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EFFECT OF FINITE SPAN ON THE AIRLOAD DISTRIBUTIONS FOR OSCILLATING WINGS 1-AERODYNAMIC THEORY OF OSCILLATING WINGS OF FINITE SPAN.

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BookPublisher: Nasa, Washington, D.C. 1947Description: 38.DDC classification: NACA | TN D-1194

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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 D-1194 (Browse shelf)	Not for loan		TR15720

Total holds: 0

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Previous	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.	NACA TN-3094 THE RESISTANCE TO AIR FLOW OF POROUS MATERIALS SUITABLE FOR BOUNDARY-LAYER-CONTROL APPLICATIONS USING AREA SUCTION.	Next

Bound With Naca Tn-1190-1193,1195-1199.Lack Nos-1196,1197,1199

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