A better understanding of propulsion system/airframe flow interactions could aid in the reduction of aircraft drag. For this purpose, NASA and the United States Air Force have conducted a series of wind-tunnel and flight tests on the F-15 airplane. This paper presents a correlation of flight test data from tests conducted at the NASA Dryden Flight Research Facility of the Ames Research Center, with data obtained from wind-tunnel tests. Flights were made at stabilized Mach numbers around 0.6, 0.9, 1.2, and 1.5 with accelerations up to near Mach number 2. Wind-tunnel tests used a 7.5 percent-scale F-15 inlet/airframe model. Flight and wind-tunnel pressure coefficients showed good agreement in most cases. Correlation of interaction effects caused by changes in cowl angle, angle-of-attack, and Mach number are presented. For the afterbody region, the pressure coefficients on the nozzle surfaces were influenced by boattail angles and Mach number. Boundary-layer thickness decreased as angle of attack increased above 4 deg.
Selected results of the F-15 propulsion interactions program
Joint Propulsion Conference ; 1982 ; Cleveland, OH
1982-06-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
YF-12 propulsion research program and results
NTRS | 1976
|Laser propulsion 10 kW thruster test program results
AIAA | 1992
|Laser Propulsion 10-kW Thruster Test Program Results
Online Contents | 1995
|