XFOIL Version 6.96 Calculated polar for: EPPLER 637 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3590 0.09124 0.08828 -0.0236 0.6014 0.0052 -9.250 -0.3588 0.08766 0.08467 -0.0252 0.5900 0.0053 -9.000 -0.3581 0.08373 0.08073 -0.0270 0.5805 0.0051 -8.750 -0.3525 0.08207 0.07905 -0.0279 0.5725 0.0055 -8.500 -0.3603 0.07729 0.07427 -0.0306 0.5645 0.0054 -8.250 -0.3649 0.07389 0.07088 -0.0332 0.5578 0.0055 -8.000 -0.3954 0.06772 0.06470 -0.0348 0.5549 0.0054 -7.750 -0.4004 0.06409 0.06102 -0.0353 0.5483 0.0054 -7.500 -0.4070 0.05912 0.05595 -0.0356 0.5433 0.0054 -7.250 -0.4003 0.05651 0.05327 -0.0354 0.5358 0.0055 -7.000 -0.3904 0.05432 0.05099 -0.0351 0.5280 0.0057 -6.750 -0.3877 0.04979 0.04631 -0.0343 0.5227 0.0057 -6.500 -0.3800 0.04608 0.04245 -0.0332 0.5161 0.0057 -6.250 -0.3707 0.04242 0.03860 -0.0318 0.5092 0.0058 -6.000 -0.3612 0.03834 0.03431 -0.0299 0.5033 0.0058 -5.500 -0.3429 0.02865 0.02396 -0.0242 0.4922 0.0058 -5.250 -0.3441 0.01920 0.01359 -0.0180 0.4895 0.0059 -5.000 -0.3257 0.01625 0.01013 -0.0158 0.4826 0.0059 -4.750 -0.3020 0.01501 0.00864 -0.0148 0.4762 0.0061 -4.500 -0.2772 0.01412 0.00756 -0.0141 0.4691 0.0061 -4.250 -0.2520 0.01343 0.00673 -0.0134 0.4622 0.0064 -4.000 -0.2267 0.01280 0.00596 -0.0127 0.4549 0.0066 -3.750 -0.2011 0.01235 0.00540 -0.0121 0.4481 0.0068 -3.500 -0.1753 0.01194 0.00490 -0.0116 0.4417 0.0070 -3.250 -0.1493 0.01164 0.00452 -0.0110 0.4355 0.0072 -3.000 -0.1232 0.01137 0.00418 -0.0106 0.4302 0.0073 -2.750 -0.0985 0.01090 0.00365 -0.0098 0.4243 0.0076 -2.500 -0.0729 0.01065 0.00334 -0.0092 0.4182 0.0079 -2.250 -0.0469 0.01041 0.00307 -0.0088 0.4131 0.0082 -2.000 -0.0207 0.01023 0.00285 -0.0083 0.4077 0.0085 -1.750 0.0056 0.01008 0.00266 -0.0079 0.4027 0.0089 -1.500 0.0322 0.00994 0.00249 -0.0075 0.3985 0.0094 -1.250 0.0587 0.00981 0.00233 -0.0071 0.3933 0.0098 -1.000 0.0848 0.00965 0.00212 -0.0066 0.3881 0.0103 -0.750 0.1113 0.00952 0.00197 -0.0062 0.3843 0.0111 -0.500 0.1382 0.00943 0.00186 -0.0059 0.3805 0.0121 -0.250 0.1650 0.00936 0.00176 -0.0056 0.3762 0.0133 0.000 0.1917 0.00930 0.00168 -0.0053 0.3719 0.0156 0.250 0.2181 0.00917 0.00162 -0.0049 0.3682 0.0351 0.500 0.2441 0.00902 0.00158 -0.0045 0.3646 0.0758 0.750 0.2695 0.00884 0.00156 -0.0040 0.3610 0.1418 1.000 0.2668 0.00686 0.00143 0.0017 0.3585 0.7423 1.250 0.2951 0.00647 0.00163 0.0022 0.3550 0.9242 1.500 0.3394 0.00669 0.00184 -0.0011 0.3511 0.9508 1.750 0.3682 0.00687 0.00197 -0.0010 0.3476 0.9614 2.000 0.4085 0.00703 0.00207 -0.0037 0.3438 0.9636 2.250 0.4404 0.00713 0.00211 -0.0045 0.3403 0.9647 2.500 0.4716 0.00719 0.00215 -0.0052 0.3375 0.9660 2.750 0.5019 0.00727 0.00219 -0.0058 0.3340 0.9676 3.000 0.5305 0.00735 0.00224 -0.0059 0.3309 0.9697 3.250 0.5527 0.00745 0.00231 -0.0047 0.3279 0.9736 3.500 0.5848 0.00754 0.00237 -0.0057 0.3248 0.9741 3.750 0.6168 0.00760 0.00242 -0.0066 0.3217 0.9748 