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EFFECT OF LOWER SURFACE SPOILERS ON THE TRANSONIC TRIM CHANGE OF A WIND-TUNNEL MODEL OF A FIGHTER AIRPLANE HAVING A MODIFIED DELTA WING

By: Robinson, Robert C.

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BookSeries: NASA Memorandum. MEMO 12-27-58A.Publisher: Nasa, Washington, D.C. 1959Description: 50p.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 12-27-58A	Not for loan		TR8793

Total holds: 0

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Previous	NASA Technical Note [NASA TN D-2859]: Low-speed wind tunnel tests of a large-scale inflatable structure paraglider	NASA Technical Note [NASA TN D-2860]: Extension of an analysis of peripheral wall conduction effects for laminar forced convection in thin-walled rectangular channels	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]	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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