EXPERIMENTAL-VERIFICATION OF A WALL INTERFERENCE CORRECTION METHOD WITH INTERFACE MEASUREMENTS

被引：0
作者：
LO, CF
ULBRICH, N
机构：
[1] University of Tennessee Space Institute, Tullahoma, TN
来源：
JOURNAL OF AIRCRAFT | 1993年 / 30卷 / 06期
基金：
美国国家航空航天局;
关键词：
Airfoils - Computational methods - Error correction - Interfaces (materials) - Pressure measurement - Subsonic aerodynamics - Transonic aerodynamics - Velocity measurement - Wall flow;
D O I：
10.2514/3.46421
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A wall interference assessment and correction method for two-dimensional subsonic wind-tunnel testing is presented. Pressure coefficient and angle-of-attack correction are calculated using velocity measurements on interfaces inside the wind tunnel. A mathematical representation of the test article and tunnel wall boundary conditions is not required. Available experimental data of an NACA 0012 airfoil tested at a Mach number of 0.70 and at two different angle of attack in a solid wall wind tunnel are applied to the method. Blockage corrections are computed and corrected surface pressure coefficients compare favorably to free-air flowfield data if the tunnel flowfield is subsonic. The present wall interference correction method can determine blockage corrections in transonic wind-tunnel flowfields with restrictions. The computed angle-of-attack correction is negligible for the given experimental data.
引用
收藏
页码：813 / 817
页数：5
相关论文
共 7 条
  • [1] Lo C.F., Tunnel Interference Assessment by Boundary Measurements, AIAA Journal, 16, 4, pp. 411-413, (1978)
  • [2] Lo C.F., Tunnel Interference Assessment from Measurements on Two Interfaces, AIAA Journal, 28, 8, pp. 1481-1484, (1990)
  • [3] Lo C.F., Ulbrich N., Comparison of One- and Two- Interface Methods for Tunnel Wall Interference Calculation, Journal of Aircraft, 27, 8, pp. 732-735, (1990)
  • [4] Green L., Zhang Q., Garriz J., Wang S., Vatsa V., Haigler K., Newman P., NASA/CAE Wind Tunnel Interference Cooperative Program-Status and Sample Results, (1991)
  • [5] Amick J.L., Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds with that Calculated by the Relaxation Method, (1950)
  • [6] Vidal R.J., Catlin P.A., Chudyk D.W., Two-Dimensional Subsonic Experiments with an NACA 0012 Airfoil, (1973)
  • [7] Lo C.F., Ulbrich N., Experimental Results on a Wall Interference Correction Method with Interface Measurements, (1992)
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