INVESTIGATION OF THE PROCESS OF ENERGY TRANSFER FROM AN INTERMITTENT JET TO SECONDARY FLUID IN AN EJECTOR-TYPE THRUST AUGMENTER
Interim summary rept., 1 Apr 1961-30 June 1962
HILLER AIRCRAFT CORP PALO ALTO CA
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The current phase of the thrust augmentation investigation is reported. Showing a correlation between analysis and test data. Improved experimental techniques were used, including color schlieren streak photography and high speed pressure transducer records. Two analyses have been made, each being a graphical-numerical solutithe non-linear partial differential equations of unsteady one-dimensional gas dynamics. The first is the detailed in the small use of wave diagrams in the physical x-t plane in conjection with the classical numerical method of calculations called Method of Characteristics. The second is the newer Vector-Polar Method which deals with wave and fluid velocity interactions only in the large. The latter is based on a combination of two plots, 1 the x-t physical plane and 2 the vector plot of the natural logarithm of pressure ratios across each major compression fan, shock wave, and rarefraction fan versus the change of particle velocity ratio. The device for converting steady flow to intermittent jets has been used in conjunction with color schlieren and high-speed pressure instrumentation and is shown to be an excellent research tool for creating intermittent jets with a range of velocities and wave forms not possible heretofore. This device also appears to have potential as a high performance thrust augmenter for turbojet lift engines.
- Rocket Engines