Wake Vortex MinimizationA 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.
IDRelationTitle19780004085WorkVortex attenuation flight experiments19780004083WorkAircraft wake-vortex minimization by use of flaps19780004082WorkGround development and flight correlation of the vortex attenuating spline device19780004075WorkInviscid modeling of aircraft trailing vortices19780004077WorkGround-based facilities for evaluating vortex minimization concepts19780004080WorkUnsuccessful Concepts for Aircraft Wake Vortex Minimization19780004079WorkFlight test techniques for wake-vortex minimization studies19780004084WorkThe development and use of spoilers as vortex attenuators19780004076WorkViscous effects in aircraft trailing vortices19780004078WorkApplication of laser velocimetry to aircraft wake-vortex measurements19780004081WorkThrust-augmented vortex attenuation