XFOIL Version 6.96 Calculated polar for: NASA RC(4)-10 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -1.2058 0.04760 0.04504 -0.0267 1.0000 0.0109 -13.750 -1.2248 0.03912 0.03620 -0.0273 1.0000 0.0110 -13.500 -1.2228 0.03583 0.03269 -0.0264 1.0000 0.0110 -13.250 -1.2151 0.03336 0.03003 -0.0253 1.0000 0.0111 -13.000 -1.2040 0.03129 0.02779 -0.0243 1.0000 0.0112 -12.750 -1.1902 0.02952 0.02587 -0.0233 1.0000 0.0113 -12.500 -1.1744 0.02796 0.02415 -0.0224 1.0000 0.0114 -12.250 -1.1570 0.02657 0.02263 -0.0215 1.0000 0.0115 -12.000 -1.1383 0.02533 0.02125 -0.0207 1.0000 0.0116 -11.750 -1.1206 0.02442 0.02007 -0.0192 0.8912 0.0116 -11.500 -1.1019 0.02353 0.01896 -0.0180 0.8587 0.0117 -11.250 -1.0811 0.02267 0.01791 -0.0171 0.8401 0.0118 -11.000 -1.0593 0.02186 0.01694 -0.0164 0.8268 0.0119 -10.750 -1.0367 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0.0869 -1.250 -0.0245 0.00806 0.00149 -0.0043 0.5942 0.0933 -1.000 0.0039 0.00802 0.00144 -0.0043 0.5843 0.0990 -0.750 0.0322 0.00800 0.00139 -0.0042 0.5713 0.1033 -0.500 0.0605 0.00799 0.00135 -0.0042 0.5533 0.1077 -0.250 0.0887 0.00802 0.00131 -0.0041 0.5290 0.1122 0.000 0.1167 0.00812 0.00129 -0.0041 0.4938 0.1149 0.250 0.1420 0.00888 0.00146 -0.0040 0.3270 0.1195 0.500 0.1693 0.00914 0.00154 -0.0039 0.2741 0.1247 0.750 0.1971 0.00930 0.00159 -0.0039 0.2434 0.1293 1.000 0.2251 0.00939 0.00162 -0.0039 0.2249 0.1344 1.250 0.2531 0.00945 0.00165 -0.0039 0.2122 0.1407 1.750 0.3091 0.00956 0.00174 -0.0038 0.1933 0.1576 2.000 0.3371 0.00960 0.00178 -0.0038 0.1854 0.1697 2.250 0.3649 0.00963 0.00184 -0.0037 0.1779 0.1928 2.500 0.3850 0.00849 0.00185 -0.0027 0.1740 0.6168 2.750 0.4098 0.00825 0.00191 -0.0020 0.1689 0.7146 3.000 0.4298 0.00783 0.00202 -0.0001 0.1638 0.8758 3.250 0.4591 0.00782 0.00215 -0.0001 0.1595 0.9397 3.500 0.4997 0.00798 0.00230 -0.0029 0.1538 0.9645 3.750 0.5374 0.00816 0.00244 -0.0050 0.1485 0.9765 4.250 0.6045 0.00844 0.00268 -0.0074 0.1418 0.9881 4.500 0.6378 0.00862 0.00281 -0.0086 0.1370 0.9924 4.750 0.6721 0.00879 0.00295 -0.0100 0.1330 0.9950 5.000 0.7071 0.00893 0.00309 -0.0116 0.1305 0.9970 5.250 0.7426 0.00909 0.00323 -0.0133 0.1270 0.9990 5.500 0.7742 0.00928 0.00337 -0.0142 0.1229 1.0000 5.750 0.7992 0.00945 0.00353 -0.0137 0.1195 1.0000 6.000 0.8244 0.00960 0.00368 -0.0131 0.1178 1.0000 6.250 0.8496 0.00976 0.00384 -0.0126 0.1154 1.0000 6.500 0.8745 0.00994 0.00401 -0.0121 0.1122 1.0000 6.750 0.8993 0.01015 0.00419 -0.0115 0.1087 