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THE EFFECTS OF STREAMWISE-DEFLECTED WING TIPS ON THE AERODYNAMIC CHARACTERISTICS OF AN ASPECT-RATIO-2 TRIANGULAR WING, BODY, AND TAIL COMBINATION

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BookPublisher: Nasa, Washington, D.C. 1959Description: 36.DDC classification: NASA | MEMO 5-18-59A

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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 5-18-59A (Browse shelf)	Not for loan		TR11441

Total holds: 0

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Previous	NASA MEMO 5-12-59L BASIC PRESSURE MESUREMENTS AT TRANSONIC SPEEDS ON A THIN 45 DEGREE CELSIUS SWEPTBACK HIGHLY TAPERED WING WITH SYSTEMATIC SPANWISE TWIST VARIATION	NASA MEMO 5-13-59L MEASUREMENTS OF TOTAL HEMISPHERICAL EMISSVTTY OF SEVERAL STABLY OXIDIZED NIKEL-TITANIUM CARBIDE CEMENTED HARD METALS FROM 600 D/F TO 1,600 D/F	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	Next

Bound With Nasa Memo 5-12-59a,5-18-59a-5-20-59a Lack No. 13-15, 17,19

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