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WIND TUNNEL TESTS AT MACH NUMBERS BETWEEN 0.6 AND 1.4 OF A 60 DEGREE SWEPT WING HAVING AN AEROFOIL SECTION DESIGNED FOR SUBCRITICAL FLOW AT A MACH NUMBER OF 1.2

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BookPublisher: Her Majesty'S Stationery Office, London 1962DDC classification: C.P. | 582

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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	C.P. 582 (Browse shelf)	Not for loan		TR10471

Total holds: 0

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Previous	C.P. 1138 FLIGHT TESTS TO INVESTIGATE THE PROBLEMS OF STEEP APPROACHES BY STOL AIRCRAFT.	C.P. 1139 EXPERMENTAL VERIFICATION OF PREDICTED STATIC HOLE SIZE EFFECTS ON A MODEL WITH LARGE STREAMWISE PRESSURE GRADIENTS.	C.P. 1140 WIND TUNNEL TESTED AT TRANSONIC AND SUPERSONIC SPEEDS TO INVESTIGATE THE LONGITUDINAL STABILITY OF A MODEL OF THE AVRO 720 AIRCRAFT.	C.P. 582 WIND TUNNEL TESTS AT MACH NUMBERS BETWEEN 0.6 AND 1.4 OF A 60 DEGREE SWEPT WING HAVING AN AEROFOIL SECTION DESIGNED FOR SUBCRITICAL FLOW AT A MACH NUMBER OF 1.2	C.P. 583 SURFACE OIL-FLOW PATTERNS ON WINGS OF DIFFERENT LEADING-EDGE RADIUS AND SWEEPBACK	C.P. 584 A SURVEY OF BUFFETING LOADS.	C.P. 585 AN EXPERIMENTAL INVESTIGATION OF THE CHARACTERISTICS OF AN OGEE WING FROM M=0.4 TO M=1.8	Next

Bound With C.P.581, 583-590

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