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EXPERMENTAL VERIFICATION OF PREDICTED STATIC HOLE SIZE EFFECTS ON A MODEL WITH LARGE STREAMWISE PRESSURE GRADIENTS.

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BookPublisher: Her Majesty'S Stationery Office, London 1971Description: 12.DDC classification: C.P. | 1139

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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. 1139 (Browse shelf)	Not for loan Untraceable		TR10586

Total holds: 0

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Previous	C.P. 1136 AIRFLOW RATE REQUIREMENTS IN PASSENGER AIRCRAFT.	C.P. 1137 SUBSONIC THEORETICAL LIFT-CURVE SLOPE, AERODYNAMIC CENTRE AND SPANWISE LOADING FOR ARBITRARY ASPECT RATIO, TAPER RATIO AND SWEEPBACK.	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	Next

Bound With C.P.1131-1138 & 1140

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