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POSTBUCKLING EFFECTS ON THE FLUTTER OF SIMPLY SUPPORTED RECTANGULAR PANELS AT SUPERSONIC SPEEDS

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BookPublisher: Nasa, Washington, D.C. 1963Description: 30.DDC classification: NASA | TN D-1615

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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-1615 (Browse shelf)	Not for loan		TR12729

Total holds: 0

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Previous	NASA TN D-1612 PRESSURE DISTRIBUTIONS OVER THE FORWARD PORTION OF THE PROJECT FIRE SPACE-VEHICLE CONFIGURATION AT MACH NUMBER FROM 0.25 TO 0.60	NASA TN D-1613 POLOT-CONTROLLED SIMULATION OF RENDEZVOUS BETWEEN A SPACE CRAFT AND A COMMANDED MODULE HAVING LOW THRUST	NASA TN D-1614 EXPERIMENTAL INVESTIGATION OF THE DYNAMIC STABILITY STABILITY OF A TOWED PARAWING GLIDER MODEL	NASA TN D-1615 POSTBUCKLING EFFECTS ON THE FLUTTER OF SIMPLY SUPPORTED RECTANGULAR PANELS AT SUPERSONIC SPEEDS	NASA TN D-1616 MEASURED AND CALCULATED SUBSONIC AND TRANSONIC FLUTTER CHARACTERISTICS OF A 45 DEGREE SWEPTBACK WING PLANFORM IN AIR AND IN FREON-12 IN THE LANGLEY TRANSONIC DYNAMICS TUNNEL	NASA TN D-1617 A STUDY OF THE EFFECTS OF BANK ANGLE, BANKING DURATION, AND TRAJECTORY POSITION OF INITIAL BANKING ON THE LATERAL AND LONGITUDINAL RANGES OF A HYPERSONIC GLOBAL REENTRY VEHICLE	NASA TN D-1618 PRESSURE DISTRIBUTIONS ON THREE RIGID WINGS SIMULATING PARAWINGS WITH VARIED CANOPY CURVATURE AND LEADING-EDGE SWEEP AT MACH NUMBERS FROM 2.29 TO 4.65	Next

Bound With Nasa Tn D-1611-14, 1616-20

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