XFOIL Version 6.96 Calculated polar for: S1010 HPV airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.9494 0.07114 0.06889 -0.0018 1.0000 0.0037 -11.750 -0.9820 0.05952 0.05725 -0.0110 1.0000 0.0035 -11.500 -1.0046 0.04780 0.04530 -0.0198 1.0000 0.0034 -11.000 -1.0405 0.03759 0.03449 -0.0188 1.0000 0.0034 -10.750 -1.0453 0.03322 0.02970 -0.0176 1.0000 0.0035 -10.500 -1.0420 0.02968 0.02576 -0.0162 1.0000 0.0036 -10.250 -1.0319 0.02699 0.02273 -0.0150 1.0000 0.0037 -10.000 -1.0172 0.02496 0.02043 -0.0140 1.0000 0.0039 -9.750 -0.9989 0.02349 0.01876 -0.0132 1.0000 0.0041 -9.500 -0.9788 0.02231 0.01742 -0.0125 1.0000 0.0044 -9.250 -0.9572 0.02139 0.01636 -0.0119 1.0000 0.0048 -9.000 -0.9358 0.02035 0.01516 -0.0112 1.0000 0.0051 -8.750 -0.9137 0.01939 0.01404 -0.0105 1.0000 0.0056 -8.500 -0.8917 0.01836 0.01280 -0.0098 1.0000 0.0060 -8.250 -0.8693 0.01740 0.01166 -0.0091 1.0000 0.0064 -8.000 -0.8477 0.01618 0.01027 -0.0082 1.0000 0.0071 -7.750 -0.8242 0.01542 0.00943 -0.0076 1.0000 0.0081 -7.500 -0.8000 0.01484 0.00876 -0.0071 1.0000 0.0093 -7.250 -0.7756 0.01429 0.00811 -0.0065 1.0000 0.0105 -7.000 -0.7507 0.01388 0.00760 -0.0060 1.0000 0.0113 -6.750 -0.7270 0.01317 0.00682 -0.0053 1.0000 0.0136 -6.500 -0.7023 0.01276 0.00636 -0.0048 1.0000 0.0154 -6.250 -0.6775 0.01235 0.00589 -0.0043 1.0000 0.0167 -6.000 -0.6529 0.01192 0.00539 -0.0036 1.0000 0.0183 -5.750 -0.6286 0.01142 0.00486 -0.0029 1.0000 0.0212 -5.500 -0.6041 0.01104 0.00445 -0.0023 1.0000 0.0238 -5.250 -0.5796 0.01068 0.00406 -0.0016 1.0000 0.0282 -5.000 -0.5553 0.01033 0.00373 -0.0009 1.0000 0.0358 -4.750 -0.5311 0.01002 0.00340 -0.0001 1.0000 0.0430 -4.500 -0.5066 0.00978 0.00315 0.0006 1.0000 0.0494 -4.250 -0.4825 0.00951 0.00291 0.0014 1.0000 0.0576 -4.000 -0.4583 0.00929 0.00270 0.0021 1.0000 0.0647 -3.750 -0.4343 0.00908 0.00251 0.0029 1.0000 0.0733 -3.500 -0.4106 0.00887 0.00234 0.0038 1.0000 0.0845 -3.250 -0.3871 0.00866 0.00217 0.0046 1.0000 0.0990 -2.750 -0.3299 0.00829 0.00190 0.0041 0.9968 0.1280 -2.500 -0.2972 0.00811 0.00179 0.0030 0.9940 0.1430 -2.250 -0.2659 0.00793 0.00167 0.0022 0.9907 0.1609 -2.000 -0.2339 0.00773 0.00157 0.0012 0.9872 0.1872 -1.750 -0.1937 0.00749 0.00147 -0.0015 0.9811 0.2230 -1.500 -0.1534 0.00716 0.00134 -0.0041 0.9598 0.2754 -1.250 -0.1196 0.00684 0.00121 -0.0053 0.9341 0.3377 -1.000 -0.0923 0.00649 0.00111 -0.0051 0.9113 0.4191 -0.750 -0.0678 0.00611 0.00103 -0.0043 0.8887 0.5153 -0.500 -0.0453 0.00563 