XFOIL Version 6.96 Calculated polar for: CLARK YM-18 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7415 0.13527 0.13188 -0.0474 1.0000 0.0303 -19.500 -0.7949 0.12136 0.11773 -0.0552 1.0000 0.0306 -19.250 -0.8207 0.11304 0.10927 -0.0599 1.0000 0.0308 -19.000 -0.8404 0.10597 0.10209 -0.0639 1.0000 0.0310 -18.750 -0.8574 0.09956 0.09556 -0.0674 1.0000 0.0311 -18.500 -0.8729 0.09349 0.08938 -0.0708 1.0000 0.0313 -18.250 -0.8878 0.08766 0.08345 -0.0740 1.0000 0.0314 -18.000 -0.9024 0.08203 0.07772 -0.0771 1.0000 0.0316 -17.750 -0.9166 0.07656 0.07214 -0.0801 1.0000 0.0317 -17.500 -0.9308 0.07126 0.06673 -0.0830 1.0000 0.0318 -17.250 -0.9443 0.06609 0.06145 -0.0858 1.0000 0.0320 -17.000 -0.9564 0.06118 0.05643 -0.0885 1.0000 0.0321 -16.750 -0.9668 0.05648 0.05161 -0.0911 1.0000 0.0323 -16.500 -0.9753 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0.00288 -0.0769 0.5925 0.2778 -1.250 0.2543 0.01008 0.00286 -0.0764 0.5829 0.2886 -1.000 0.2807 0.01007 0.00284 -0.0761 0.5737 0.3007 -0.750 0.3061 0.01007 0.00283 -0.0755 0.5633 0.3129 -0.500 0.3320 0.01006 0.00283 -0.0751 0.5525 0.3265 -0.250 0.3565 0.01003 0.00283 -0.0744 0.5412 0.3497 0.000 0.3811 0.00997 0.00284 -0.0737 0.5289 0.3829 0.250 0.4050 0.00987 0.00287 -0.0730 0.5178 0.4272 0.500 0.4280 0.00979 0.00291 -0.0721 0.5059 0.4786 0.750 0.4519 0.00972 0.00296 -0.0713 0.4932 0.5284 1.000 0.4752 0.00968 0.00302 -0.0704 0.4800 0.5740 1.250 0.4978 0.00968 0.00310 -0.0693 0.4654 0.6210 1.500 0.5201 0.00971 0.00321 -0.0682 0.4492 0.6672 1.750 0.5422 0.00978 0.00333 -0.0670 0.4315 0.7079 2.000 0.5638 0.00988 0.00347 -0.0657 0.4126 0.7467 2.250 0.5851 0.01003 0.00363 -0.0643 0.3938 0.7823 2.750 0.6287 0.01037 0.00399 -0.0618 0.3648 0.8407 3.000 0.6511 0.01053 0.00417 -0.0606 0.3558 0.8685 3.250 0.6741 0.01071 0.00436 -0.0596 0.3478 0.8929 3.500 0.6975 0.01092 0.00456 -0.0586 0.3413 0.9135 3.750 0.7238 0.01111 0.00475 -0.0583 0.3359 0.9329 4.000 0.7524 0.01134 0.00496 -0.0585 0.3306 0.9510 4.250 0.7829 0.01162 0.00520 -0.0592 0.3254 0.9664 4.500 0.8165 0.01186 0.00542 -0.0605 0.3211 0.9785 4.750 0.8529 0.01211 0.00565 -0.0625 0.3168 0.9865 5.000 0.8879 0.01237 0.00589 -0.0643 0.3131 0.9933 5.250 0.9249 0.01268 0.00615 -0.0665 0.3090 0.9986 5.500 0.9387 0.01289 0.00633 -0.0640 0.3054 1.0000 5.750 0.9516 0.01300 0.00645 -0.0611 0.3028 1.0000 6.000 0.9668 0.01316 0.00661 -0.0588 0.2992 1.0000 6.250 0.9830 0.01338 0.00682 -0.0567 0.2949 1.0000 6.500 0.9998 0.01366 0.00706 -0.0549 0.2908 1.0000 6.750 1.0175 0.01397 0.00734 -0.0532 0.2869 1.0000 7.000 1.0388 0.01417 0.00757 -0.0522 0.2843 1.0000 7.250 1.0597 0.01442 0.00783 -0.0512 0.2810 1.0000 7.500 1.0797 0.01471 0.00812 -0.0501 0.2771 1.0000 7.750 1.0986 0.01507 0.00845 -0.0488 0.2729 1.0000 8.000 1.1179 0.01544 0.00881 -0.0477 0.2690 1.0000 8.250 1.1394 0.01572 0.00911 -0.0469 0.2656 1.0000 8.500 1.1601 0.01604 0.00946 -0.0460 0.2622 1.0000 8.750 1.1800 0.01642 0.00984 -0.0451 0.2588 1.0000 9.000 1.1987 0.01686 0.01027 -0.0440 0.2552 1.0000 9.250 1.2179 0.01729 0.01071 -0.0430 0.2517 1.0000 9.500 1.2385 0.01766 0.01112 -0.0422 0.2478 1.0000 9.750 1.2577 0.01812 0.01159 -0.0413 0.2432 1.0000 10.000 1.2753 0.01866 0.01212 -0.0403 0.2387 1.0000 10.250 1.2936 0.01918 0.01266 -0.0393 0.2346 1.0000 10.500 1.3125 0.01969 0.01319 -0.0385 0.2295 1.0000 10.750 1.3287 0.02034 0.01384 -0.0374 0.2236 1.0000 11.000 1.3454 0.02099 0.01450 -0.0364 0.2177 1.0000 11.250 1.3607 0.02174 0.01524 -0.0354 0.2095 1.0000 11.500 1.3748 0.02258 0.01606 -0.0342 0.2012 1.0000 11.750 1.3863 0.02359 0.01704 -0.0329 0.1916 1.0000 12.000 1.3982 0.02461 0.01804 -0.0316 0.1821 1.0000 12.250 1.4084 0.02578 0.01919 -0.0303 0.1733 1.0000 12.500 1.4166 0.02711 0.02048 -0.0289 0.1647 1.0000 12.750 1.4265 0.02835 0.02172 -0.0278 0.1569 1.0000 13.000 1.4337 0.02981 0.02317 -0.0265 0.1496 1.0000 13.250 1.4415 0.03129 0.02465 -0.0253 0.1422 1.0000 13.500 1.4486 0.03286 0.02622 -0.0242 0.1358 1.0000 13.750 1.4547 0.03453 0.02790 -0.0231 0.1293 1.0000 14.000 1.4609 0.03626 0.02965 -0.0222 0.1240 1.0000 14.250 1.4670 0.03803 0.03144 -0.0213 0.1189 1.0000 14.500 1.4709 0.04005 0.03348 -0.0204 0.1143 1.0000 14.750 1.4763 0.04198 0.03544 -0.0197 0.1100 1.0000 15.000 1.4786 0.04424 0.03772 -0.0190 0.1058 1.0000 15.250 1.4819 0.04646 0.03997 -0.0184 0.1022 1.0000 15.500 1.4846 0.04880 0.04236 -0.0179 0.0989 1.0000 15.750 1.4845 0.05146 0.04506 -0.0175 0.0958 1.0000 16.000 1.4852 0.05409 0.04774 -0.0171 0.0934 1.0000 16.250 1.4877 0.05659 0.05030 -0.0169 0.0914 1.0000 16.500 1.4881 0.05936 0.05314 -0.0168 0.0896 1.0000 16.750 1.4869 0.06236 0.05621 -0.0167 0.0880 1.0000 17.000 1.4837 0.06562 0.05952 -0.0168 0.0864 1.0000 17.250 1.4790 0.06912 0.06309 -0.0169 0.0849 1.0000 17.500 1.4793 0.07207 0.06612 -0.0171 0.0837 1.0000 17.750 1.4772 0.07536 0.06950 -0.0174 0.0825 1.0000 18.000 1.4737 0.07884 0.07306 -0.0178 0.0812 1.0000 18.250 1.4688 0.08253 0.07682 -0.0183 0.0800 1.0000 18.500 1.4627 0.08642 0.08079 -0.0190 0.0788 1.0000 18.750 1.4550 0.09058 0.08501 -0.0197 0.0776 1.0000