XFOIL Version 6.96 Calculated polar for: SOMERS S102 AIRFOIL (BLUNT) 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.3099 0.10789 0.10457 -0.0471 1.0000 0.0514 -11.250 -0.3144 0.10357 0.10028 -0.0488 1.0000 0.0531 -11.000 -0.4435 0.10290 0.09940 -0.0463 1.0000 0.0481 -10.750 -0.4374 0.10010 0.09661 -0.0465 1.0000 0.0493 -10.500 -0.4377 0.09568 0.09223 -0.0486 1.0000 0.0505 -10.250 -0.4444 0.08958 0.08616 -0.0527 1.0000 0.0517 -10.000 -0.4613 0.08203 0.07863 -0.0586 1.0000 0.0522 -9.750 -0.4832 0.07601 0.07259 -0.0625 1.0000 0.0525 -9.500 -0.5079 0.07162 0.06818 -0.0638 1.0000 0.0525 -9.250 -0.5388 0.06926 0.06586 -0.0613 1.0000 0.0521 -9.000 -0.5738 0.06807 0.06471 -0.0575 0.9970 0.0514 -8.750 -0.5777 0.06379 0.05956 -0.0685 0.9808 0.0560 -7.000 -0.4090 0.02892 0.02204 -0.0810 0.9309 0.0299 -6.750 -0.3787 0.02600 0.01879 -0.0811 0.9251 0.0278 -6.500 -0.3524 0.02401 0.01642 -0.0801 0.9161 0.0265 -6.250 -0.3243 0.02250 0.01481 -0.0797 0.9096 0.0266 -6.000 -0.3000 0.02135 0.01362 -0.0788 0.9010 0.0272 -5.750 -0.2751 0.02031 0.01256 -0.0781 0.8940 0.0283 -5.500 -0.2521 0.01945 0.01167 -0.0772 0.8859 0.0299 -5.250 -0.2293 0.01851 0.01073 -0.0766 0.8791 0.0331 -5.000 -0.2048 0.01791 0.01009 -0.0763 0.8726 0.0381 -4.750 -0.1821 0.01684 0.00905 -0.0763 0.8657 0.0451 -4.500 -0.1570 0.01565 0.00791 -0.0767 0.8609 0.0697 -4.250 -0.1374 0.01334 0.00786 -0.0783 0.8540 0.5843 -4.000 -0.1120 0.01469 0.00920 -0.0760 0.8488 0.6195 -3.750 -0.0891 0.01606 0.01062 -0.0726 0.8448 0.6409 -3.500 -0.0676 0.01727 0.01186 -0.0694 0.8393 0.6577 -3.250 -0.0481 0.01862 0.01325 -0.0650 0.8347 0.6761 -3.000 -0.0273 0.01978 0.01437 -0.0612 0.8310 0.6967 -2.750 -0.0058 0.02019 0.01474 -0.0583 0.8278 0.7027 -2.500 0.0212 0.02002 0.01450 -0.0588 0.8231 0.7054 -2.250 0.0502 0.01974 0.01411 -0.0599 0.8190 0.7081 -2.000 0.0815 0.01938 0.01361 -0.0617 0.8155 0.7111 -1.750 0.1149 0.01900 0.01307 -0.0642 0.8129 0.7136 -1.500 0.1413 0.01889 0.01294 -0.0643 0.8092 0.7148 -1.250 0.1691 0.01877 0.01278 -0.0649 0.8056 0.7158 -1.000 0.1972 0.01867 0.01263 -0.0654 0.8023 0.7172 -0.750 0.2264 0.01853 0.01244 -0.0661 0.7993 0.7185 -0.500 0.2568 0.01839 0.01223 -0.0672 0.7969 0.7195 -0.250 0.2854 0.01838 0.01221 -0.0681 0.7939 0.7209 0.000 0.3141 0.01837 0.01219 -0.0691 0.7901 0.7224 0.250 0.3440 0.01830 0.01210 -0.0703 0.7868 0.7235 0.500 0.3748 0.01819 0.01194 -0.0715 0.7836 0.7245 0.750 0.4054 0.01800 0.01169 -0.0722 0.7782 0.7260 1.000 0.4347 0.01772 0.01137 -0.0728 0.7690 0.7275 1.250 0.4652 0.01740 0.01097 -0.0733 0.7605 0.7284 1.500 0.4954 0.01710 0.01061 -0.0739 0.7516 0.7294 1.750 0.5231 0.01683 0.01033 -0.0737 0.7421 0.7302 2.000 0.5524 0.01648 0.00991 -0.0737 0.7329 0.7312 2.250 0.5791 0.01634 0.00981 -0.0735 0.7234 0.7325 2.500 0.6085 0.01618 0.00963 -0.0738 0.7174 0.7338 2.750 0.6363 0.01609 0.00960 -0.0740 0.7095 0.7349 3.000 0.6659 0.01588 0.00937 -0.0743 0.7015 0.7361 3.250 0.6936 0.01575 0.00928 -0.0744 0.6917 0.7374 3.500 0.7235 0.01554 