0.00096 -0.0031 0.8665 0.6397 -0.250 -0.0235 0.00530 0.00097 -0.0014 0.8412 0.7525 0.000 0.0000 0.00523 0.00099 0.0000 0.8082 0.8081 0.250 0.0236 0.00530 0.00097 0.0014 0.7534 0.8410 0.500 0.0454 0.00563 0.00096 0.0030 0.6404 0.8666 0.750 0.0678 0.00611 0.00103 0.0043 0.5148 0.8885 1.000 0.0923 0.00649 0.00111 0.0051 0.4192 0.9111 1.250 0.1196 0.00683 0.00121 0.0053 0.3382 0.9341 1.500 0.1534 0.00716 0.00134 0.0041 0.2754 0.9598 1.750 0.1937 0.00749 0.00147 0.0015 0.2224 0.9813 2.000 0.2340 0.00773 0.00157 -0.0013 0.1874 0.9873 2.250 0.2660 0.00793 0.00166 -0.0022 0.1611 0.9908 2.500 0.2974 0.00811 0.00179 -0.0031 0.1431 0.9941 2.750 0.3300 0.00828 0.00190 -0.0042 0.1280 0.9969 3.250 0.3868 0.00866 0.00216 -0.0046 0.0989 1.0000 3.500 0.4103 0.00886 0.00234 -0.0037 0.0849 1.0000 3.750 0.4340 0.00908 0.00251 -0.0029 0.0733 1.0000 4.000 0.4580 0.00929 0.00270 -0.0021 0.0647 1.0000 4.250 0.4822 0.00951 0.00291 -0.0013 0.0577 1.0000 4.500 0.5063 0.00978 0.00315 -0.0005 0.0495 1.0000 4.750 0.5307 0.01002 0.00340 0.0002 0.0432 1.0000 5.000 0.5550 0.01033 0.00373 0.0009 0.0359 1.0000 5.250 0.5794 0.01068 0.00406 0.0016 0.0282 1.0000 5.500 0.6039 0.01104 0.00444 0.0023 0.0238 1.0000 5.750 0.6285 0.01142 0.00486 0.0030 0.0211 1.0000 6.000 0.6528 0.01192 0.00538 0.0037 0.0184 1.0000 6.250 0.6774 0.01235 0.00588 0.0043 0.0167 1.0000 6.500 0.7023 0.01276 0.00637 0.0048 0.0154 1.0000 6.750 0.7271 0.01318 0.00686 0.0053 0.0136 1.0000 7.000 0.7508 0.01388 0.00761 0.0060 0.0113 1.0000 7.250 0.7757 0.01431 0.00813 0.0065 0.0105 1.0000 7.500 0.8002 0.01484 0.00876 0.0070 0.0093 1.0000 7.750 0.8244 0.01544 0.00945 0.0076 0.0081 1.0000 8.000 0.8478 0.01621 0.01030 0.0082 0.0070 1.0000 8.250 0.8695 0.01740 0.01167 0.0090 0.0064 1.0000 8.500 0.8920 0.01837 0.01281 0.0097 0.0060 1.0000 8.750 0.9141 0.01938 0.01403 0.0105 0.0056 1.0000 9.000 0.9360 0.02039 0.01520 0.0112 0.0051 1.0000 9.250 0.9579 0.02132 0.01628 0.0118 0.0047 1.0000 9.500 0.9798 0.02218 0.01727 0.0123 0.0044 1.0000 9.750 0.9999 0.02337 0.01862 0.0131 0.0041 1.0000 10.000 1.0176 0.02497 0.02045 0.0139 0.0039 1.0000 10.250 1.0324 0.02700 0.02274 0.0149 0.0037 1.0000 10.500 1.0413 0.02989 0.02599 0.0162 0.0035 1.0000 10.750 1.0439 0.03354 0.03005 0.0175 0.0034 1.0000 11.000 1.0369 0.03823 0.03518 0.0187 0.0034 1.0000 11.500 1.0051 0.04793 0.04543 0.0195 0.0034 1.0000 11.750 0.9772 0.06116 0.05889 0.0092 0.0034 1.0000 12.000 0.9483 0.07168 0.06942 0.0013 0.0037 1.0000