1. AIAA-2001-2462
2. AIAA-2001-2462
3. The wind-tunnel model is shown in Figure 5 mounted in the NTF test section on a straight sting. Force and moment data used herein were acquired at Mach 0.90 over an angle-of-attack range from -2 to 12 deg for Reynolds numbers of 11, 33, and 88 million, based on the mean aerodynamic chord. Dynamic pressure was varied from approximately 970 to 1800 psf, and included a dynamic pressure sweep at Rn=33 million to isolate and enable correction for static aeroelastic effects as described in reference 18. Detailed information on the various instrumentation devices, the data acquisition and control computers, and the data reduction algorithms is provided in reference 19, including corrections for free-stream flow angularity and cavity pressure effects. Wall and model support interference effects have not been accounted for in the data, but were minimized through model sizing (ref. 18). All data presented herein was acquired with fixed transition on the forebody, as described in reference 18, and natural transition on the wing. Data repeatability was determined as described in reference 18, and can be characterized with 95% confidence intervals of
4. AIAA-2001-2462