4.000 0.6484 0.00768 0.00248 -0.0075 0.3187 0.9755 4.250 0.6796 0.00777 0.00255 -0.0083 0.3156 0.9764 4.500 0.7102 0.00788 0.00264 -0.0090 0.3122 0.9774 4.750 0.7404 0.00797 0.00272 -0.0096 0.3091 0.9786 5.000 0.7702 0.00805 0.00280 -0.0102 0.3063 0.9799 5.250 0.7989 0.00815 0.00290 -0.0105 0.3031 0.9815 5.500 0.8251 0.00827 0.00301 -0.0102 0.2995 0.9835 5.750 0.8522 0.00840 0.00313 -0.0102 0.2960 0.9851 6.000 0.8837 0.00848 0.00323 -0.0112 0.2933 0.9856 6.250 0.9148 0.00858 0.00333 -0.0120 0.2890 0.9863 6.500 0.9451 0.00871 0.00345 -0.0128 0.2844 0.9870 6.750 0.9752 0.00884 0.00358 -0.0135 0.2798 0.9878 7.000 1.0052 0.00896 0.00371 -0.0142 0.2738 0.9887 7.250 1.0345 0.00914 0.00387 -0.0148 0.2678 0.9898 7.500 1.0636 0.00926 0.00402 -0.0153 0.2630 0.9908 7.750 1.0919 0.00942 0.00418 -0.0157 0.2575 0.9919 8.000 1.1198 0.00961 0.00437 -0.0160 0.2519 0.9931 8.250 1.1471 0.00979 0.00457 -0.0162 0.2454 0.9943 8.500 1.1760 0.01002 0.00478 -0.0168 0.2376 0.9950 8.750 1.2046 0.01027 0.00501 -0.0174 0.2275 0.9957 9.000 1.2332 0.01051 0.00525 -0.0180 0.2181 0.9965 9.250 1.2609 0.01089 0.00557 -0.0185 0.2033 0.9975 9.500 1.2871 0.01139 0.00598 -0.0189 0.1846 0.9985 9.750 1.3121 0.01198 0.00648 -0.0191 0.1624 0.9995 10.000 1.3333 0.01259 0.00700 -0.0186 0.1446 1.0000 10.250 1.3481 0.01320 0.00754 -0.0167 0.1281 1.0000 10.500 1.3608 0.01390 0.00816 -0.0145 0.1115 1.0000 10.750 1.3725 0.01461 0.00879 -0.0121 0.0968 1.0000 11.000 1.3834 0.01530 0.00943 -0.0096 0.0837 1.0000 11.250 1.3939 0.01597 0.01007 -0.0071 0.0738 1.0000 11.500 1.4025 0.01666 0.01073 -0.0043 0.0646 1.0000 11.750 1.4097 0.01736 0.01142 -0.0013 0.0567 1.0000 12.000 1.4149 0.01803 0.01210 0.0020 0.0514 1.0000 12.250 1.4099 0.01875 0.01283 0.0070 0.0464 1.0000 12.500 1.4102 0.01955 0.01365 0.0107 0.0424 1.0000 12.750 1.4092 0.02067 0.01481 0.0137 0.0385 1.0000 13.000 1.4078 0.02218 0.01634 0.0159 0.0335 1.0000 13.250 1.4075 0.02399 0.01820 0.0172 0.0301 1.0000 13.500 1.4044 0.02637 0.02061 0.0179 0.0258 1.0000 13.750 1.4055 0.02861 0.02293 0.0181 0.0236 1.0000 14.000 1.4028 0.03139 0.02576 0.0181 0.0213 1.0000 14.250 1.3964 0.03466 0.02909 0.0178 0.0178 1.0000 14.500 1.3896 0.03803 0.03252 0.0175 0.0157 1.0000 14.750 1.3789 0.04189 0.03645 0.0170 0.0134 1.0000 15.000 1.3748 0.04504 0.03969 0.0166 0.0131 1.0000 15.500 1.3507 0.05326 0.04804 0.0153 0.0099 1.0000 15.750 1.3415 0.05714 0.05201 0.0146 0.0093 1.0000 16.000 1.3342 0.06095 0.05589 0.0138 0.0090 1.0000 16.250 1.3248 0.06508 0.06010 0.0128 0.0085 1.0000 16.500 1.3176 0.06901 0.06410 0.0118 0.0081 1.0000 16.750 1.3107 0.07298 0.06815 0.0108 0.0078 1.0000 17.000 1.3035 0.07701 0.07226 0.0097 0.0076 1.0000 17.250 1.2947 0.08132 0.07664 0.0085 0.0071 1.0000 17.500 1.2902 0.08507 0.08047 0.0074 0.0071 1.0000 17.750 1.2819 0.08943 0.08490 0.0061 0.0068 1.0000 18.000 1.2731 0.09389 0.08944 0.0047 0.0064 1.0000