XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY RC-10(N)1 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.6045 0.09881 0.09737 0.0123 1.0000 0.0101 -9.250 -0.6051 0.09349 0.09207 0.0088 1.0000 0.0101 -9.000 -0.6067 0.08762 0.08623 0.0042 1.0000 0.0101 -6.750 -0.6023 0.04420 0.04124 -0.0103 0.7927 0.0114 -6.500 -0.5861 0.04124 0.03809 -0.0098 0.7872 0.0119 -6.250 -0.5684 0.03789 0.03451 -0.0088 0.7825 0.0129 -6.000 -0.5416 0.03551 0.03183 -0.0072 0.7777 0.0141 -5.000 -0.4712 0.01957 0.01431 -0.0009 0.7601 0.0145 -4.750 -0.4474 0.01723 0.01177 -0.0001 0.7559 0.0135 -4.500 -0.4217 0.01564 0.00997 0.0005 0.7517 0.0136 -4.250 -0.3939 0.01572 0.00996 0.0006 0.7472 0.0142 -4.000 -0.3686 0.01386 0.00789 0.0013 0.7431 0.0143 -3.750 -0.3452 0.01180 0.00567 0.0022 0.7391 0.0149 -3.500 -0.3195 0.01108 0.00492 0.0026 0.7347 0.0155 -3.250 -0.2932 0.01061 0.00441 0.0029 0.7303 0.0160 -3.000 -0.2669 0.01019 0.00393 0.0032 0.7262 0.0165 -2.750 -0.2402 0.00978 0.00349 0.0035 0.7218 0.0171 -2.500 -0.2131 0.00948 0.00316 0.0036 0.7172 0.0181 -2.250 -0.1860 0.00923 0.00285 0.0038 0.7129 0.0191 -2.000 -0.1590 0.00888 0.00246 0.0040 0.7084 0.0201 -1.750 -0.1320 0.00852 0.00205 0.0042 0.7035 0.0229 -1.500 -0.1043 0.00837 0.00186 0.0042 0.6988 0.0258 -1.250 -0.0766 0.00815 0.00164 0.0043 0.6939 0.0329 -1.000 -0.0490 0.00793 0.00149 0.0043 0.6886 0.0553 -0.750 -0.0328 0.00604 0.00115 0.0057 0.6836 0.5350 -0.500 -0.0084 0.00559 0.00112 0.0064 0.6780 0.6582 -0.250 0.0175 0.00537 0.00106 0.0068 0.6723 0.7137 0.000 0.0387 0.00488 0.00103 0.0084 0.6670 0.8307 0.250 0.0634 0.00471 0.00110 0.0095 0.6609 0.9170 0.500 0.0941 0.00475 0.00114 0.0091 0.6550 0.9478 0.750 0.1292 0.00485 0.00125 0.0078 0.6488 0.9700 1.000 0.1649 0.00493 0.00128 0.0061 0.6425 0.9744 1.250 0.2000 0.00499 0.00131 0.0045 0.6361 0.9777 1.500 0.2324 0.00505 0.00134 0.0035 0.6291 0.9820 1.750 0.2667 0.00511 0.00137 0.0020 0.6220 0.9846 2.000 0.3026 0.00517 0.00139 0.0001 0.6133 0.9865 2.250 0.3375 0.00523 0.00140 -0.0015 0.5984 0.9887 2.500 0.3714 0.00530 0.00143 -0.0029 0.5843 0.9912 2.750 0.4042 0.00538 0.00148 -0.0041 0.5708 0.9937 3.250 0.4738 0.00554 0.00156 -0.0074 0.5389 0.9966 3.500 0.5086 0.00565 0.00161 -0.0092 0.5158 0.9983 3.750 0.5432 0.00580 0.00168 -0.0108 0.4886 0.9997 4.000 0.5719 0.00605 0.00177 -0.0113 0.4429 1.0000 4.250 0.5985 0.00641 0.00192 -0.0115 0.3882 1.0000 4.500 0.6245 0.00678 0.00210 -0.0115 0.3392 1.0000 4.750 0.6499 0.00723 0.00231 -0.0114 0.2840 1.0000 5.000 0.6746 0.00774 0.00257 -0.0113 0.2251 1.0000 5.250 0.6985 0.00828 0.00287 -0.0110 0.1691 1.0000 5.500 0.7221 0.00877 0.00317 -0.0106 