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FORMULAS PERTINENT TO THE CALCULATION OF FLOW-FIELD EFFECTS AT SUPERSONIC SPEEDS DUE TO WING THICKNESS

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BookPublisher: Nasa, Washington, D.C. 1959Description: 26.DDC classification: NASA | MEMO 4-3-59L -

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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 4-3-59L - (Browse shelf)	Not for loan Untraceable		TR7688

Total holds: 0

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Previous	NASA MEMO 4-27-59E - HEAT TRANSFER FROM CYLINDERS IN TRANSITION FROM SLIP FLOW TO FREE-MOLECULE FLOW	NASA MEMO 4-30-59E - EXPERIMENTAL INVESTIGATION OF GAS-SIDE PERFORMANCE OF A COMPACT FINNED-TUBE HEAT EXCHANGER	NASA MEMO 4-30-59L TRANSONIC AERODYNAMIC CHARACTERISTICS OF TWO WEDGE AIRFOIL SECTIONS INCLUDING UNSTEADY FLOW STUDIES	NASA MEMO 4-3-59L - FORMULAS PERTINENT TO THE CALCULATION OF FLOW-FIELD EFFECTS AT SUPERSONIC SPEEDS DUE TO WING THICKNESS	NASA MEMO 4-4-59L - EFFECTS OF FOREBODY DEFLECTION ON STABILITY AND CONTROL CHARACTERISTICS OF A CANARD AIRPLANE CONFIGURATION WITH A HIGH TRAPEZOIDAL WING AT A MACH NUMBER OF 2.01	NASA MEMO 4-9-59E - EXPLORATORY INVESTIGATION OF AERODYNAMIC FLAMEHOLDERS FOR AFTERBURNER APPLICATION	NASA MEMO 4-9-59L - SOME BASIC ASPECTS OF MAGNETOHYDRODYNAMIC BOUNDARY-LAYER FLOWS	Next

Bound With Nasa Memo 4-1-59l-4-19-59l

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