A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor

Xiao Min; Liu Bo; Zhong Yongxing

Volume 15 Issue 3

Jul. 2000

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Xiao Min, Liu Bo, Zhong Yongxing. A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor[J]. Journal of Aerospace Power, 2000, 15(3): 237-240.

Citation:

Xiao Min, Liu Bo, Zhong Yongxing. A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor[J]. Journal of Aerospace Power, 2000, 15(3): 237-240.

Xiao Min, Liu Bo, Zhong Yongxing. A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor[J]. Journal of Aerospace Power, 2000, 15(3): 237-240.

Citation:

Xiao Min, Liu Bo, Zhong Yongxing. A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor[J]. Journal of Aerospace Power, 2000, 15(3): 237-240.

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A Study on Geometric Methods for Designing Supersonic Aerofoil of Axial Flow Compressor

1.
Aero.Gas Turbine Establishment,Jiangyou 621703,China
2.
7th Dept.Northwest Polytechnic University,Xi'an 710072,China

Received Date: 1999-07-07
Rev Recd Date: 2000-02-09
Publish Date: 2000-07-28

Abstract

Abstract

Three geometric methods for designing supersonic airfoil meanline are studied.The parameters which control curvature in the leading region of airfoil and their variations are considered.The flow fields of the cascade designed with these methods are analyzed.It is shown that the Mach number distribution of designed blade surface is ideal,shock wave structure is reasonable.But the exponential method is superior.
- axial flow compressor,
- blade,
- blade profile,
- design