XFOIL Version 6.96 Calculated polar for: LWK 80-100 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.6531 0.08752 0.08408 -0.0210 1.0000 0.0579 -10.000 -0.6732 0.07911 0.07568 -0.0286 1.0000 0.0576 -9.750 -0.6939 0.07334 0.06985 -0.0320 1.0000 0.0580 -9.500 -0.7153 0.06881 0.06525 -0.0329 1.0000 0.0581 -9.250 -0.7075 0.04239 0.03846 -0.0340 1.0000 0.0399 -9.000 -0.7211 0.03720 0.03315 -0.0317 1.0000 0.0382 -8.750 -0.8180 0.04242 0.03702 -0.0215 1.0000 0.0315 -8.500 -0.8068 0.04054 0.03482 -0.0192 1.0000 0.0308 -8.250 -0.7973 0.03744 0.03141 -0.0170 1.0000 0.0304 -8.000 -0.7908 0.03400 0.02756 -0.0142 1.0000 0.0307 -7.750 -0.7827 0.02967 0.02281 -0.0118 1.0000 0.0314 -7.500 -0.7678 0.02792 0.02101 -0.0104 1.0000 0.0338 -7.250 -0.7517 0.02628 0.01919 -0.0085 1.0000 0.0352 -7.000 -0.7363 0.02456 0.01726 -0.0063 1.0000 0.0368 -6.750 -0.7243 0.02317 0.01566 -0.0034 1.0000 0.0386 -6.500 -0.7146 0.02223 0.01451 -0.0001 1.0000 0.0403 -6.250 -0.7030 0.02052 0.01267 0.0026 1.0000 0.0432 -6.000 -0.6921 0.01994 0.01212 0.0052 1.0000 0.0474 -5.750 -0.6783 0.01937 0.01141 0.0076 1.0000 0.0521 -5.500 -0.6529 0.01803 0.01010 0.0075 0.9978 0.0585 -5.250 -0.6209 0.01717 0.00916 0.0062 0.9938 0.0677 -5.000 -0.5881 0.01643 0.00839 0.0047 0.9902 0.0788 -4.750 -0.5588 0.01558 0.00757 0.0039 0.9859 0.0930 -4.500 -0.5294 0.01466 0.00681 0.0028 0.9820 0.1161 -4.250 -0.5036 0.01375 0.00617 0.0025 0.9772 0.1609 -4.000 -0.4833 0.01224 0.00556 0.0027 0.9720 0.3254 -3.750 -0.4738 0.01079 0.00541 0.0057 0.9662 0.5863 -3.500 -0.4501 0.01083 0.00580 0.0073 0.9615 0.7035 -3.250 -0.4182 0.01109 0.00605 0.0070 0.9583 0.7498 -3.000 -0.3831 0.01135 0.00626 0.0060 0.9561 0.7759 -2.750 -0.3626 0.01160 0.00644 0.0079 0.9503 0.7954 -2.500 -0.3325 0.01185 0.00663 0.0079 0.9468 0.8138 -2.250 -0.2981 0.01204 0.00678 0.0070 0.9444 0.8283 -2.000 -0.2620 0.01228 0.00696 0.0059 0.9426 0.8431 -1.750 -0.2381 0.01254 0.00722 0.0074 0.9381 0.8585 -1.500 -0.2097 0.01279 0.00746 0.0081 0.9345 0.8733 -1.250 -0.1771 0.01295 0.00760 0.0076 0.9317 0.8857 -1.000 -0.1357 0.01310 0.00771 0.0053 0.9300 0.8934 -0.750 -0.0983 0.01311 0.00769 0.0034 0.9278 0.9003 -0.500 -0.0685 0.01321 0.00778 0.0029 0.9231 0.9059 -0.250 -0.0442 0.01318 0.00772 0.0034 0.9178 0.9133 0.000 0.0000 0.01318 0.00772 0.0000 0.9155 0.9155 0.250 0.0442 0.01318 0.00772 -0.0034 0.9133 0.9178 0.500 0.0686 0.01321 0.00778 -0.0029 0.9059 0.9230 0.750 0.0984 0.01312 0.00769 -0.0034 0.9004 0.9278 1.000 0.1357 0.01309 0.00771 -0.0053 0.8933 0.9300 1.250 0.1776 0.01293 0.00757 -0.0076 0.8853 0.9315 1.500 0.2100 0.01278 0.00746 -0.0081 0.8732 0.9345 1.750 0.2382 0.01255 0.00723 -0.0074 0.8587 0.9382 2.000 0.2624 0.01227 0.00695 -0.0059 0.8429 0.9426 2.250 0.2982 0.01204 0.00676 -0.0070 0.8280 0.9444 2.500 0.3328 0.01184 0.00661 -0.0079 0.8134 0.9468 2.750 0.3628 0.01161 0.00644 -0.0079 0.7954 0.9503 3.000 0.3832 0.01136 0.00627 -0.0060 0.7764 0.9561 3.250 0.4185 0.01109 0.00606 -0.0070 0.7501 0.9583 3.500 0.4504 0.01084 0.00582 -0.0073 0.7059 0.9615 3.750 0.4743 0.01078 0.00543 -0.0058 0.5908 0.9661 4.000 0.4837 0.01221 0.00555 -0.0027 0.3297 0.9720 4.250 0.5040 0.01373 0.00616 -0.0025 0.1641 0.9772 4.500 0.5298 0.01462 0.00677 -0.0029 0.1190 0.9820 4.750 0.5601 0.01543 0.00747 -0.0040 0.0949 0.9857 5.000 0.5886 0.01638 0.00834 -0.0048 0.0797 0.9902 5.250 0.6212 0.01714 0.00914 -0.0063 0.0676 0.9939 5.500 0.6533 0.01796 0.01002 -0.0076 0.0579 0.9978 5.750 0.6783 0.01923 0.01130 -0.0075 0.0511 1.0000 6.000 0.6914 0.01967 0.01183 -0.0051 0.0459 1.0000 6.250 0.7029 0.02131 0.01344 -0.0027 0.0411 1.0000 6.500 0.7138 0.02200 0.01431 0.0004 0.0392 1.0000 6.750 0.7237 0.02307 0.01558 0.0036 0.0374 1.0000 7.000 0.7360 0.02444 0.01712 0.0064 0.0358 1.0000 7.250 0.7516 0.02605 0.01892 0.0085 0.0345 1.0000 7.500 0.7676 0.02739 0.02035 0.0102 0.0326 1.0000 7.750 0.7807 0.03051 0.02368 0.0120 0.0310 1.0000 8.000 0.7889 0.03427 0.02788 0.0146 0.0304 1.0000 8.250 0.7969 0.03749 0.03149 0.0172 0.0304 1.0000 8.500 0.8019 0.04168 0.03603 0.0197 0.0307 1.0000 8.750 0.8147 0.04323 0.03784 0.0218 0.0312 1.0000 9.000 0.7434 0.06174 0.05796 0.0300 0.0597 1.0000 9.250 0.7316 0.06545 0.06181 0.0314 0.0588 1.0000 9.500 0.7148 0.06891 0.06535 0.0329 0.0578 1.0000 9.750 0.6938 0.07343 0.06994 0.0320 0.0578 1.0000 10.000 0.6724 0.07938 0.07594 0.0282 0.0578 1.0000 10.250 0.6543 0.08731 0.08387 0.0214 0.0573 1.0000 10.500 0.6501 0.09268 0.08921 0.0181 0.0563 1.0000 10.750 0.6481 0.09752 0.09403 0.0158 0.0556 1.0000 11.000 0.6476 0.10215 0.09864 0.0140 0.0550 1.0000