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EXPERIMENTAL INVESTIGATION OF GAS-SIDE PERFORMANCE OF A COMPACT FINNED-TUBE HEAT EXCHANGER

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BookPublisher: Nasa, Washington, D.C. 1959Description: 24.DDC classification: NASA | MEMO 4-30-59E -

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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 4-30-59E - (Browse shelf)	Not for loan		TR7713

Total holds: 0

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Previous	NASA MEMO 4-23-59L ANALYTICAL INVESTIGATION OF A FLIKER-TYPE ROLL CONTROL FOR A MACH NUMBER 6 MISSILE WITH AERODYNAMIC CONTROLS OVER AN ALTITUDE RANGE OF 82,000 TO 282,000 FEET	NASA MEMO 4-2-59L - STABILITY CHARACTERISTICS FROM MACH NUMBER 1.0 TO 3.2 OF A MISSILE OF FINENESS RATIO 11.5 WITH A 10(DEGREE) FLARED-SKIRT AFTERBODY	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	Next

Bound With Nasa Memo 4-6-59e-4-30-59e

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