 90DEGREE.	NASA TN D-1603 EXPERIMENTAL INVESTIGATION OF BLAST LOADING ON AN AIRFOIL IN MACH NUMBER 0.7 AIRFLOW WITH INITIAL ANGLE-OF-ATTACK CHANGE OF20 DEGREE.	NASA TN D-1604 EQUQATIONS FOR DETERMINING VEHICILE POSITION IN EARTH-MOON SPACE FROM SIMULATNEOUS ONBOARD OPTICAL MEASUREMENTS.	NASA TN D-1605 EXPLORATORY INVESTIGATION OF THE EFFECT OF A FORWARD-FACING JET ON THE BOW SHOCK OF A BLUENT BODY IN A MACH NUMBER 6 FREE STREAM.	Next

Bond With Nasa Tn D -1601,1603-10.

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