Forebody flow field effects on the high angle-of-attack lateral-directional aerodynamics of the F/A-18

[1]  David M. Richwine,et al.  In-Flight Flow Visualization Characteristics of the NASA F-18 High Alpha Research Vehicle at High Angles of Attack , 1989 .

[2]  P. Lamont The effect of Reynolds number on normal and side forces on ogive-cylinders at high incidence , 1985 .

[3]  D. Banks Wind-tunnel investigation of the forebody aerodynamics of a vortex-lift fighter configuration at high angles of attack , 1988 .

[4]  Daniel W. Banks,et al.  Surface flow visualization of separated flows on the forebody of an F-18 aircraft and wind-tunnel model , 1988 .

[5]  Cary Moskovitz,et al.  Experimental investigation of a new device to control the asymmetric flowfield on forebodies at large angles of attack , 1990 .

[6]  R. Hall,et al.  Progress in developing gritting techniques for high angle of attack flows , 1994 .

[7]  Vladislav Klein,et al.  Aerodynamic parameters of High-Angle-of attack Research Vehicle (HARV) estimated from flight data , 1990 .

[8]  R. E. Curry,et al.  An airborne system for vortex flow visualization on the F-18 high-alpha research vehicle , 1988 .

[9]  R. E. Curry,et al.  A smoke generator system for aerodynamic flight research , 1989 .

[10]  Daniel W. Banks,et al.  F-18 high alpha research vehicle surface pressures: Initial in-flight results and correlation with flow visualization and wind-tunnel data , 1990 .

[11]  Daniel W. Banks,et al.  Experimental investigation of the F/A-18 vortex flows at subsonic through transonic speeds , 1989 .

[12]  Gary E. Erickson Wind tunnel investigation of vortex flows on F/A-18 configuration at subsonic through transonic speed , 1991 .