1. The "Rockwell Semispan Propulsive WinglCanard model was tested in NASA Ages 14-foot tunnel during the fall of 1982 . The baseline configuration, as discussed in the previous section, was tested at Mach numbers of .6,8 and .9. at angles of attack from -4 to 12 degrees. Thcrc were five rows of pressure taps on the wing and two rows on the canard. In addition to force, inioment and pressure data, some flow field surveys were also made. All wind tunnel pressure data are spanwise position referenced by butt plane (B. P.) distance in inches, with B.P. = 0.0 occurring 5.47 inches from the fuselage center line. PANDORA wing and canard pressure profiles arc referenced by station number as generated by the code. all^ angles of attack (or alphas) are referenced to the fuselage.
2. Y Mach .6Alpha Two Degrees Case (figs 5-9)
3. The predicted canard pressures are in excellent agreement with experiment at the outboard station (fig. 9) and fair agreement at the inboard station (fig. 8) with the leading edge expansion being over predicted. The cove region is again of special interest where good agreement between experiment and predicted results did occur for both canard locations. Mach .9, Alpha 2. Derecs(figs 10-14)