XFOIL Version 6.94 Calculated polar for: RG-12 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2015 0.00614 0.00208 -0.0443 0.8491 0.8656 0.500 0.2532 0.00621 0.00204 -0.0428 0.8111 0.8836 1.000 0.3026 0.00632 0.00203 -0.0408 0.7703 0.9020 1.500 0.3498 0.00646 0.00206 -0.0383 0.7264 0.9202 2.000 0.3971 0.00662 0.00209 -0.0360 0.6790 0.9378 2.500 0.4480 0.00683 0.00215 -0.0347 0.6269 0.9542 3.000 0.5067 0.00713 0.00230 -0.0353 0.5705 0.9688 3.500 0.5721 0.00754 0.00250 -0.0376 0.5056 0.9819 4.000 0.6414 0.00806 0.00281 -0.0410 0.4326 0.9933 4.500 0.6938 0.00862 0.00314 -0.0411 0.3640 1.0000 5.000 0.7354 0.00930 0.00356 -0.0388 0.2956 1.0000 5.500 0.7807 0.01022 0.00416 -0.0373 0.2130 1.0000 6.000 0.8267 0.01122 0.00487 -0.0359 0.1437 1.0000 6.500 0.8718 0.01236 0.00575 -0.0344 0.0851 1.0000 7.000 0.9157 0.01368 0.00692 -0.0326 0.0438 1.0000 7.500 0.9584 0.01511 0.00833 -0.0306 0.0241 1.0000 8.000 0.9964 0.01705 0.01043 -0.0277 0.0154 1.0000 8.500 1.0313 0.01922 0.01275 -0.0245 0.0110 1.0000 9.000 1.0587 0.02243 0.01631 -0.0203 0.0099 1.0000 9.500 1.0880 0.02571 0.01999 -0.0165 0.0094 1.0000 10.000 1.1103 0.03002 0.02478 -0.0123 0.0092 1.0000 10.500 1.1206 0.03448 0.02973 -0.0069 0.0088 1.0000 11.000 1.1193 0.03829 0.03392 -0.0008 0.0083 1.0000 11.500 1.1081 0.04292 0.03893 0.0041 0.0079 1.0000 12.000 1.0798 0.05023 0.04669 0.0064 0.0079 1.0000 12.500 1.0407 0.06074 0.05764 0.0038 0.0082 1.0000 13.000 1.0014 0.07420 0.07146 -0.0041 0.0082 1.0000 13.500 0.9576 0.09227 0.08984 -0.0165 0.0085 1.0000