XFOIL Version 6.96 Calculated polar for: NASA RC(5)-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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5770 0.08293 0.08098 0.0024 0.8129 0.0159 -8.250 -0.5846 0.07681 0.07480 -0.0046 0.8044 0.0160 -8.000 -0.6827 0.03455 0.03136 -0.0170 0.8007 0.0143 -7.750 -0.6716 0.03037 0.02678 -0.0159 0.7947 0.0142 -7.500 -0.6646 0.02502 0.02085 -0.0141 0.7893 0.0141 -7.250 -0.6451 0.02283 0.01833 -0.0132 0.7840 0.0141 -6.500 -0.5835 0.01598 0.01046 -0.0102 0.7697 0.0146 -6.250 -0.5586 0.01501 0.00938 -0.0097 0.7649 0.0150 -6.000 -0.5325 0.01450 0.00880 -0.0094 0.7602 0.0154 -5.750 -0.5061 0.01394 0.00816 -0.0091 0.7557 0.0159 -5.500 -0.4797 0.01331 0.00745 -0.0087 0.7510 0.0162 -5.250 -0.4533 0.01275 0.00680 -0.0084 0.7466 0.0166 -5.000 -0.4267 0.01225 0.00621 -0.0080 0.7424 0.0170 -4.750 -0.3998 0.01178 0.00568 -0.0078 0.7381 0.0174 -4.500 -0.3728 0.01138 0.00523 -0.0075 0.7337 0.0177 -4.250 -0.3458 0.01104 0.00481 -0.0072 0.7294 0.0180 -4.000 -0.3204 0.01029 0.00400 -0.0066 0.7251 0.0188 -3.750 -0.2933 0.00995 0.00364 -0.0064 0.7206 0.0197 -3.500 -0.2659 0.00969 0.00336 -0.0062 0.7163 0.0206 -3.250 -0.2384 0.00950 0.00312 -0.0060 0.7122 0.0218 -3.000 -0.2109 0.00921 0.00282 -0.0058 0.7081 0.0231 -2.750 -0.1834 0.00894 0.00254 -0.0056 0.7037 0.0255 -2.500 -0.1556 0.00878 0.00235 -0.0055 0.6994 0.0279 -2.250 -0.1281 0.00854 0.00212 -0.0053 0.6945 0.0343 -2.000 -0.1004 0.00831 0.00194 -0.0051 0.6876 0.0448 -1.750 -0.0727 0.00816 0.00181 -0.0050 0.6805 0.0578 -1.500 -0.0446 0.00801 0.00171 -0.0050 0.6737 0.0708 -1.250 -0.0167 0.00791 0.00161 -0.0049 0.6672 0.0834 -1.000 0.0116 0.00779 0.00154 -0.0049 0.6609 0.0961 -0.750 0.0397 0.00770 0.00146 -0.0049 0.6542 0.1109 -0.500 0.0678 0.00758 0.00141 -0.0049 0.6483 0.1310 -0.250 0.0958 0.00744 0.00134 -0.0048 0.6410 0.1576 0.000 0.1194 0.00661 0.00119 -0.0043 0.6342 0.3951 0.250 0.1397 0.00563 0.00113 -0.0030 0.6273 0.6783 0.500 0.1588 0.00500 0.00112 -0.0009 0.6198 0.8531 0.750 0.1865 0.00488 0.00120 -0.0004 0.6109 0.9366 1.000 0.2243 0.00496 0.00127 -0.0023 0.6024 0.9620 1.250 0.2603 0.00506 0.00132 -0.0038 0.5933 0.9739 1.500 0.2974 0.00517 0.00138 -0.0057 0.5821 0.9818 1.750 0.3365 0.00528 0.00143 -0.0081 0.5694 0.9863 2.000 0.3754 0.00539 0.00147 -0.0104 0.5548 0.9903 2.250 0.4131 0.00553 0.00152 -0.0125 0.5334 0.9944 2.500 0.4513 0.00569 0.00155 -0.0149 0.4977 0.9964 2.750 0.4896 0.00620 0.00167 -0.0175 0.4048 0.9987 3.000 0.5243 0.00684 0.00190 -0.0196 0.3138 1.0000 3.250 0.5506 0.00717 0.00204 -0.0195 0.2741 1.0000 3.500 0.5766 0.00739 0.00215 -0.0193 0.2506 1.0000 3.750 0.6025 0.00758 0.00226 -0.0190 0.2339 1.0000 4.000 0.6282 0.00776 0.00237 -0.0187 0.2204 1.0000 4.250 0.6537 0.00793 0.00249 -0.0184 0.2086 1.0000 4.500 0.6791 0.00812 0.00263 -0.0180 0.1982 1.0000 4.750 0.7044 0.00827 0.00275 -0.0176 0.1906 1.0000 5.000 