Abstract
The performance of a representative short takeoff and vertical landing model during transition flight is investigated by comparison of experimental and numerical simulations. The model consists of a 60-deg cropped delta wing planform; a simple fuselage shape blended to the wing; and tandem, circular, highpressure-air lift-jets that exit perpendicularly to the flat lower surface. The configuration minimizes the geometric complexity while retaining the important flow physics of the lift-jet/aerodynamic surface interaction. Three-dimensional, laminar, and turbulent Navier-Stokes computations are made using a multiple, overset grid scheme. Results are presented for jet-off and powered-lift cases and compared with the measured forces and pressures for the model at a freestream Mach number of 0.146, a 10-deg angle of attack, and sonic lift-jets. Computational flow visualization illustrates the presence of primary and secondary wing leading-edge vortices and the deflection of the lift-jets by the freestream. Significantly, both computational fluid dynamics and experiment predict a jet-induced lift loss that is mostly a result of a reduction in the suction pressure at the wing leading edge.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call