1.0000 7.000 0.9241 0.01035 0.00439 -0.0110 0.1063 1.0000 7.250 0.9492 0.01052 0.00458 -0.0105 0.1047 1.0000 7.500 0.9740 0.01072 0.00478 -0.0099 0.1023 1.0000 7.750 0.9986 0.01094 0.00499 -0.0094 0.0993 1.0000 8.000 1.0230 0.01119 0.00522 -0.0088 0.0962 1.0000 8.250 1.0475 0.01142 0.00547 -0.0083 0.0939 1.0000 8.500 1.0722 0.01163 0.00570 -0.0078 0.0922 1.0000 8.750 1.0965 0.01187 0.00595 -0.0072 0.0896 1.0000 9.000 1.1205 0.01214 0.00621 -0.0067 0.0867 1.0000 9.250 1.1441 0.01245 0.00651 -0.0061 0.0832 1.0000 9.500 1.1683 0.01270 0.00679 -0.0055 0.0815 1.0000 9.750 1.1923 0.01297 0.00707 -0.0050 0.0792 1.0000 10.000 1.2160 0.01327 0.00739 -0.0044 0.0766 1.0000 10.250 1.2392 0.01363 0.00773 -0.0039 0.0734 1.0000 10.500 1.2627 0.01395 0.00808 -0.0033 0.0712 1.0000 10.750 1.2863 0.01426 0.00842 -0.0028 0.0690 1.0000 11.000 1.3090 0.01466 0.00881 -0.0022 0.0654 1.0000 11.250 1.3313 0.01509 0.00923 -0.0016 0.0615 1.0000 11.500 1.3537 0.01549 0.00964 -0.0011 0.0579 1.0000 11.750 1.3749 0.01601 0.01014 -0.0004 0.0538 1.0000 12.000 1.3967 0.01645 0.01060 0.0002 0.0510 1.0000 12.250 1.4173 0.01698 0.01114 0.0009 0.0474 1.0000 12.500 1.4375 0.01753 0.01169 0.0017 0.0443 1.0000 12.750 1.4574 0.01809 0.01227 0.0025 0.0412 1.0000 13.000 1.4755 0.01877 0.01295 0.0034 0.0379 1.0000 13.250 1.4940 0.01937 0.01358 0.0043 0.0355 1.0000 13.500 1.5099 0.02012 0.01435 0.0054 0.0326 1.0000 13.750 1.5238 0.02084 0.01511 0.0068 0.0305 1.0000 14.000 1.5363 0.02168 0.01598 0.0082 0.0282 1.0000 14.250 1.5474 0.02270 0.01703 0.0095 0.0260 1.0000 14.500 1.5593 0.02372 0.01810 0.0105 0.0241 1.0000 14.750 1.5690 0.02498 0.01939 0.0114 0.0221 1.0000 15.000 1.5791 0.02624 0.02071 0.0122 0.0204 1.0000 15.250 1.5870 0.02775 0.02226 0.0130 0.0185 1.0000 15.500 1.5945 0.02931 0.02388 0.0136 0.0170 1.0000 15.750 1.6009 0.03102 0.02565 0.0142 0.0156 1.0000 16.000 1.6047 0.03300 0.02769 0.0147 0.0143 1.0000 16.250 1.6094 0.03493 0.02970 0.0151 0.0134 1.0000 16.500 1.6114 0.03717 0.03201 0.0153 0.0124 1.0000 17.000 1.6101 0.04238 0.03739 0.0154 0.0109 1.0000 17.250 1.6075 0.04532 0.04043 0.0152 0.0103 1.0000 17.500 1.6013 0.04875 0.04396 0.0147 0.0098 1.0000 17.750 1.5924 0.05266 0.04798 0.0139 0.0094 1.0000 18.000 1.5810 0.05710 0.05254 0.0126 0.0090 1.0000 18.250 1.5682 0.06205 0.05762 0.0109 0.0088 1.0000 18.500 1.5505 0.06802 0.06374 0.0084 0.0087 1.0000 18.750 1.5247 0.07568 0.07158 0.0048 0.0086 1.0000 19.000 1.4840 0.08660 0.08273 -0.0008 0.0088 1.0000