Diamond Port Jet Interaction With Supersonic Flow

FAN Huai-guo; ZHANG Chun-xiao; HE Chuan

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FAN Huai-guo, ZHANG Chun-xiao, HE Chuan. Diamond Port Jet Interaction With Supersonic Flow[J]. Applied Mathematics and Mechanics, 2005, 26(10): 1209-1215.

Citation:

FAN Huai-guo, ZHANG Chun-xiao, HE Chuan. Diamond Port Jet Interaction With Supersonic Flow[J]. Applied Mathematics and Mechanics, 2005, 26(10): 1209-1215.

Citation:

FAN Huai-guo, ZHANG Chun-xiao, HE Chuan. Diamond Port Jet Interaction With Supersonic Flow[J]. Applied Mathematics and Mechanics, 2005, 26(10): 1209-1215.

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Diamond Port Jet Interaction With Supersonic Flow

1.
College of Power Engineering, Chongqing University, Chongqing 400044, P. R. China;

Received Date: 2004-02-23
Rev Recd Date: 2005-05-13
Publish Date: 2005-10-15

Abstract

Abstract

Interaction flow field of the sonic air jet through diamond shaped orifices at different incidence angles (10 degrees, 27.5 degrees, 45 degrees and 90 degrees) and total pressures (0.10 and 0.46 MPa) with a Mach 5.0 freestream was studied experimentally. A 90 degrees circular injector was examined for comparison. Cross-section Mach number contours were acquired by a Pitot-cone five-hole pressure probe. The results indicate that the low Mach semicircular region close to the wall is the wake region. The boundary layer thinning is in the areas adjacent to the wake. For the detached case, the interaction shock extends further into the freestream, and the shock shape has more curvature, also the low-Mach upwash region is larger. The vortices of the plume and the height of the jet interaction shock increase with increasing incidence angle and jet pressure. 90 degrees diamond and circular injector have stronger plume vorticity, and for the circular injector low-Mach region is smaller than that for the diamond injector. Tapered ramp increases the plume vorticity, and the double ramp reduces the level of vorticity. The three-dimensional interaction shock shape was modeled from the surface shock shape, the center plane shock shape, and cross-sectional shock shape. The shock total pressure was estimated with the normal component of the Mach number using normal shock theory. The shock induced total pressure losses decrease with decreasing jet incidence angle and injection pressure, where the largest losses are incurred by the 90 degrees, circular injector.
- diamond injector,
- jet interaction with cross flow,
- interaction shock wave,
- counter-rotating vortices,
- mixing

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References(12)

References

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