This paper presents a discussion of a methodology of the paneled-wing method for calculating aircraft-induced wake velocities. This discussion will include a description of how an aircraft and its wake are represented by finite length vortex filaments, how the strength and location of these filaments are determined based upon aircraft characteristics and trajectory data, and how the induced velocity values are determined once the location and strength of the vortex filaments are known. Examples will be presented showing comparisons between induced velocity values calculated using both the paneled-wing method and Strickland's lifting line method. Comparison is also made between calculated results from the paneled-wing method and wind tunnel data collected in the wake of a scale model aircraft. Additional examples will show the effect of including aircraft downwash calculations in a trajectory analysis for a parachute-retarded store delivered via aircraft. 3 refs., 12 figs.
Vortex panel method for calculating aircraft downwash on parachute trajectories
1991
18 pages
Report
Keine Angabe
Englisch
Downwash Design Criteria for VTOL Aircraft
British Library Conference Proceedings | 1993
|Line-vortex theory for calculation of supersonic downwash
Engineering Index Backfile | 1950
|