An approximate method for calculating aircraft downwash on parachute trajectories

Conference · Sun Jan 01 00:00:00 EST 1989

OSTI ID:5792470

Strickland, J. H.

An approximate method for calculating velocities induced by aircraft on parachute trajectories is presented herein. A simple system of quadrilateral vortex panels is used to model the aircraft wing and its wake. The purpose of this work is to provide a simple analytical tool which can be used to approximate the effect of aircraft-induced velocities on parachute performance. Performance issues such as turnover and wake recontact may be strongly influenced by velocities induced by the wake of the delivering aircraft, especially if the aircraft is maneuvering at the time of parachute deployment. 7 refs., 9 figs.

• Research Organization: Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
• DOE Contract Number: AC04-76DP00789
• OSTI ID: 5792470
• Report Number(s): SAND-88-0442C; AIAA-89-0899; CONF-8904118-9; ON: DE89008122
• Resource Relation: Conference: 10. AIAA aerodynamic decelerator systems technical conference, Cocoa Beach, FL (United States), 18-20 Apr 1989
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
99 GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE
75 CONDENSED MATTER PHYSICS
SUPERCONDUCTIVITY AND SUPERFLUIDITY
PARACHUTES
MATHEMATICAL MODELS
A CODES
AERODYNAMICS
AIRCRAFT
COMPRESSIBLE FLOW
TRAJECTORIES
TURBULENCE
VELOCITY
VORTEX FLOW
COMPUTER CODES
FLUID FLOW
FLUID MECHANICS
MECHANICS
420200* - Engineering- Facilities
Equipment
& Techniques
990230 - Mathematics & Mathematical Models- (1987-1989)
640410 - Fluid Physics- General Fluid Dynamics