A status report is presented on research directed at reducing the vortex disturbances of aircraft wakes. The objective of such a reduction is to minimize the hazard to smaller aircraft that might encounter these wakes. Inviscid modeling was used to study trailing vortices and viscous effects were investigated. Laser velocimeters were utilized in the measurement of aircraft wakes. Flight and wind tunnel tests were performed on scale and full model scale aircraft of various design. Parameters investigated included the effect of wing span, wing flaps, spoilers, splines and engine thrust on vortex attenuation. Results indicate that vortives may be alleviated through aerodynamic means.
Wake Vortex Minimization
1977-01-01
Sonstige
Keine Angabe
Englisch
TIBKAT | 1977
Recent development in wake vortex minimization
Tema Archiv | 1978
|Recent Development in Wake Vortex Minimization
SAE Technical Papers | 1978
|Summary of NASA wake-vortex minimization research
NTRS | 1976
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