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DESIGN OF INJECTORS AND ABLATIVE THRUST CHAMBERS FOR A FLOX-PROPANE ROCKET ENGINE WITH A 1.2-INCH THROAT DIAMETER

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BookPublisher: Nasa, Washington, D.C. 1969Description: 34.DDC classification: NASA | TN D-5324 -

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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 TN D-5324 - (Browse shelf)	Not for loan		TR9242

Total holds: 0

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Previous	NASA TN D-5320 - FABRICATION PROCESS FOR GLASS COATED ELECTRON-BOMBARDMENT ION THRUSTER GRIDS	NASA TN D-5322 - STUDY OF HELIUM PENETRATION AND SPREDING IN A MACH 2 AIRSTREAM USING A DELTA WING INJECTOR	NASA TN D-5323 - TESTS OF SODIUM BOILING IN A SINGLE TUBE-IN-SHELL HEAT EXCHANGER OVER THE RANGE 1720(DEGREE) TO 1980(DEGREE) F (1211 TO 1355 K)	NASA TN D-5324 - DESIGN OF INJECTORS AND ABLATIVE THRUST CHAMBERS FOR A FLOX-PROPANE ROCKET ENGINE WITH A 1.2-INCH THROAT DIAMETER	NASA TN D-5325 - MINITURE TWO-AXIS FLUXGATE MAGNETOMETER	NASA TN D-5326 - CORROSION IN A COBALT ALLOY, TWO-PHASE MERCURY LOOP	NASA TN D-5327 - PERFORMANCE OF TWO MODELS OF COMMERCIAL UNBONDED STRAIN-GAGE-TYPE ABSOLUTE PRESSURE TRANSDUCER AT 260(DEGREE) C	Next

Bound With Nasa Tn D-5321-30

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