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THE RESULTS OF WIND-TUNNEL TESTS TO A MACH NUMBER OF 0.90 OF A FOUR-ENGINE PROPELLER-DRIVEN AIRPLANE CONFIGURATION HAVING A WING WITH 40 DEGREE OF SWEEPBACK AND AN ASPECT RATIO OF 10

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BookPublisher: Naca, Washington 1956Description: 171.DDC classification: NACA | TN 3789

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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	NACA TN 3789 (Browse shelf)	Not for loan		TR11267

Total holds: 0

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Previous	NACA TN 3786 HANDBOOK OF STRUCTURAL STABILITY	NACA TN 3787 HEAT-CAPACITY MEASUREMENTS OF TITANIUM AND OF A HYDRIDE OF TITANIUM FOR TEMPERATURES FROM 4 DEGREE TO 15 DEGREE K INCLUDING A DETAILED DESCRIPTION OF A SPECIAL ADIABATIC SPECIFIC-HEAT CALORIMETER	NACA TN 3788 STABILITY DERIVATIVES OF CONES AT SUPERSONIC SPEEDS	NACA TN 3789 THE RESULTS OF WIND-TUNNEL TESTS TO A MACH NUMBER OF 0.90 OF A FOUR-ENGINE PROPELLER-DRIVEN AIRPLANE CONFIGURATION HAVING A WING WITH 40 DEGREE OF SWEEPBACK AND AN ASPECT RATIO OF 10	NACA TN D-1194 EFFECT OF FINITE SPAN ON THE AIRLOAD DISTRIBUTIONS FOR OSCILLATING WINGS 1-AERODYNAMIC THEORY OF OSCILLATING WINGS OF FINITE SPAN.	NACA TN-3092 HYDRODYNAMIC DRAG OF 12-AND 21- PERCENT-THICK SUFACE-PIERING STRUTS.	NACA TN-3093 EFFECT OF TYPE OF POROUS SURFACE AND SUCTION VELOCITY DISTRIBUTION ON THE CHARACTERISTICS OF.A 10.5-PERCENT-THICK AIRFOIL WITH AREA SUCTION.	Next

Bound With Naca Tn 3780-88.

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