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A SIMPLE METHOD FOR DETERMINING HEAT TRANSFER, SKIN FRICTION, AND BOUNDARY-LAYER THICKNESS FOR HYPERSONIC LAMINAR BOUNDARY-LAYER FLOWS IN A PRESSURE GRADIENT

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BookPublisher: Nasa, Washington, D.C. 1959DDC classification: NASA | MEMO 5-24-59L

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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 MEMO 5-24-59L (Browse shelf)	Not for loan Untraceable		TR7409

Total holds: 0

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Previous	NASA MEMO 5-20-59A AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF A CANARD CONTROL ON THE LIFT, DRAG, AND PITCHING MOMENT OF AN ASPECT-RATIO-2.O TRIANGULAR WING INCORPORATING A FORM OF CONICAL CAMBER	NASA MEMO 5-20-59L LOW-SUBSONIC MEASUREMENTS OF THE STATIC AND OSCILATORY LATERAL STABILITY DERIVATIVES OF A SWEPTBACK-WING AIRPLANE CONFIGURATION AT ANGLES OF ATTACK FROM-10 D/C TO 90 D/C	NASA MEMO 5-23-59L WATER-LANDING CHARACTERISTICS OF A REENTRY CAPSULE	NASA MEMO 5-24-59L A SIMPLE METHOD FOR DETERMINING HEAT TRANSFER, SKIN FRICTION, AND BOUNDARY-LAYER THICKNESS FOR HYPERSONIC LAMINAR BOUNDARY-LAYER FLOWS IN A PRESSURE GRADIENT	NASA MEMO 5-25-59 - 1958 NASA/USAF SPACE PRIBES (ABLE-1)	NASA MEMO 5-25-59L INVESTIGATION OF THE STABILITY OF VERY FLAT SPIN AND ANALYSIS OF EFFECTS OF APPLYING VARIOUS MOMENTS UTILIZING THE THREE MOMENT EQUATIONS OF MOTION	NASA MEMO 5-26-59L MODIFIED MATRIX METHOD FOR CALCULATING STEADY-STATE SPAN LODING ON FLEXIBLE WINGS IN SUBSONIC FLIGHT	Next

Bound With Nasa Memo 5-12-59l-5-23-59l And 5-24-59l-5-28-59l, Lack No.14-17, 19, 21-22, 27

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