EVALUATION OF TWO MULTIELEMENT CAPILLARY TUBE INJECTORS.
Final rept. 20 Apr-29 Oct 65 on Phase 2,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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This technical report presents the results of tests conducted on two multielement, capillary-tube injector designs at simulated altitudes. Workhorse test hardware was designed to produce 10 pounds of thrust at 100 psia chamber pressure using nitrogen tetroxide N2O4 and 50 N2H450 UDMH as propellants. Test injectors employed capillary tubing having internal diameters of .010 inches in multielement configurations. A transientsteady-state performance evaluation was conducted, with results indicating generally low performance at test conditions. Author
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