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EXPLORATORY INVESTIGATION OF THE EFFECTS OF BOUNDARY-LAYER CONTROL ON THE PRESSURE-RECOVERY CHARACTERISTICS OF A CIRCULAR INTERNAL-CONTRACTION INLET WITH TRANSLATING CENTERBODY AT MACH NUMBERS OF 2.0

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BookSeries: NASA Memorandum. 12-31-58A.Publisher: NASA, Washington, D.C. 1959Description: 44p.Subject(s): Aerodynamics

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Item type	Current location	Collection	Call number	Vol info	Status	Date due	Barcode	Item holds
Technical Report	PK Kelkar Library, IIT Kanpur	COMPACT STORAGE (BASEMENT)		NASA MEMO 12-31-58A	Not for loan		TR8795

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Previous	EFFECT OF LEADING-EDGE SWEEP AND SURFACE INCLINATION ON THE HYPERSONIC FLOW FIELD OVER A BLUNT FLAT PLATE	EFFECT OF LOWER SURFACE SPOILERS ON THE TRANSONIC TRIM CHANGE OF A WIND-TUNNEL MODEL OF A FIGHTER AIRPLANE HAVING A MODIFIED DELTA WING	EFFCET OF LARGE WING-TIP MASSES ON OSCILLATORY STABILITY OF WING BENDING COUPLED WITH AIRPLANE PITCH	EXPLORATORY INVESTIGATION OF THE EFFECTS OF BOUNDARY-LAYER CONTROL ON THE PRESSURE-RECOVERY CHARACTERISTICS OF A CIRCULAR INTERNAL-CONTRACTION INLET WITH TRANSLATING CENTERBODY AT MACH NUMBERS OF 2.0	Cavitation and noncovinatinal performance of an 80.6 degree flat platehelical inducer at three rotational speeds [NASA TN D-1439]	on the effct of heat additio in the empirical correlation of void fractions for steam water flow [NASA TN [D-1440]	WIND-TUNNEL INVESTIGATION OF STEADY-STATE AERODYNAMICS OF A COMPOSITE-LIFT VTOL AIRCRAFT MODEL [NASA TN D-5232]	Next

NASA Memorandum :12-1-58A-12-4-58A; 12-24-58A-12-31-58A
Bound Vol. No.102443;Contents: TR8786-95

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