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WIND-TUNNEL INVESTIGATION OF A NUMBER OF TOTAL-PRESSURE TUBES AT HIGH ANGLES OF ATTACK

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BookPublisher: Nasa, Washington, D.C. Description: 48.DDC classification: NACA | TN 2261

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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	NACA TN 2261 (Browse shelf)	Not for loan		TR15639

Total holds: 0

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Previous	NACA TN 2146 ON THE EFFECT OF SUBSONIC TRAILING EDGES ON DAMPING IN ROLL AND PITCH OF THIN SWEPTBACK WINGS IN A SUPERSONIC STREAM	NACA TN 2147 SOME CONICAL AND QUASI-CONICAL FLOWS IN LINEARIZED SUPERSONIC-WING THEORY	NACA TN 2149 INVESTIGATION OF BOUNDARY-LAYER CONTROL TO IMPROVE THE LIFT AND DRAG CHARACTERISTICS OF THE NACA 652-415 AIRFOIL SECTION WITH DOUBLE SLOTTED AND PLAIN FLAPS	NACA TN 2261 WIND-TUNNEL INVESTIGATION OF A NUMBER OF TOTAL-PRESSURE TUBES AT HIGH ANGLES OF ATTACK	NACA TN 2262 ROLLING AND YAWING MOMENTS FOR SWEPT-BACK WINGS IN SIDESLIP AT SUPERSONIC SPEEDS	NACA TN 2263 THE USE OF A LUMINESCENT LACQUER FOR THE VISUAL INDICATION OF BOUNDARY-LAYER TRANSITION	NACA TN 2264 AIRFOIL PROFILES FOR MINIMUM PRESSURE DRAG AT SUPERSONIC VELOCITIES - GENERAL ANALYSIS WITH APPLICATION TO LINEARIZED SUPERSONIC FLOW	Next

Bound With Naca Tn 2260,2262-70

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