XFOIL Version 6.96 Calculated polar for: EPPLER 635 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -1.0218 0.03068 0.02764 0.0001 1.0000 0.0045 -11.000 -1.0238 0.02682 0.02336 0.0037 1.0000 0.0047 -10.750 -1.0106 0.02512 0.02148 0.0057 1.0000 0.0048 -10.500 -0.9959 0.02356 0.01973 0.0075 1.0000 0.0049 -10.250 -0.9711 0.02265 0.01839 0.0077 0.8405 0.0050 -10.000 -0.9527 0.02203 0.01752 0.0094 0.7918 0.0052 -9.750 -0.9340 0.02113 0.01639 0.0109 0.7575 0.0052 -9.500 -0.9128 0.02053 0.01562 0.0120 0.7299 0.0054 -9.250 -0.8914 0.01986 0.01476 0.0131 0.7059 0.0056 -9.000 -0.8703 0.01904 0.01375 0.0143 0.6852 0.0058 -8.750 -0.8484 0.01829 0.01281 0.0154 0.6669 0.0059 -8.500 -0.8257 0.01762 0.01198 0.0163 0.6487 0.0062 -8.250 -0.8029 0.01693 0.01112 0.0173 0.6326 0.0064 -8.000 -0.7794 0.01634 0.01038 0.0182 0.6181 0.0065 -7.750 -0.7558 0.01576 0.00966 0.0190 0.6036 0.0067 -7.500 -0.7312 0.01537 0.00918 0.0197 0.5894 0.0071 -7.250 -0.7056 0.01520 0.00897 0.0202 0.5768 0.0074 -7.000 -0.6801 0.01496 0.00865 0.0207 0.5645 0.0076 -6.750 -0.6546 0.01471 0.00832 0.0213 0.5519 0.0080 -6.500 -0.6295 0.01434 0.00786 0.0219 0.5401 0.0083 -6.250 -0.6041 0.01399 0.00742 0.0225 0.5293 0.0087 -6.000 -0.5789 0.01363 0.00696 0.0231 0.5196 0.0090 -5.750 -0.5534 0.01329 0.00652 0.0237 0.5097 0.0093 -5.500 -0.5285 0.01288 0.00603 0.0244 0.4999 0.0098 -5.250 -0.5025 0.01267 0.00577 0.0248 0.4898 0.0101 -5.000 -0.4760 0.01252 0.00560 0.0252 0.4811 0.0105 -4.750 -0.4498 0.01235 0.00537 0.0256 0.4731 0.0111 -4.500 -0.4236 0.01215 0.00511 0.0261 0.4644 0.0117 -4.250 -0.3976 0.01191 0.00481 0.0266 0.4561 0.0122 -4.000 -0.3716 0.01170 0.00453 0.0271 0.4474 0.0126 -3.750 -0.3451 0.01154 0.00432 0.0275 0.4407 0.0128 -3.500 -0.3209 0.01109 0.00381 0.0283 0.4336 0.0136 -3.250 -0.2949 0.01089 0.00359 0.0288 0.4269 0.0142 -3.000 -0.2687 0.01072 0.00337 0.0293 0.4194 0.0147 -2.750 -0.2427 0.01053 0.00315 0.0297 0.4129 0.0154 -2.500 -0.2165 0.01035 0.00292 0.0302 0.4069 0.0159 -2.000 -0.1637 0.01009 0.00258 0.0311 0.3956 0.0170 -1.750 -0.1374 0.00995 0.00239 0.0315 0.3891 0.0175 -1.500 -0.1114 0.00977 0.00217 0.0320 0.3839 0.0183 -1.250 -0.0849 0.00964 0.00202 0.0324 0.3791 0.0191 -1.000 -0.0584 0.00954 0.00189 0.0328 0.3738 0.0200 -0.750 -0.0316 0.00947 0.00179 0.0331 0.3688 0.0210 -0.500 -0.0047 0.00940 0.00170 0.0334 0.3639 0.0223 -0.250 0.0222 0.00934 0.00162 0.0337 0.3592 0.0253 0.000 0.0483 0.00922 0.00156 0.0341 0.3551 0.0466 0.250 0.0738 0.00902 0.00151 0.0347 0.3510 0.0985 0.500 0.0986 0.00879 0.00146 0.0353 0.3463 0.1709 0.750 0.0880 0.00660 0.00120 0.0428 0.3437 0.7486 1.000 0.1138 0.00617 0.00131 0.0436 0.3402 0.8987 1.250 0.1793 0.00642 0.00159 0.0356 0.3345 0.9362 1.500 0.2110 0.00666 0.00179 0.0351 0.3298 0.9476 1.750 0.2454 0.00683 0.00191 0.0338 0.3259 0.9499 2.000 0.2788 0.00699 0.00204 0.0327 0.3224 0.9535 2.250 0.2975 0.00707 0.00209 0.0348 0.3191 0.9589 2.500 0.3296 0.00716 0.00213 0.0339 0.3149 0.9594 2.750 0.3615 0.00724 