XFOIL Version 6.94 Calculated polar for: S3021-095-84 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3609 0.00761 0.00245 -0.0687 0.7195 1.0000 0.500 0.4093 0.00774 0.00240 -0.0671 0.6973 1.0000 1.000 0.4583 0.00790 0.00240 -0.0655 0.6761 1.0000 1.500 0.5077 0.00810 0.00243 -0.0640 0.6555 1.0000 2.000 0.5573 0.00829 0.00254 -0.0626 0.6342 1.0000 2.500 0.6070 0.00849 0.00266 -0.0612 0.6115 1.0000 3.000 0.6565 0.00874 0.00279 -0.0598 0.5885 1.0000 3.500 0.7061 0.00896 0.00301 -0.0583 0.5621 1.0000 4.000 0.7554 0.00923 0.00324 -0.0569 0.5341 1.0000 4.500 0.8044 0.00955 0.00353 -0.0555 0.5027 1.0000 5.000 0.8530 0.00993 0.00387 -0.0540 0.4666 1.0000 5.500 0.9003 0.01043 0.00430 -0.0523 0.4252 1.0000 6.000 0.9462 0.01106 0.00482 -0.0506 0.3747 1.0000 6.500 0.9890 0.01195 0.00546 -0.0485 0.3073 1.0000 7.000 1.0306 0.01301 0.00631 -0.0464 0.2447 1.0000 7.500 1.0722 0.01410 0.00725 -0.0443 0.1915 1.0000 8.000 1.1080 0.01567 0.00846 -0.0416 0.1210 1.0000 8.500 1.1313 0.01829 0.01048 -0.0373 0.0318 1.0000 9.000 1.1590 0.02038 0.01265 -0.0332 0.0178 1.0000 9.500 1.1804 0.02252 0.01501 -0.0283 0.0153 1.0000 10.000 1.1839 0.02532 0.01805 -0.0214 0.0144 1.0000 10.500 1.1910 0.02830 0.02127 -0.0162 0.0141 1.0000 11.000 1.1995 0.03162 0.02483 -0.0124 0.0136 1.0000 11.500 1.2087 0.03529 0.02876 -0.0096 0.0126 1.0000 12.000 1.2155 0.03970 0.03343 -0.0072 0.0122 1.0000 12.500 1.2207 0.04480 0.03884 -0.0053 0.0120 1.0000 13.000 1.2224 0.05059 0.04498 -0.0042 0.0120 1.0000 13.500 1.2154 0.05777 0.05257 -0.0041 0.0120 1.0000 14.000 1.1987 0.06660 0.06185 -0.0056 0.0122 1.0000 14.500 1.1729 0.07737 0.07305 -0.0093 0.0123 1.0000 15.000 1.1411 0.09036 0.08645 -0.0155 0.0125 1.0000 15.500 1.1050 0.10580 0.10227 -0.0243 0.0128 1.0000 16.000 1.0673 0.12355 0.12034 -0.0352 0.0130 1.0000 16.500 1.0247 0.14488 0.14194 -0.0485 0.0134 1.0000 17.000 0.9726 0.17232 0.16952 -0.0642 0.0142 1.0000