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AN EXPERIMENTAL STUDY OF THE GLANCING INTERACTION BETWEEN A SHOCK WAVE AND A TURBULENT BOUNDARY LAYER.

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BookPublisher: Her Majesty'S Stationery Office, London 1961Description: 8.DDC classification: ARC | C.P. 555

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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 C.P. 555 (Browse shelf)	Not for loan		TR11021

Total holds: 0

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Previous	ARC C.P. 552 ON THE REPRESENTATION OF FAN-WING CHARACTERISTICS IN A FORM SUITABLE FOR THE ANALYSIS OF TRANSITION MOTIONS, WITH RESULTS OF TESTS OF AN ASPECT-RATIO-1 WING WITH FAN AT 0.354 CHORD.	ARC C.P. 553 FREE-FLIGHT MEASUREMENTS OF THE ZERO-LIFT DRAG AND BASE PRESSURE ON A WIND TUNNEL INTERFERENCE MODEL (M=0.8 - 1.5)	ARC C.P. 554 BOUNDARY LAYER MEASUREMENTS AT LOW SPEED ON TWO WINGS OF 45 DEGREE AND 55 DEGREE SWEEP.	ARC C.P. 555 AN EXPERIMENTAL STUDY OF THE GLANCING INTERACTION BETWEEN A SHOCK WAVE AND A TURBULENT BOUNDARY LAYER.	ARC C.P. 556 SOME CALCULATIONS BY THE CROCCO-LEES AND OTHER METHODS OF INTERACTIONS BETWEEN SHOCK WAVES AND LAMINAR BOUNDARY LAYERS, INCLUDING EFFECTS OF HEAT TRANSFER AND SUCTION.	ARC C.P. 557 DESIGN AND OPERATION OF THE N.G.T.E. THERMAL SHOCK ANALOGUE.	ARC C.P. 558 A NOTE ON THE USE OF STEADY EXPANSIONS IN SHOCK TUBES AND SHOCK TUNNELS.	Next

Bound With Arc C.P. 551-54, 556-60

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