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- W2122585223 abstract "The present work documents the experimental database of a combined computational and experimental parametric study of the internal aerodynamics of a generic three-dimensional sidewall compression scramjet inlet configuration at Mach 10. A total of 256 channels of pressure data, including static pressure orifices, pitot pressures, and exit flow rakes, along with oil flow and infrared thermography, provided a detailed experimental description of the flow. Mach 10 tests were performed for three geometric contraction ratios (3, 5, and 9), three Reynolds numbers (0.55 x 10super6 per foot, 1.14 x 10super6 per foot, and 2.15 x 10super6 per foot), and three cowl positions (at the throat and two forward positions). For the higher contraction ratios, a large forward separation of the inflow boundary layer was observed, making the high contraction ratio configurations unsuitable for flight operation. A decrease in the free-stream unit Reynolds number (Re) of only a factor of 2 led to a similar upstream separation. Although the presence of such large-scale separations leads to the question of whether the inlet is started, the presence of internal oblique swept shock interactions the sidewalls seems to indicate that at least in the classical sense, the inlet is not unstarted. The laminar inflow boundary layer therefore appears to be very sensitive to increases in contraction ratio (CR) or decreases in Reynolds number; only the CR = 3 configuration with 0, 25, and 50 percent cowl at Re = 2.15 x 10super6 per foot operated on design." @default.
- W2122585223 created "2016-06-24" @default.
- W2122585223 creator A5065189477 @default.
- W2122585223 date "2003-09-01" @default.
- W2122585223 modified "2023-09-23" @default.
- W2122585223 title "Mach 10 Experimental Database of a Three-Dimensional Scramjet Inlet Flow Field" @default.
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