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CALCULATION OF DERIVATIVES FOR A CROPPED DELTA WING WITH AN OSCILLATING CONSTANT-CHORD FLAP IN A SUPERSONIC AIR STREAM

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BookPublisher: Her Majesty'S Stationery Office, London 1958Description: 34.DDC classification: HMSO-R&M-3059 | -

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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	HMSO-R&M-3059 - (Browse shelf)	Not for loan		TR8902

Total holds: 0

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Previous	HMSO-R&M-3056 - USE OF PILOT - TUBES IN THE MEASURMENT OF LAMINAR BOUNDARY LAYERS IN SUPERSONIC FLOW	HMSO-R&M-3057 - ON THE INTEGRAL EQUATIONS OF TWO-DIMENSIONAL SUBSONIC FLUTTER DERIVATIVE THEORY	HMSO-R&M-3058 - ACCURACY OF MEASURMENT OF TURBULENT SKIN FRICTION BY MEANS OF SURFACE PITOT-TUBES AND THE DISTRIBUTION OF SKIN FRICTION ON A FLAT PLATE	HMSO-R&M-3059 - CALCULATION OF DERIVATIVES FOR A CROPPED DELTA WING WITH AN OSCILLATING CONSTANT-CHORD FLAP IN A SUPERSONIC AIR STREAM	HMSO-R&M-3060 - CALCULATION OF DERIVATIVES FOR A CROPPED DELTA WING WITH SUBSONIC LEADING EDGES OSCILLATING IN A SUPERSONIC AIR STREAM	HMSO-R&M-3061 - NOTE ON THE CONVERGENCE OF NUMERICAL SOULITIONS OF THE NAVIER-STROKES EQUATIONS	HMSO-R&M-3062 - EXPERIMENTAL INVESTIGATION OF THE EFFECT OF ENGINE LOADS ON WING STRUCTURES	Next

Bound With Hmso-R&M-3050-69

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