0.00219 0.0330 0.3111 0.9600 3.000 0.3932 0.00732 0.00224 0.0321 0.3075 0.9606 3.250 0.4245 0.00740 0.00230 0.0314 0.3038 0.9613 3.500 0.4555 0.00750 0.00237 0.0306 0.3002 0.9622 3.750 0.4861 0.00759 0.00244 0.0300 0.2969 0.9631 4.000 0.5162 0.00767 0.00251 0.0294 0.2934 0.9642 4.250 0.5455 0.00776 0.00259 0.0291 0.2894 0.9655 4.500 0.5736 0.00787 0.00268 0.0289 0.2857 0.9672 4.750 0.5907 0.00798 0.00280 0.0313 0.2829 0.9716 5.000 0.6223 0.00806 0.00288 0.0303 0.2796 0.9720 5.250 0.6537 0.00816 0.00297 0.0294 0.2751 0.9725 5.500 0.6845 0.00829 0.00308 0.0286 0.2699 0.9730 5.750 0.7153 0.00838 0.00318 0.0279 0.2653 0.9736 6.000 0.7454 0.00850 0.00329 0.0272 0.2597 0.9742 6.250 0.7754 0.00864 0.00342 0.0265 0.2545 0.9750 6.500 0.8053 0.00875 0.00355 0.0259 0.2494 0.9759 6.750 0.8344 0.00891 0.00370 0.0254 0.2433 0.9769 7.000 0.8629 0.00905 0.00385 0.0250 0.2381 0.9780 7.250 0.8906 0.00921 0.00401 0.0248 0.2319 0.9793 7.500 0.9169 0.00940 0.00420 0.0249 0.2257 0.9809 7.750 0.9391 0.00959 0.00440 0.0259 0.2193 0.9831 8.000 0.9663 0.00980 0.00461 0.0257 0.2124 0.9840 8.250 0.9960 0.01003 0.00481 0.0249 0.2020 0.9844 8.500 1.0257 0.01026 0.00504 0.0241 0.1926 0.9850 8.750 1.0547 0.01055 0.00532 0.0234 0.1817 0.9856 9.000 1.0819 0.01103 0.00570 0.0228 0.1609 0.9864 9.250 1.1068 0.01173 0.00625 0.0225 0.1324 0.9873 9.500 1.1320 0.01236 0.00678 0.0222 0.1119 0.9884 9.750 1.1568 0.01300 0.00735 0.0219 0.0954 0.9897 10.000 1.1808 0.01363 0.00791 0.0218 0.0808 0.9910 10.250 1.2030 0.01432 0.00854 0.0220 0.0664 0.9924 10.500 1.2243 0.01496 0.00916 0.0224 0.0562 0.9937 10.750 1.2484 0.01563 0.00980 0.0220 0.0477 0.9946 11.000 1.2728 0.01641 0.01055 0.0214 0.0376 0.9955 11.250 1.2942 0.01742 0.01150 0.0211 0.0263 0.9966 11.500 1.3163 0.01821 0.01229 0.0208 0.0214 0.9977 11.750 1.3360 0.01929 0.01336 0.0205 0.0148 0.9990 12.000 1.3548 0.02038 0.01446 0.0203 0.0105 1.0000 12.250 1.3559 0.02147 0.01559 0.0235 0.0074 1.0000 12.750 1.3301 0.02417 0.01844 0.0324 0.0051 1.0000 13.000 1.3234 0.02640 0.02075 0.0336 0.0045 1.0000 13.250 1.3146 0.02938 0.02381 0.0340 0.0035 1.0000 13.500 1.3139 0.03180 0.02632 0.0340 0.0036 1.0000 13.750 1.3083 0.03486 0.02946 0.0339 0.0034 1.0000 14.000 1.3010 0.03817 0.03287 0.0336 0.0032 1.0000 14.250 1.2925 0.04167 0.03645 0.0332 0.0030 1.0000 14.500 1.2784 0.04586 0.04074 0.0325 0.0026 1.0000 14.750 1.2698 0.04946 0.04442 0.0320 0.0026 1.0000 15.000 1.2607 0.05316 0.04821 0.0314 0.0026 1.0000 15.250 1.2500 0.05710 0.05224 0.0306 0.0025 1.0000 15.500 1.2401 0.06109 0.05632 0.0297 0.0024 1.0000 15.750 1.2303 0.06520 0.06051 0.0287 0.0024 1.0000 16.000 1.2223 0.06921 0.06459 0.0276 0.0024 1.0000 16.250 1.2147 0.07320 0.06866 0.0265 0.0023 1.0000 16.500 1.2039 0.07773 0.07328 0.0251 0.0022 1.0000 16.750 1.1964 0.08187 0.07750 0.0238 0.0021 1.0000 17.000 1.1892 0.08603 0.08173 0.0226 0.0022 1.0000 17.250 1.1823 0.09017 0.08596 0.0212 0.0021 1.0000 17.500 1.1728 0.09479 0.09066 0.0197 0.0020 1.0000