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논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 저널정보
- 한국유체기계학회 International Journal of Fluid Machinery and Systems International Journal of Fluid Machinery and Systems Vol.15 No.3
- 발행연도
- 2022.9
- 수록면
- 376 - 384 (9page)
- DOI
- 10.5293/IJFMS.2022.15.3.376
이용수
초록· 키워드
오류제보하기
The aim of the present study is two-fold. Firstly, it attempts to solve the asymptotic model of the 2D stationary potential flow of a supersonic viscous fluid over thin airfoils. In the case of a high Re number: Re=O(10<SUP>5</SUP>), and a free stream Mach number of M<SUB>∞</SUB> = 1.45, the asymptotic solution is built using the new successive complementary expansion method. The theoretical Mach number of the flow is estimated in the outer inviscid zone along the airfoil surface, and a correction term is added to account for the viscous boundary layer effect in order to get an accurate approximation throughout the whole domain.
Secondly, for comparison purposes, numerical simulations of the NACA 43013 airfoil were run for the Mach number distribution in each area. On the one hand, when compared to numerical simulations, the asymptotic supersonic laminar viscous flow solution shows good agreement for the laminar boundary layer but begins to diverge slightly from 𝒙 = 𝟎, 𝟑.At this point, the laminar-turbulent transition starts, then the turbulent boundary layer develops towards the trailing edge. On the other hand, the Mach number distribution for the outer inviscid region matches the simulation and illustrates the change in velocity upon interaction with both the detached shock wave and the expansion waves.
Secondly, for comparison purposes, numerical simulations of the NACA 43013 airfoil were run for the Mach number distribution in each area. On the one hand, when compared to numerical simulations, the asymptotic supersonic laminar viscous flow solution shows good agreement for the laminar boundary layer but begins to diverge slightly from 𝒙 = 𝟎, 𝟑.At this point, the laminar-turbulent transition starts, then the turbulent boundary layer develops towards the trailing edge. On the other hand, the Mach number distribution for the outer inviscid region matches the simulation and illustrates the change in velocity upon interaction with both the detached shock wave and the expansion waves.
목차
Abstract
1. Introduction
2. Solution of the problem
3. Numerical simulation results for NACA 43013 & interpretations
4. Interpretation
5. Conclusion
References
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