A High Resolution Aeroelasticity Method for Fighter Aircraft at Flight Reynolds Numbers
Abstract
The principle objective of the present study was the application and assessment of Detached-Eddy Simulation for predicting the massively separated flow around forebodies. Computations were performed of the flow around both stationary and rotating forebodies at a Reynolds number of 2.1 million and at angles of attack of 60 and 90 degrees. While RANS predictions at 60 degrees angle of attack were adequate for the mean pressure distribution, at 90 degrees angle-of-attack, RANS yielded coherent vortical structures along the forebody that result in substantially greater variations in the surface pressure than measured. DES predictions accurately accounted for the chaotic structure in the wake; predicted pressures were in good agreement with measurements. For the forebody undergoing prescribed rotary motion at a spin coefficient of 0.2, DES predictions were mostly adequate though with some discrepancies between predicted and measured pressures. Possible causes for the discrepancies and discussion of other issues important to successful applications of DES are also summarized in this report. In the supplement, RANS and DES were applied to prediction of the separated flow over a surface-mounted hump, the objective being an assessment of the techniques in an application relevant to flow control. Detailed comparisons of the RANS and DES against experiments for three configurations are reported.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 20, 2004
- Accession Number
- ADA427305
Entities
People
- Kyle D. Squires
Organizations
- Arizona State University