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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5182 0.09022 0.08879 0.0027 1.0000 0.0101 -9.500 -0.5190 0.08644 0.08503 0.0006 1.0000 0.0102 -9.250 -0.5345 0.07877 0.07739 -0.0060 1.0000 0.0101 -9.000 -0.5345 0.07350 0.07189 -0.0127 0.8783 0.0102 -8.750 -0.5502 0.07100 0.06903 -0.0109 0.7887 0.0103 -8.500 -0.5665 0.06781 0.06568 -0.0088 0.7544 0.0103 -8.250 -0.5752 0.06422 0.06193 -0.0075 0.7293 0.0104 -8.000 -0.5784 0.06075 0.05832 -0.0063 0.7089 0.0104 -7.750 -0.5781 0.05745 0.05487 -0.0050 0.6900 0.0106 -7.500 -0.5741 0.05445 0.05171 -0.0036 0.6728 0.0108 -7.250 -0.5685 0.05135 0.04844 -0.0021 0.6572 0.0112 -7.000 -0.5633 0.04752 0.04442 -0.0001 0.6440 0.0114 -6.750 -0.5548 0.04034 0.03679 0.0038 0.6353 0.0131 -6.500 -0.6098 0.02079 0.01554 0.0175 0.6398 0.0101 -6.250 -0.5896 0.01936 0.01388 0.0188 0.6251 0.0103 -6.000 -0.5654 0.01919 0.01365 0.0194 0.6104 0.0107 -5.500 -0.5174 0.01801 0.01221 0.0210 0.5828 0.0116 -5.250 -0.4933 0.01679 0.01074 0.0220 0.5703 0.0122 -5.000 -0.4681 0.01591 0.00967 0.0228 0.5588 0.0127 -4.750 -0.4423 0.01547 0.00906 0.0235 0.5473 0.0130 -4.500 -0.4175 0.01385 0.00725 0.0242 0.5363 0.0138 -4.250 -0.3917 0.01343 0.00680 0.0247 0.5252 0.0144 -4.000 -0.3657 0.01303 0.00633 0.0252 0.5149 0.0151 -3.750 -0.3396 0.01271 0.00593 0.0256 0.5049 0.0160 -3.500 -0.3129 0.01249 0.00564 0.0261 0.4953 0.0168 -3.250 -0.2861 0.01233 0.00540 0.0265 0.4860 0.0173 -3.000 -0.2637 0.01126 0.00426 0.0277 0.4772 0.0182 -2.750 -0.2389 0.01086 0.00382 0.0284 0.4688 0.0190 -2.250 -0.1875 0.01039 0.00328 0.0296 0.4529 0.0212 -2.000 -0.1618 0.01019 0.00301 0.0302 0.4450 0.0219 -1.750 -0.1356 0.01000 0.00278 0.0307 0.4376 0.0225 -1.250 -0.0849 0.00950 0.00217 0.0321 0.4241 0.0256 -1.000 -0.0586 0.00939 0.00201 0.0325 0.4172 0.0277 -0.750 -0.0319 0.00929 0.00187 0.0329 0.4112 0.0293 -0.500 -0.0058 0.00914 0.00174 0.0334 0.4047 0.0407 -0.250 0.0159 0.00862 0.00164 0.0346 0.3994 0.1759 0.000 0.0115 0.00661 0.00136 0.0407 0.3961 0.6811 0.250 0.0462 0.00597 0.00156 0.0398 0.3900 0.9200 0.500 0.0939 0.00627 0.00181 0.0358 0.3835 0.9398 0.750 0.1306 0.00657 0.00205 0.0343 0.3779 0.9481 1.000 0.1671 0.00707 0.00247 0.0330 0.3723 0.9584 1.250 0.2316 0.00758 0.00291 0.0255 0.3661 0.9610 1.500 0.2719 0.00776 0.00303 0.0230 0.3605 0.9627 1.750 0.3042 0.00786 0.00307 0.0220 0.3555 0.9640 2.000 0.3355 0.00791 0.00309 0.0213 0.3519 0.9657 2.250 0.3641 0.00798 0.00313 0.0211 0.3476 0.9680 2.500 0.3857 0.00810 0.00320 0.0225 0.3432 0.9717 2.750 0.4193 0.00813 0.00321 0.0212 0.3391 0.9723 3.000 0.4526 0.00816 0.00323 0.0200 0.3352 0.9729 3.250 0.4854 0.00822 0.00325 0.0188 0.3310 0.9737 3.500 0.5177 0.00832 0.00331 0.0178 0.3264 0.9746 3.750 0.5500 0.00834 0.00334 0.0168 0.3231 0.9756 4.000 0.5814 0.00839 0.00338 0.0159 0.3189 0.9767 4.250 0.6118 0.00848 0.00345 0.0152 0.3148 0.9782 4.500 0.6412 0.00858 0.00354 