By Loren E. Bollinger, Martin Goldsmith, Alexis W. Lemmon Jr. (Eds.)
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Extra resources for Liquid Rockets and Propellants
Purchased from American Institute of Aeronautics and Astronautics LIQUID ROCKETS AND PROPELLANTS THE FULL-SCALE DIFFUSER The nominal diametrical scale factor between the model diffuser and the full-scale diffuser is ten. The fullscale diffuser is modelled after configuration 2 with some minor alterations 0 A sketch of the vacuum chamber,, which contains the engine3 and the diffuser is shown in Fig. 27 0 Note that the engine and the diffuser are not mechanically coupled but rather that the diffuser is attached to the vacuum chamber.
E. , with D^ = D e> and these tests indicated that there was a strong tendency for the nozzle flow to separate near the nozzle exit plane, even when the diffuser was started. This effect was sometimes noticed for constantarea-duct type diffusers when Dk/D e = 1. 0 as well as for second-throat type diffusers. The presence of a cavity with Dfo > De eliminated this problem, A limited number of tests were made with configurations 2 and 3 using a reduced cavity diameter, with Dk/D e = 1. 065 rather than the value listed in Fig.
40 Using a vacuum tank plus manifold and piping volume of approximately 4. 25 ft Purchased from American Institute of Aeronautics and Astronautics LIQUID ROCKETS AND PROPELLANTS Table 4. Results obtained with constant-area-duct type diffusers withy ~ 1. 6 16. 0516 1. 110 5. 1 20. 0626 1. 4 19. 0626 1. 0626 (1) Using an approximate one-dimensional flow theory. These parameters are a function of 7, € , and A/A e only. Table 5. Best results obtained with a vacuum-tank start using configuration 2 with y ~ 1.