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ESTIMATION OF STATIC LONGITUDINAL STABILITY OF AIRCRAFT CONFIGURATIONS AT HIGH MACH NUMBERS AND AT ANGLES OF ATTACK BETWEEN 0(DEGREE) AND +-180(DEGREE)

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BookPublisher: Nasa, Washington, D.C. 1962Description: 72.DDC classification: NASA | MEMO 1-17-59A -

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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 MEMO 1-17-59A - (Browse shelf)	Not for loan		TR7771

Total holds: 0

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Previous	NASA MEMO 11-5-58L - ANALYTICAL AND EXPERIMENTAL DETERMINATION OF THE COUPLED NATURAL FREQUENCIES AND MODE SHAPES OF A DYNAMIC MODEL OF A SINGLE-ROTOR HELICOPTER	NASA MEMO 1-16-59A - NUMERICAL METHOD FOR CALCULATING THE WAVE DRAG OF A CONFIGURATION FROM THE SECOND DERIVATIVE OF THE AREA DISTRIBUTION OF A SERIES OF EQUIVALENT BODIES OF REVOLUTION	NASA MEMO 1-16-59L SEMIEMPIRICAL PROCEDURE FOR ESTIMATING LIFT AND DRAG CHARACTERISTICS OF PROPELLER-WING-FLAP CONFIGURATIONS FOR VERTICAL-AND SHORT-TAKE-OFF-AND-LANDING AIRPLANES	NASA MEMO 1-17-59A - ESTIMATION OF STATIC LONGITUDINAL STABILITY OF AIRCRAFT CONFIGURATIONS AT HIGH MACH NUMBERS AND AT ANGLES OF ATTACK BETWEEN 0(DEGREE) AND +-180(DEGREE)	NASA MEMO 1-18-59A - SUBSONIC WING LOADINGS ON A 45(DEGREE) SWEPTBACK-WING AND BODY COMBINATION AT HIGH ANGLES OF ATTACK	NASA MEMO 1-19-59A - FINISHING AND INSPECTION OF MODEL SURFACES BOUNDARY-LAYER-TRANSITION TESTS	NASA MEMO 1-20-59A - BOUNDARY-LAYER TRANSITION ON HOLLOW CYLINDERS IN SUPERSONIC FREE FLIGHT AS AFFECTED BY MACH NUMBER AND A SCREWTHREAD TYPE OF SURFACE ROUGHNESS	Next

Bound With Nasa Memo 1-8-59a-1-29-59a

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