0.0148 0.3110 0.9799 4.750 0.6673 0.00867 0.00364 0.0151 0.3076 0.9823 5.000 0.6947 0.00876 0.00373 0.0151 0.3036 0.9840 5.250 0.7274 0.00883 0.00377 0.0138 0.2984 0.9846 5.500 0.7601 0.00884 0.00381 0.0127 0.2943 0.9852 5.750 0.7921 0.00888 0.00386 0.0116 0.2895 0.9860 6.000 0.8233 0.00899 0.00394 0.0107 0.2840 0.9869 6.250 0.8548 0.00903 0.00401 0.0097 0.2802 0.9880 6.500 0.8856 0.00910 0.00409 0.0089 0.2749 0.9891 6.750 0.9152 0.00925 0.00422 0.0082 0.2692 0.9904 7.000 0.9446 0.00930 0.00432 0.0077 0.2651 0.9917 7.250 0.9732 0.00943 0.00445 0.0073 0.2595 0.9931 7.500 1.0024 0.00958 0.00461 0.0068 0.2538 0.9943 7.750 1.0342 0.00962 0.00469 0.0056 0.2480 0.9950 8.000 1.0648 0.00978 0.00483 0.0047 0.2404 0.9959 8.250 1.0954 0.00986 0.00495 0.0038 0.2344 0.9968 8.500 1.1251 0.01004 0.00513 0.0030 0.2258 0.9978 8.750 1.1553 0.01021 0.00530 0.0021 0.2163 0.9988 9.000 1.1853 0.01045 0.00551 0.0012 0.2034 0.9997 9.250 1.2102 0.01077 0.00580 0.0013 0.1893 1.0000 9.500 1.2312 0.01121 0.00616 0.0021 0.1713 1.0000 9.750 1.2515 0.01172 0.00659 0.0030 0.1509 1.0000 10.000 1.2701 0.01237 0.00714 0.0040 0.1302 1.0000 10.250 1.2881 0.01305 0.00773 0.0051 0.1115 1.0000 10.500 1.3048 0.01379 0.00839 0.0064 0.0944 1.0000 10.750 1.3216 0.01446 0.00901 0.0077 0.0815 1.0000 11.000 1.3374 0.01516 0.00967 0.0092 0.0700 1.0000 11.250 1.3524 0.01587 0.01035 0.0107 0.0604 1.0000 11.500 1.3663 0.01661 0.01107 0.0124 0.0517 1.0000 11.750 1.3788 0.01738 0.01182 0.0143 0.0440 1.0000 12.000 1.3893 0.01821 0.01266 0.0164 0.0374 1.0000 12.250 1.3960 0.01919 0.01362 0.0189 0.0310 1.0000 12.500 1.4023 0.02009 0.01454 0.0215 0.0265 1.0000 12.750 1.4014 0.02121 0.01567 0.0250 0.0218 1.0000 13.000 1.3829 0.02241 0.01691 0.0310 0.0190 1.0000 13.250 1.3726 0.02419 0.01877 0.0337 0.0172 1.0000 13.500 1.3620 0.02687 0.02151 0.0348 0.0145 1.0000 13.750 1.3475 0.03052 0.02521 0.0349 0.0107 1.0000 14.000 1.3393 0.03382 0.02860 0.0347 0.0095 1.0000 14.250 1.3212 0.03831 0.03315 0.0342 0.0073 1.0000 14.500 1.3138 0.04169 0.03662 0.0338 0.0073 1.0000 14.750 1.2995 0.04587 0.04089 0.0331 0.0064 1.0000 15.000 1.2911 0.04944 0.04456 0.0326 0.0065 1.0000 15.250 1.2710 0.05445 0.04964 0.0316 0.0057 1.0000 15.500 1.2638 0.05799 0.05327 0.0309 0.0059 1.0000 15.750 1.2431 0.06341 0.05878 0.0295 0.0053 1.0000 16.000 1.2346 0.06743 0.06289 0.0284 0.0052 1.0000 16.250 1.2251 0.07167 0.06721 0.0272 0.0049 1.0000 16.500 1.2156 0.07599 0.07162 0.0260 0.0050 1.0000 16.750 1.2031 0.08084 0.07656 0.0245 0.0047 1.0000 17.000 1.1958 0.08497 0.08078 0.0232 0.0046 1.0000 17.250 1.1878 0.08927 0.08515 0.0218 0.0047 1.0000 17.500 1.1784 0.09388 0.08984 0.0202 0.0044 1.0000 17.750 1.1661 0.09899 0.09503 0.0184 0.0043 1.0000 18.000 1.1589 0.10334 0.09945 0.0169 0.0043 1.0000 18.250 1.1514 0.10783 0.10402 0.0153 0.0043 1.0000 18.500 1.1434 0.11247 0.10874 0.0135 0.0043 1.0000 18.750 1.1282 0.11835 0.11470 0.0112 0.0041 1.0000