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SOME FINITE DIFFERENCE SOLUTIONS OF THE LAMINAR COMPRESSIBLE BOUNDARY LAYER SHOWING THE EFFECTS OF UPSTREAM TRANSPIRATION COOLING

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BookPublisher: Nasa, Washington, D.C. 1959Description: 33.DDC classification: NASA | MEMO 2-26-59A -

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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 2-26-59A - (Browse shelf)	Not for loan		TR7526

Total holds: 0

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Previous	NASA MEMO 2-25-59A - NUMERICAL SOLUTION OF THE FLOW OF A PERFACT GAS OVER A CIRCULAR CYLINDER AT INFINITE MACH NUMBER	NASA MEMO 2-25-59E HALOGEN-CONTAINING GASES AS BOUNDARY LUBRICANTS FOR CORROSION-RESISTANT ALLOYS AT 1200 DEGREE F	NASA MEMO 2-25-59L - SEVERAL METHODS FOR REDUCING THE DRAG OF TRANSPORT CONFIGURATIONS AT HIGH SUBSONIC SPEEDS	NASA MEMO 2-26-59A - SOME FINITE DIFFERENCE SOLUTIONS OF THE LAMINAR COMPRESSIBLE BOUNDARY LAYER SHOWING THE EFFECTS OF UPSTREAM TRANSPIRATION COOLING	NASA MEMO 2-27-59A - LOW-SPEED TESTS OF SEMISPAN-WING MODELS AT ANGLES OF ATTACK FROM 0(DEGREE) TO 180(DEGREE)	NASA MEMO 2-27-59E DETAILS OF EXACT LOW PRANDTL NUMBER BOUNDARY-LAYER SOLUTIONS FOR FORCED AND FOR FREE CONVECTION	NASA MEMO 2-28-59L - COMPARISON OF MEASURED FLAPWISE STRUCTURAL BENDING MOMENTS ON A TEETERING ROTOR BLADE WITH RESULTS CALCULATING FROM THE MEASURED PRESSURE DISTRIBUTION	Next

Bound With Nasa Memo 2-3-59a-2-27-59a

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