Wind Tunnel Measurements of Total Force and Extremity Flail Potential Forces on a Crew Member in Close Proximity to a Cockpit
Abstract
In order to determine the aerodynamic forces acting upon a crewmember/escape seat combination at transonic speeds, and the flail potential forces acting on the crewmember's extremities, an existing half scale man/seat combination was integrated with a model of the forward portion of the F-16. The combination was tested in the Arnold Engineering Development Center Propulsion Wind Tunnel (PWT) Facility Transonic Wind Tunnel (16T) during the period September 9 to September 15, 1978, over the Mach number range 0.4 to 1.2. The basic data obtained in this way are reported in Reichenau. The present report describes the experimental set-up in detail and presents some typical force and force area (force/sq. q) plots. From earlier work it was determined that the flow over the model was 'supercritical', implying a turbulent boundary layer at separation, and a reasonably realistic simulation of full-scale conditions. Very marked interference effects were observed on the man/seat combination, due to fuselage proximity. The most dramatic were large increases in upper arm and upper leg flail potential forces. In almost all cases, the most severe interference occurred when a 'flow diverter' was mounted in front of the cockpit. Comparisons with other sources of data revealed generally good agreement, except that the drag of the model was somewhat low; presumably due to the fact that the model was smoother than its full scale equivalent.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1980
- Accession Number
- ADA100917
Entities
People
- Harold L. Newhouse
- James P. Brown
- Peter R. Payne