AFWAL Advanced STOL Nozzle Test Results at Mach Numbers from 0.6 to 1.5.
Abstract
Wind tunnel data were obtained on a 1/8-scale model of an advanced fighter aircraft to measure the effect of simulated jet plumes from various advanced nozzles on the highly integrated airframe. Aerodynamic forces and thrust loads were measured on the entire model, excluding the vertical tail which was used to support the model. Wind surface pressure data were simultaneously obtained at selected test conditions. Four axisymmetric and nonaxisymmetric nozzle designs were tested in various configurations including afterburner and nonafterburner power settings and nozzle deflection angles up to 20 deg. High-pressure air was used to simulate exhaust plumes at nozzle pressure ratios up to 13 while model angle of attack varied from 0 to 10 deg. Free-stream test conditions included Mach numbers from 0.6 to 1.5 at a constant unit Reynolds number of 2.0 x million/ft. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1982
- Accession Number
- ADB085898
Entities
People
- C. L. Smith
Organizations
- Arnold Engineering Development Complex