Abstract
This paper describes a method with correction for the sidewall effects and the evaluation of the air foil test in the two-dimensional transonic wind tunnel. Surface pressure and drag measurements on the NACA0012 airfoil were conducted in the two-dimensional wind tunnel of National Aerospace Laboratory (NAL,Japan). Using a comparison with other wind tunnel data, the wall interference effects are discussed, especially those from the sidewall. The results suggest that the Mach number of the actual flow around the airfoil is lower than the setting Mach number. The Mach number correction for the sidewall boundary-layer effects based on the similarity rule was applied to the present measurements, thereby showing that the shock positions the pressure distributions, and the minimum drag coefficients are in good agreement with both other wind tunnel results and the Navier-Stokes calculation. It is shown that this correction method and the evaluation indicates satisfactory transonic airfoil test results in the NAL two-dimensional transonic wind tunnel. 10 refs., 11 figs., 1 tab.
Sudani, N;
Kanda, H;
Sato, M;
Miwa, H;
Matsuno, K;
Takanashi, S
[1]
- National Aerospace Laboratory, Tokyo (Japan)
Citation Formats
Sudani, N, Kanda, H, Sato, M, Miwa, H, Matsuno, K, and Takanashi, S.
Evaluation of NACA0012 airfoil test results in the NAL two-dimensional transonic wind tunnel.
Japan: N. p.,
1991.
Web.
Sudani, N, Kanda, H, Sato, M, Miwa, H, Matsuno, K, & Takanashi, S.
Evaluation of NACA0012 airfoil test results in the NAL two-dimensional transonic wind tunnel.
Japan.
Sudani, N, Kanda, H, Sato, M, Miwa, H, Matsuno, K, and Takanashi, S.
1991.
"Evaluation of NACA0012 airfoil test results in the NAL two-dimensional transonic wind tunnel."
Japan.
@misc{etde_10149457,
title = {Evaluation of NACA0012 airfoil test results in the NAL two-dimensional transonic wind tunnel}
author = {Sudani, N, Kanda, H, Sato, M, Miwa, H, Matsuno, K, and Takanashi, S}
abstractNote = {This paper describes a method with correction for the sidewall effects and the evaluation of the air foil test in the two-dimensional transonic wind tunnel. Surface pressure and drag measurements on the NACA0012 airfoil were conducted in the two-dimensional wind tunnel of National Aerospace Laboratory (NAL,Japan). Using a comparison with other wind tunnel data, the wall interference effects are discussed, especially those from the sidewall. The results suggest that the Mach number of the actual flow around the airfoil is lower than the setting Mach number. The Mach number correction for the sidewall boundary-layer effects based on the similarity rule was applied to the present measurements, thereby showing that the shock positions the pressure distributions, and the minimum drag coefficients are in good agreement with both other wind tunnel results and the Navier-Stokes calculation. It is shown that this correction method and the evaluation indicates satisfactory transonic airfoil test results in the NAL two-dimensional transonic wind tunnel. 10 refs., 11 figs., 1 tab.}
place = {Japan}
year = {1991}
month = {May}
}
title = {Evaluation of NACA0012 airfoil test results in the NAL two-dimensional transonic wind tunnel}
author = {Sudani, N, Kanda, H, Sato, M, Miwa, H, Matsuno, K, and Takanashi, S}
abstractNote = {This paper describes a method with correction for the sidewall effects and the evaluation of the air foil test in the two-dimensional transonic wind tunnel. Surface pressure and drag measurements on the NACA0012 airfoil were conducted in the two-dimensional wind tunnel of National Aerospace Laboratory (NAL,Japan). Using a comparison with other wind tunnel data, the wall interference effects are discussed, especially those from the sidewall. The results suggest that the Mach number of the actual flow around the airfoil is lower than the setting Mach number. The Mach number correction for the sidewall boundary-layer effects based on the similarity rule was applied to the present measurements, thereby showing that the shock positions the pressure distributions, and the minimum drag coefficients are in good agreement with both other wind tunnel results and the Navier-Stokes calculation. It is shown that this correction method and the evaluation indicates satisfactory transonic airfoil test results in the NAL two-dimensional transonic wind tunnel. 10 refs., 11 figs., 1 tab.}
place = {Japan}
year = {1991}
month = {May}
}