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AN EXPERIMENTAL INVESTIGATION OF THE TRANSONIC FLOW OVER AN UNSWEPT WING OF ASPECT RATIO 3.5, TAPER RATIO 0.5, WITH A 4 PERCENT BICONVEX SECTION.

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BookPublisher: Her Majesty'S Stationery Office, London 1955Description: 31.DDC classification: ARC | R&M 3209

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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	ARC R&M 3209 (Browse shelf)	Not for loan		TR16006

Total holds: 0

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Previous	ARC R&M 3206 DIRECT SOLUTION OF THE FLUTTER PROBLEM	ARC R&M 3207 THE CACULATION OF THE COMPRESSIBLE TURBULENT BOUNDARY LAYER IN AN ARBITRARY PRESSURE GRADIENT- A CORRELATION OF CERTAIN PREVIOUS METHODS.	ARC R&M 3208 SUBSONIC WIND-TUNNEL TESTS ON A CRESCENT-WINGED AIRCRAFT, INCLUDING TESTS OF LEADING-EDGE DROOP DESIGNS AND SEVERAL TAILPLANE HEIGHTS.	ARC R&M 3209 AN EXPERIMENTAL INVESTIGATION OF THE TRANSONIC FLOW OVER AN UNSWEPT WING OF ASPECT RATIO 3.5, TAPER RATIO 0.5, WITH A 4 PERCENT BICONVEX SECTION.	ARC R&M 3210 ELEVATOR FLUTTER INVOLVING TWO TABS	ARC R&M 3211 AN EXPERIMENTAL INVESTIGATION AT SUPERSONIC SPEEDS OF THE CHARACTERISTICS OF TWO GOTHIE WINGS, ONE PLANE AND ONE CAMBERED.	ARC R&M 3212 A SUPERSONIC TUNNEL DESIGN FOR TESTING ENGINE INTAKES.	Next

Bound With Arc R&M 3201-3208,3210-3220.

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