0.7296 0.00845 0.00289 -0.0172 0.1824 1.0000 5.250 0.7548 0.00861 0.00304 -0.0167 0.1753 1.0000 5.500 0.7797 0.00881 0.00320 -0.0162 0.1685 1.0000 5.750 0.8049 0.00896 0.00335 -0.0158 0.1630 1.0000 6.000 0.8295 0.00920 0.00354 -0.0153 0.1557 1.0000 6.250 0.8547 0.00935 0.00371 -0.0148 0.1517 1.0000 6.500 0.8795 0.00955 0.00389 -0.0144 0.1463 1.0000 6.750 0.9040 0.00979 0.00411 -0.0139 0.1401 1.0000 7.000 0.9290 0.00996 0.00430 -0.0134 0.1360 1.0000 7.250 0.9534 0.01020 0.00452 -0.0129 0.1301 1.0000 7.500 0.9780 0.01042 0.00475 -0.0124 0.1251 1.0000 7.750 1.0026 0.01064 0.00496 -0.0120 0.1204 1.0000 8.000 1.0264 0.01095 0.00525 -0.0114 0.1140 1.0000 8.250 1.0511 0.01114 0.00547 -0.0110 0.1104 1.0000 8.500 1.0751 0.01142 0.00573 -0.0104 0.1047 1.0000 8.750 1.0989 0.01172 0.00603 -0.0099 0.0994 1.0000 9.000 1.1227 0.01199 0.00630 -0.0094 0.0942 1.0000 9.250 1.1458 0.01234 0.00663 -0.0088 0.0873 1.0000 9.500 1.1692 0.01266 0.00693 -0.0083 0.0814 1.0000 9.750 1.1920 0.01304 0.00731 -0.0077 0.0753 1.0000 10.000 1.2148 0.01341 0.00767 -0.0071 0.0695 1.0000 10.250 1.2372 0.01384 0.00808 -0.0065 0.0637 1.0000 10.500 1.2593 0.01429 0.00852 -0.0059 0.0580 1.0000 10.750 1.2812 0.01475 0.00899 -0.0052 0.0526 1.0000 11.000 1.3018 0.01533 0.00953 -0.0045 0.0461 1.0000 11.250 1.3230 0.01585 0.01006 -0.0038 0.0411 1.0000 11.500 1.3428 0.01648 0.01067 -0.0031 0.0356 1.0000 11.750 1.3614 0.01719 0.01136 -0.0022 0.0304 1.0000 12.000 1.3806 0.01783 0.01202 -0.0014 0.0266 1.0000 12.250 1.3981 0.01859 0.01279 -0.0004 0.0229 1.0000 12.500 1.4138 0.01946 0.01366 0.0007 0.0193 1.0000 12.750 1.4298 0.02024 0.01448 0.0018 0.0168 1.0000 13.000 1.4407 0.02121 0.01548 0.0036 0.0146 1.0000 13.250 1.4517 0.02216 0.01648 0.0051 0.0132 1.0000 13.500 1.4585 0.02354 0.01792 0.0066 0.0116 1.0000 13.750 1.4698 0.02465 0.01911 0.0075 0.0110 1.0000 14.000 1.4794 0.02596 0.02050 0.0084 0.0103 1.0000 14.250 1.4866 0.02755 0.02215 0.0091 0.0096 1.0000 14.500 1.4880 0.02974 0.02444 0.0100 0.0089 1.0000 14.750 1.4954 0.03140 0.02619 0.0105 0.0086 1.0000 15.000 1.5017 0.03320 0.02809 0.0109 0.0083 1.0000 15.250 1.5060 0.03523 0.03021 0.0112 0.0080 1.0000 15.500 1.5086 0.03748 0.03256 0.0114 0.0078 1.0000 15.750 1.5088 0.04005 0.03522 0.0114 0.0075 1.0000 16.000 1.5064 0.04297 0.03824 0.0113 0.0073 1.0000 16.250 1.5005 0.04640 0.04178 0.0109 0.0072 1.0000 16.500 1.4909 0.05040 0.04591 0.0102 0.0070 1.0000 16.750 1.4773 0.05511 0.05075 0.0090 0.0069 1.0000 17.000 1.4612 0.06050 0.05629 0.0073 0.0068 1.0000 17.250 1.4421 0.06677 0.06272 0.0048 0.0067 1.0000 17.500 1.4203 0.07384 0.06994 0.0017 0.0067 1.0000 17.750 1.3962 0.08180 0.07806 -0.0021 0.0067 1.0000 18.000 1.3703 0.09040 0.08683 -0.0062 0.0067 1.0000 18.250 1.3426 0.09948 0.09606 -0.0105 0.0068 1.0000 18.500 1.3130 0.10886 0.10559 -0.0149 0.0069 1.0000 18.750 1.2825 0.11842 0.11529 -0.0194 0.0070 1.0000