APSI/Advanced Exhaust Nozzle Test Results at Mach Numbers from 0.6 to 1.5.
Abstract
A test program was conducted in the Propulsion Wind Tunnel to obtain force and moment and surface pressure data on a 0.096-scale model of a proposed tactical aircraft. The force data were acquired with two separate internal balances, which measured the aircraft and the nozzle thrust-minus-drag loads, respectively.Results were obtained for two axisymmetric and four nonaxisymmetric nozzles at three simulated power settings. Nozzle deflections were simulated to define the change in maneuverability to be gained by vectoring the simulated exhaust jet. In addition to the simulated powered configurations, an open inlet flow-through reference configuration was tested to determine the basic airframe aerodynamics with forward and aft wing placements. The tests were conducted at Mach number from 0.6 to 1.5 at a free-stream Reynols number of 2.5 million/ft. Angle of attack was varied from -1 to 16 deg at nozzle pressure ratios from 1.0 (jet-off) to 20. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1979
- Accession Number
- ADB043562
Entities
People
- Ernest J. Lucas
Organizations
- Arnold Engineering Development Complex