A study of aircraft trailing vortex systems, involving actual flight testing as well as model testing and analytical considerations, resulted in a method for predicting the vortex geometry and velocity field downstream of an aircraft. It is found that the vortex decay can be described by geometric similarity considerations and not by any modification of the Navier-Stokes equations. This conclusion is based on detailed velocity measurements made through the vortex immediately behind a test aircraft up to distances of approximately 1000 chord lengths downstream of the aircraft. The report includes a presentation of the data on which the conclusions are based, as well as a description of test equipment and procedures. (Author)
Structure of Trailing Vortices
1968
10 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Vortices , Supersonic planes , Interactions , Wake , Turbulence , Swept-back wings , Trailing edge , Equations of motion , Model tests , Flight testing , Velocity , Geometry , Reprints
Structure of trailing vortices.
AIAA | 1968
|Structure of trailing vortices
Engineering Index Backfile | 1968
|AIAA | 1994
British Library Conference Proceedings | 1994
|British Library Conference Proceedings | 1994
|