0.00904 -0.0747 0.6828 0.7387 3.750 0.7513 0.01537 0.00894 -0.0748 0.6714 0.7402 4.000 0.7793 0.01519 0.00879 -0.0749 0.6586 0.7417 4.250 0.8073 0.01498 0.00860 -0.0749 0.6428 0.7434 4.500 0.8346 0.01475 0.00837 -0.0747 0.6221 0.7453 4.750 0.8588 0.01455 0.00821 -0.0739 0.5912 0.7467 5.000 0.8786 0.01452 0.00794 -0.0721 0.5023 0.7482 5.250 0.8780 0.01613 0.00847 -0.0675 0.3385 0.7497 5.500 0.8881 0.01736 0.00925 -0.0652 0.2717 0.7514 5.750 0.9043 0.01820 0.00989 -0.0637 0.2427 0.7532 6.000 0.9231 0.01889 0.01046 -0.0627 0.2255 0.7552 6.250 0.9427 0.01955 0.01104 -0.0618 0.2135 0.7573 6.500 0.9632 0.02017 0.01159 -0.0611 0.2043 0.7595 6.750 0.9845 0.02074 0.01217 -0.0604 0.1970 0.7615 7.000 1.0049 0.02128 0.01273 -0.0596 0.1906 0.7636 7.250 1.0255 0.02197 0.01339 -0.0588 0.1848 0.7662 7.500 1.0476 0.02246 0.01396 -0.0581 0.1793 0.7691 7.750 1.0699 0.02308 0.01458 -0.0577 0.1745 0.7721 8.000 1.0946 0.02389 0.01535 -0.0577 0.1700 0.7750 8.250 1.1168 0.02438 0.01598 -0.0571 0.1656 0.7778 8.500 1.1387 0.02495 0.01660 -0.0565 0.1613 0.7807 8.750 1.1652 0.02586 0.01746 -0.0568 0.1570 0.7840 9.000 1.1873 0.02647 0.01824 -0.0563 0.1533 0.7879 9.250 1.2094 0.02709 0.01897 -0.0558 0.1493 0.7921 9.500 1.2308 0.02771 0.01967 -0.0552 0.1455 0.7958 9.750 1.2595 0.02885 0.02078 -0.0559 0.1410 0.8003 10.000 1.2767 0.02941 0.02157 -0.0547 0.1377 0.8060 10.250 1.2930 0.02999 0.02231 -0.0532 0.1338 0.8116 10.500 1.3117 0.03064 0.02300 -0.0523 0.1300 0.8184 10.750 1.3362 0.03179 0.02424 -0.0525 0.1257 0.8255 11.000 1.3461 0.03238 0.02509 -0.0501 0.1223 0.8341 11.250 1.3586 0.03302 0.02588 -0.0484 0.1185 0.8441 11.500 1.3750 0.03373 0.02659 -0.0473 0.1147 0.8569 11.750 1.3866 0.03471 0.02781 -0.0455 0.1109 0.8750 12.000 1.3862 0.03518 0.02862 -0.0415 0.1078 0.9293 12.250 1.3958 0.03595 0.02947 -0.0403 0.1040 1.0000 12.500 1.4152 0.03713 0.03052 -0.0403 0.0996 1.0000 12.750 1.4167 0.03835 0.03202 -0.0384 0.0964 1.0000 13.000 1.4218 0.03953 0.03332 -0.0370 0.0925 1.0000 13.250 1.4291 0.04062 0.03439 -0.0360 0.0891 1.0000 13.500 1.4341 0.04227 0.03617 -0.0348 0.0853 1.0000 13.750 1.4363 0.04389 0.03799 -0.0337 0.0814 1.0000 14.000 1.4402 0.04540 0.03952 -0.0330 0.0779 1.0000 14.250 1.4432 0.04740 0.04162 -0.0321 0.0742 1.0000 14.500 1.4444 0.04951 0.04390 -0.0315 0.0703 1.0000 14.750 1.4460 0.05158 0.04599 -0.0311 0.0670 1.0000 15.000 1.4453 0.05418 0.04873 -0.0305 0.0634 1.0000 15.250 1.4445 0.05681 0.05151 -0.0303 0.0598 1.0000 15.500 1.4427 0.05959 0.05428 -0.0302 0.0567 1.0000 15.750 1.4384 0.06295 0.05784 -0.0301 0.0536 1.0000 16.000 1.4345 0.06634 0.06139 -0.0304 0.0506 1.0000 16.250 1.4290 0.06995 0.06499 -0.0308 0.0482 1.0000 16.500 1.4206 0.07419 0.06941 -0.0313 0.0459 1.0000 16.750 1.4120 0.07864 0.07405 -0.0322 0.0437 1.0000 17.000 1.4037 0.08316 0.07867 -0.0335 0.0418 1.0000 17.250 1.3950 0.08761 0.08309 -0.0345 0.0400 1.0000 17.500 1.3812 0.09340 0.08911 -0.0365 0.0387 1.0000 17.750 1.3668 0.09953 0.09547 -0.0390 0.0374 1.0000