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Design of Curved Shock Compression Surface and Experimental Investigation

Author: JuYan
Tutor: ZhangYuan
School: Nanjing University of Aeronautics and Astronautics
Course: Aerospace Propulsion Theory and Engineering
Keywords: Hypersonic inlet Aircraft / engine integration design Unconventional compression wall Bending shock Other pressure gradient
CLC: V229
Type: Master's thesis
Year: 2005
Downloads: 272
Quote: 12
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Abstract


In the design of the precursor with an inlet integration of hypersonic aircraft , in order to shorten the compression surface length and ensure the stability of the precursor boundary layer in the compression surface of the concept of a novel unconventional compression surface design and study its design method, using the bending compression type surface formed in this way can produce bent shock . In this paper, the theoretical analysis , the method of numerical simulation and experimental study of compression face surface has different curvature of this study , and isentropic compression and conventional two-dimensional wedge compression compare . The main compression surface uniform flow conditions the design point and the aerodynamic performance of the non- design point , a brief analysis of the aerodynamic performance of the non - uniform flow conditions , the design point . According to the theory , design and processing M5.3 bending the compression surface model , M5.3 and M3.85 wind tunnel experiment , experiment , measuring the compression surface static pressure distribution and compression of the surface of the outlet section Pitot total pressure distribution , and shooting a bent shock morphology schlieren photographs . The results show that : the curved shock compression wall smaller initial compression angle , can reduce the risk of the precursor of the boundary layer separation ; compression and isentropic compression surface length can be reduced by 25% compared ; compression surface on pressure along the flow close to the pressure gradient distribution , lower than the maximum entropy compression pressure gradient , far lower than the two-dimensional wedge compression surface pressure gradient . Different to flow conditions and under different working conditions , the curved compression surface and a bending shock compression system's overall performance is better . Wind tunnel test results confirmed that the supersonic flow in compression surface square became the desired bending shock , shock surface morphology consistent with the results of numerical simulation , the wall pressure distribution is similar to the pressure gradient , export Pitot total pressure distribution and numerical simulation The results are similar . In this paper, the bending shock compression wall design is feasible .

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