AN INVESTIGATION OF THE OXIDIZER FLOW PASSAGES IN A DUAL-COMBUSTION LIQUID ROCKET ENGINE.
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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This work was undertaken to determine the pressure drops in the oxidizer flow passages of a compact dual-combustion liquid rocket engine by means of fluid dynamic model tests, using air instead of liquids, to establish design data. Investigated also were flow distributions and flow instabilities by measurements and flow visualization methods. Changes are indicated to improve the original design. The air tests were carried out over a range of Reynolds numbers to establish the effect of compressibility on the pressure drop loss coefficients. Water tests were undertaken to check the validity of the results and of the proposed calculating method. Author
- Fluid Mechanics
- Liquid Propellant Rocket Engines