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THE SHOCK-WAVE NOISE PROBLEM OF SUPERSONIC AIRCRAFT IN STEADY FLIGHT

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BookPublisher: Nasa, Washington, D.C. 1959Description: 15.DDC classification: NASA | MEMO 3-4-59L

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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	NASA MEMO 3-4-59L (Browse shelf)	Not for loan		TR7389

Total holds: 0

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Previous	NASA MEMO 3-2-59L WIND-TUNNEL INVESTIGATION AT MACH NUMBERS FROM 1.60 TO 4.50 OF THE STATIC-STABILITY CHARACTURISTICS OF TWO NONLIFTING VEHICLES SUITABLE FOR REENTRY	NASA MEMO 3-3-59E PERFORMANCE OF TWO BARON -MODIFIED S-816 ALLOYS IN A TURBOJET OPERATED AT 1650 DEGREE F	NASA MEMO 3-3-59L WIND-TUNNEL INVESTIGATION OF THE EFFECT OF ANGLE OF ATTACK AND FLAPPING-HINGE OFFSET ON PERIODIC BENDING MOMENTS AND FLAPPING OF A SMALL ROTOR	NASA MEMO 3-4-59L THE SHOCK-WAVE NOISE PROBLEM OF SUPERSONIC AIRCRAFT IN STEADY FLIGHT	NASA MEMO 3-5-59L NOISE PROBLEMS ASSOCIATED WITH GROUND OPERATIONS OF JET AIRCRAFT	NASA MEMO 3-6-59L A FIVE-STAGE SOLID-FUEL SOUNDING-ROCKET SYSTEM	NASA MEMO 3-7-59L INFLUANCE OF LARGE POSITIVE DIHEDRAL ON HEAT TRANSFER TO LEADING EDGES OF HIGHLY SWEPT WINGS AT VERY HIGH MACH NUMBERS	Next

Bound With Tr007387-88, Tr007390-98

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