An Experimental Investigation of the Subcritical and Supercritical Flow About a Swept Semispan Wing
Abstract
An experimental investigation of the turbulent, subcritical and supercritical flow over a swept, NACA 0012 semispan wing in a solid-wall wind tunnel is described. The program was conducted over a range of free-stream Mach numbers (0.5 to 0.84), Reynolds numbers based on wing chord (2x10 to the 6th power to 8x10 to the 6th power), and angles of attack (0 deg to 2 deg) to provide a variety of test cases for assessment of wing computer codes and tunnel-wall-interference effects. The supercritical cases include flows both without and with three-dimensional flow separation. The principal data obtained were mean surface pressures for both the wing and tunnel walls. In addition, surface oil- flow patterns on the wing and mean-velocity, flow-field surveys (by laser Doppler velocimetry) were obtained for supercritical flow. All the pressure and flow-field data are given in tabular form, with representative results presented graphically to illustrate some of the effects of the test parameters. Comparison of the wing pressure sure data with results from two inviscid wing codes are also shown to assess the importance of viscous-flow and tunnel-wall effects.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1983
- Accession Number
- ADA279800
Entities
People
- H. L. Seegmiller
- William K. Lockman
Organizations
- National Aeronautics and Space Administration