Design of nozzle inviscid contour based on axial Mach number distribution

Hu Zhenzhen; Li Zhenqian; Shi Yilei; Chen Aiguo

doi:10.11729/syltlx20150115

Volume 30 Issue 4

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Hu Zhenzhen, Li Zhenqian, Shi Yilei, et al. Design of nozzle inviscid contour based on axial Mach number distribution[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(4): 97-104. doi: 10.11729/syltlx20150115

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Design of nozzle inviscid contour based on axial Mach number distribution

doi: 10.11729/syltlx20150115

Hypersonic Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2015-09-04
Rev Recd Date: 2015-12-04
Publish Date: 2016-08-25

Abstract

Abstract

The supersonic inviscid contour design methods were studied for the hypersonic wind tunnel axial-symmetric nozzle. The Direct-design technique based on the axial Mach number distribution presetting was introduced, the axial Mach number distribution presetting method based on the ratio of area was improved, and a new multipoint-control characteristic point distribution method was proposed. The designed nozzle characteristic network was triangulated and compared with the numerical simulation result, and influencing factors were analyzed for the nozzle inviscid contour. Results indicate that: the feasibility of the axial Mach number distribution presetting method based on the ratio of area is guaranteed by the present improvement; the nozzle inviscid contour is significantly affected by the axial Mach number distribution, axial characteristic point distribution and the amount of characteristic points on the boundary.
- hypersonic wind tunnel,
- supersonic inviscid contour,
- direct-design,
- axial Mach number distribution

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References(19)

References

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