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AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF A CANARD CONTROL ON THE LIFT, DRAG, AND PITCHING MOMENT OF AN ASPECT-RATIO-2.O TRIANGULAR WING INCORPORATING A FORM OF CONICAL CAMBER

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BookPublisher: Nasa, Washington, D.C. 1959Description: 29.DDC classification: NASA | MEMO 5-20-59A

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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 5-20-59A (Browse shelf)	Not for loan		TR11442

Total holds: 0

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Previous	NASA MEMO 5-16-59A THE STATIC AND DYNAMIC ROTARY STABILITY DERIVATIVES AT SUBSONIC SPEEDS ON AN AIRPLANE MODEL HAVING WING AND TAIL SURFACES SWEPT BACK 45	NASA MEMO 5-18-59A THE EFFECTS OF STREAMWISE-DEFLECTED WING TIPS ON THE AERODYNAMIC CHARACTERISTICS OF AN ASPECT-RATIO-2 TRIANGULAR WING, BODY, AND TAIL COMBINATION	NASA MEMO 5-18-59L EXPERIMENTAL INVESTIGATION OF FLUTTER OF BUCKLED CURVED PANELS HAVING LONGITUDINAL STRINGERS AT TRANSONIC AND SUPERSONIC SPEEDS	NASA MEMO 5-20-59A AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF A CANARD CONTROL ON THE LIFT, DRAG, AND PITCHING MOMENT OF AN ASPECT-RATIO-2.O TRIANGULAR WING INCORPORATING A FORM OF CONICAL CAMBER	NASA MEMO 5-20-59L LOW-SUBSONIC MEASUREMENTS OF THE STATIC AND OSCILATORY LATERAL STABILITY DERIVATIVES OF A SWEPTBACK-WING AIRPLANE CONFIGURATION AT ANGLES OF ATTACK FROM-10 D/C TO 90 D/C	NASA MEMO 5-23-59L WATER-LANDING CHARACTERISTICS OF A REENTRY CAPSULE	NASA MEMO 5-24-59L A SIMPLE METHOD FOR DETERMINING HEAT TRANSFER, SKIN FRICTION, AND BOUNDARY-LAYER THICKNESS FOR HYPERSONIC LAMINAR BOUNDARY-LAYER FLOWS IN A PRESSURE GRADIENT	Next

Bound With Nasa Memo 5-12-59a-5-18-59a Lack No.13-15,17,19

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