NAVIER-STOKES PREDICTIONS FOR THE F-18 WING AND FUSELAGE AT LARGE INCIDENCE

被引：6

作者：

CUMMINGS, RM

RIZK, YM

SCHIFF, LB

CHADERJIAN, NM

机构：

[1] NASA Ames Research Center, Moffett Field, CA

[2] National Research Council Research Associate, California Polytechnic State University, Aeronautical Engineering Department

[3] High Alpha Technology, Fluid Dynamics Division

来源：

JOURNAL OF AIRCRAFT | 1992年 / 29卷 / 04期

关键词：

D O I：

10.2514/3.46203

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Navier-Stokes solutions have been obtained using the Chimera overset grid scheme for flow over the wing, fuselage, and wing leading-edge extension (LEX) of the F-18 aircraft at high incidence. Solutions are also presented for flow over the fuselage forebody at high angles of attack. The solutions are for turbulent flows at high-Reynolds-number flight-test conditions, and are compared with available qualitative and quantitative experimental data. Comparisons of predicted surface flow patterns, off-surface flow visualizations, and surface-pressure distributions are in good agreement with flight-test data. The ability of the numerical method to predict the bursting of the LEX vortex as it encounters the adverse pressure gradient field of the wing is demonstrated.

引用

页码：565 / 574

页数：10

共 39 条

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