Comparison of Flows Over a Supercritical and a Conventional Airfoil

Authors

  • Jenika Mistry

Keywords:

Supercritical airfoil, NACA/LANGLEY 0011 airfoil, NACA 0012 airfoil, Pressure coefficient, Transonic Mach number.

Abstract

A comparison of flows over the NACA/LANGLEY 0011 supercritical airfoil and NACA 0012 has been carried out at transonic Mach speed of 280 m/s. The analysis is carried out in the ANSYS Workbench. The boundary conditions are set accordingly and the Spalart-Allmaras turbulence model is used. Structured mesh has been generated for accurate results of flow simulation around the airfoil. Pressure coefficient curve, Velocity contour and Pressure contour are generated for both the airfoils and are compared. The simulation and analysis of pressure coefficient curve proves the effectiveness of the supercritical airfoil at transonic speeds.

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References

J. D. Anderson, Introduction to Flight, Published by McGraw Hill Education (India) Private Limited, 2018.

J. D. Anderson, Fundamentals of Aerodynamics, Published by McGraw-Hill, 2011.

Whitcomb, R. T., and L. R. Clark: “An Airfoil Shape for Efficient Flight at Supercritical Mach Numbers”, NASA TMX-1109, July 1965.

Published

2021-09-09

How to Cite

[1]
Jenika Mistry, “Comparison of Flows Over a Supercritical and a Conventional Airfoil”, TEMSJ, vol. 3, no. 4, pp. 216-220, Sep. 2021.

Issue

Section

Articles