0.1279 1.0000 5.750 0.7458 0.00916 0.00344 -0.0102 0.1024 1.0000 6.000 0.7695 0.00951 0.00371 -0.0097 0.0836 1.0000 6.250 0.7931 0.00985 0.00399 -0.0091 0.0694 1.0000 6.500 0.8166 0.01018 0.00428 -0.0085 0.0578 1.0000 6.750 0.8400 0.01051 0.00458 -0.0080 0.0484 1.0000 7.000 0.8631 0.01089 0.00492 -0.0073 0.0404 1.0000 7.250 0.8864 0.01122 0.00526 -0.0067 0.0356 1.0000 7.500 0.9091 0.01164 0.00568 -0.0060 0.0305 1.0000 7.750 0.9324 0.01196 0.00601 -0.0054 0.0274 1.0000 8.000 0.9535 0.01259 0.00665 -0.0045 0.0229 1.0000 8.250 0.9770 0.01286 0.00696 -0.0039 0.0217 1.0000 8.500 0.9997 0.01322 0.00735 -0.0033 0.0198 1.0000 8.750 1.0201 0.01387 0.00801 -0.0023 0.0172 1.0000 9.000 1.0413 0.01440 0.00860 -0.0014 0.0161 1.0000 9.250 1.0635 0.01479 0.00903 -0.0007 0.0151 1.0000 9.500 1.0853 0.01522 0.00949 0.0000 0.0139 1.0000 9.750 1.1049 0.01589 0.01020 0.0009 0.0126 1.0000 10.000 1.1226 0.01678 0.01117 0.0021 0.0116 1.0000 10.250 1.1439 0.01725 0.01171 0.0028 0.0111 1.0000 10.500 1.1644 0.01782 0.01233 0.0035 0.0104 1.0000 10.750 1.1844 0.01841 0.01297 0.0043 0.0097 1.0000 11.000 1.2026 0.01917 0.01377 0.0052 0.0091 1.0000 11.250 1.2095 0.02099 0.01574 0.0073 0.0082 1.0000 11.500 1.2285 0.02157 0.01640 0.0081 0.0080 1.0000 11.750 1.2457 0.02228 0.01719 0.0090 0.0077 1.0000 12.000 1.2602 0.02305 0.01804 0.0103 0.0073 1.0000 12.250 1.2723 0.02389 0.01895 0.0117 0.0069 1.0000 12.500 1.2840 0.02486 0.01999 0.0128 0.0066 1.0000 12.750 1.2942 0.02606 0.02126 0.0138 0.0063 1.0000 13.000 1.2999 0.02775 0.02304 0.0147 0.0060 1.0000 13.250 1.2962 0.03045 0.02590 0.0158 0.0058 1.0000 13.500 1.2893 0.03362 0.02926 0.0167 0.0056 1.0000 13.750 1.2962 0.03545 0.03121 0.0169 0.0055 1.0000 14.000 1.3003 0.03761 0.03348 0.0171 0.0054 1.0000 14.250 1.3026 0.04004 0.03605 0.0171 0.0053 1.0000 14.500 1.3023 0.04280 0.03894 0.0169 0.0052 1.0000 14.750 1.2995 0.04597 0.04224 0.0165 0.0051 1.0000 15.000 1.2946 0.04949 0.04590 0.0159 0.0050 1.0000 15.250 1.2878 0.05340 0.04995 0.0149 0.0049 1.0000 15.500 1.2789 0.05775 0.05444 0.0135 0.0048 1.0000 15.750 1.2677 0.06266 0.05949 0.0117 0.0048 1.0000 16.000 1.2546 0.06824 0.06522 0.0093 0.0048 1.0000 16.250 1.2394 0.07449 0.07162 0.0063 0.0047 1.0000 16.500 1.2215 0.08158 0.07885 0.0028 0.0047 1.0000 16.750 1.2012 0.08937 0.08680 -0.0012 0.0047 1.0000 17.000 1.1777 0.09815 0.09572 -0.0057 0.0048 1.0000 17.250 1.1500 0.10801 0.10573 -0.0108 0.0048 1.0000 17.500 1.1205 0.11862 0.11649 -0.0162 0.0049 1.0000 17.750 1.0884 0.13016 0.12816 -0.0220 0.0050 1.0000 18.000 1.0533 0.14300 0.14113 -0.0286 0.0051 1.0000 18.250 1.0057 0.15998 0.15825 -0.0373 0.0053 1.0000