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NASA Memorandum [NASA MEMO 4-18-59A]: Predicted static aeroelastic effects on wings with supersonic leading edges and streamwise tips

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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 4-14-59A to 4-27-59A	Not for loan		TR11610

Total holds: 0

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Previous	SOUND MEASUREMENT ON A FULL-SCALE JET-ENGINE INLET-NOISE-SUPPRESSOR COWLING. [NASA TN D-4639]	MAXIMUM DROP DIAMETERS FOR THE ATOMIZATION OF LIQUID JETS INJECTED COCURRENTLY INTO ACCELERATING OR DECELERATING GAS STREAMS [NASA TN D-4640]	NASA Memorandum [NASA MEMO 4-15-59A]: A flight investigation of the low-speed handling qualities of a tailless delta-wing fighter airplane	NASA Memorandum [NASA MEMO 4-18-59A]: Predicted static aeroelastic effects on wings with supersonic leading edges and streamwise tips	NASA Memorandum [NASA MEMO 4-19-59A]: Supersonic and moment-of-area rules combined for rapid zero-lift wave-drag calculations	NASA Memorandum [NASA MEMO 4-20-59A]: Static stability and control of canard configurations at mach numbers from 0.70 to 2.22- lateral-directional characteristics of an unswept wing and canard	NASA Memorandum [NASA MEMO 4-21-59A]: Longitudinal stability and control characteristics at mach numbers from 0.70 to 2.22 of a triangular wing configuration equipped with a canard control, a trailing-edge-flap control or a cambered forebody	Next

Bound together NASA MEMO 4-14-59A to 4-27-59A
Lack No.4-16 to 4-17, 4-22 to 4-25

Bound vol. Acc. No. 102439 contains Acc. No. TR11609 to TR11615

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