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AERODYNAMIC CHARACTERISTICS OF A BODY IN THE FLOW FIELD NEAR THE TIP OF A CIRCULAR-ARC WING OF RECTANGULAR -PLAN FROM AT A MACH NUMBER OF 2.01

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BookPublisher: Nasa, Washington, D.C. 1960Description: 39.DDC classification: NASA | TM X-211 -

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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 TM X-211 - (Browse shelf)	Not for loan		TR8819

Total holds: 0

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Previous	NASA TM X-197 EXPERIMENTAL INVESTIGATION OF A TRANSONIC COMPRESSOR CASCADE AND TEST RESULTS FOR FOUR BLADE SECTIONS	NASA TM X-208 - HEAT TRANSFER TO 36.75(DEGREE) AND 45(DEGREE) SWEPT BLUNT LEADING EDGES IN FREE FLIGHT AT MACH NUMBERS FROM 1.70 TO 2.99 AND FROM 2.50 TO 4.05	NASA TM X-210 - INVESTIGATION OF THE SUBSONIC STABILITY AND CONTROL CHARACTERISTICS OF A 1/7-SCALE MODEL OF THE NORTH AMERICAN X-15 AIRPLANE WITH AND WITHOUT FUSELAGE FOREBODY STRAKES	NASA TM X-211 - AERODYNAMIC CHARACTERISTICS OF A BODY IN THE FLOW FIELD NEAR THE TIP OF A CIRCULAR-ARC WING OF RECTANGULAR -PLAN FROM AT A MACH NUMBER OF 2.01	NASA TM X-215 - EFFECT OF AFTERBODY TERMINAL FAIRINGS ON THE PERFORMANCE OF A PYLON-MOUNTED TURBOJET-NACELLE MODEL	NASA TM X-218 - INTERFERENCE EFFECTSAT TRANSONIC SPEEDS OF JETS EXHAUSTING FROM THE HULL STEP OF A MODEL OF A LARGE, WATER-BASED AIRPLANE	NASA TM X-222 - STATIC LONGITUDINAL STABILITY CHARACTERISTICS OF A BLUNTED GLIDER REENTRY CONFIGURATION HAVING 79.5(DEGREE) SWEEPBACK & 45(DEGREE) DIHEDRAL AT A MACH NUMBER OF 6.2 & ANGLES OF ATTACK UP TO 20(DEGREE)	Next

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