XFOIL Version 6.96 Calculated polar for: GOE 703 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.7311 0.07282 0.06538 -0.0846 1.0000 0.0536 -15.000 -0.7553 0.06769 0.06006 -0.0858 1.0000 0.0536 -14.750 -0.7717 0.06382 0.05603 -0.0860 1.0000 0.0538 -14.500 -0.7826 0.06072 0.05281 -0.0855 1.0000 0.0541 -14.250 -0.7930 0.05786 0.04982 -0.0845 1.0000 0.0542 -14.000 -0.7998 0.05551 0.04738 -0.0832 1.0000 0.0546 -13.750 -0.8063 0.05330 0.04507 -0.0815 1.0000 0.0550 -13.500 -0.8121 0.05131 0.04299 -0.0794 1.0000 0.0555 -13.250 -0.8175 0.04945 0.04101 -0.0771 1.0000 0.0560 -13.000 -0.8220 0.04773 0.03917 -0.0745 1.0000 0.0565 -12.750 -0.8270 0.04613 0.03745 -0.0716 1.0000 0.0571 -12.500 -0.8307 0.04469 0.03588 -0.0684 1.0000 0.0577 -12.250 -0.8347 0.04337 0.03443 -0.0650 1.0000 0.0583 -12.000 -0.8390 0.04219 0.03311 -0.0612 1.0000 0.0589 -11.750 -0.8434 0.04122 0.03202 -0.0572 1.0000 0.0593 -11.500 -0.8449 0.04044 0.03129 -0.0534 1.0000 0.0598 -11.250 -0.8217 0.03915 0.03001 -0.0542 0.9957 0.0607 -11.000 -0.7942 0.03778 0.02859 -0.0557 0.9886 0.0618 -10.750 -0.7667 0.03647 0.02720 -0.0572 0.9816 0.0632 -10.500 -0.7410 0.03523 0.02582 -0.0581 0.9733 0.0647 -10.250 -0.7126 0.03403 0.02456 -0.0595 0.9665 0.0665 -10.000 -0.6901 0.03297 0.02352 -0.0597 0.9565 0.0682 -9.750 -0.6632 0.03190 0.02239 -0.0607 0.9489 0.0706 -9.500 -0.6373 0.03087 0.02128 -0.0612 0.9400 0.0732 -9.250 -0.6104 0.02982 0.02025 -0.0621 0.9325 0.0758 -9.000 -0.5838 0.02886 0.01923 -0.0627 0.9234 0.0790 -8.750 -0.5505 0.02779 0.01816 -0.0647 0.9177 0.0834 -8.500 -0.5248 0.02698 0.01731 -0.0650 0.9069 0.0890 -8.250 -0.4916 0.02601 0.01636 -0.0669 0.8998 0.0964 -8.000 -0.4667 0.02526 0.01564 -0.0670 0.8885 0.1052 -7.750 -0.4332 0.02444 0.01482 -0.0687 0.8804 0.1186 -7.500 -0.4084 0.02385 0.01426 -0.0686 0.8687 0.1328 -7.250 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-2.250 0.1494 0.01995 0.01168 -0.0614 0.6760 0.7541 -2.000 0.1696 0.02025 0.01191 -0.0595 0.6690 0.7723 -1.750 0.2024 0.02076 0.01235 -0.0597 0.6617 0.7842 -1.500 0.2307 0.02109 0.01254 -0.0592 0.6558 0.7970 -1.250 0.2494 0.02137 0.01277 -0.0571 0.6491 0.8114 -1.000 0.2858 0.02182 0.01314 -0.0582 0.6419 0.8197 -0.750 0.3120 0.02209 0.01329 -0.0575 0.6361 0.8316 -0.500 0.3429 0.02251 0.01365 -0.0577 0.6296 0.8429 -0.250 0.3775 0.02292 0.01402 -0.0585 0.6224 0.8525 0.250 0.4465 0.02354 0.01447 -0.0604 0.6104 0.8716 0.500 0.4646 0.02382 0.01476 -0.0585 0.6037 0.8835 0.750 0.5063 0.02394 0.01480 -0.0611 0.5973 0.8880 1.000 0.5380 0.02401 0.01477 -0.0619 0.5921 0.8936 1.250 0.5512 0.02418 0.01498 -0.0593 0.5853 0.9016 1.500 0.5851 0.02421 0.01498 -0.0606 0.5790 0.9050 1.750 0.6166 0.02422 0.01490 -0.0615 0.5737 0.9093 2.000 0.6310 0.02441 0.01512 -0.0591 0.5676 0.9167 2.250 0.6590 0.02446 0.01518 -0.0594 0.5610 0.9206 2.500 0.6911 0.02445 0.01512 -0.0604 0.5553 0.9241 2.750 0.7164 0.02454 0.01519 -0.0602 0.5495 0.9289 3.000 0.7298 0.02476 0.01546 -0.0577 0.5430 0.9353 3.250 0.7619 0.02472 0.01540 -0.0588 0.5369 0.9381 3.500 0.7925 0.02472 0.01534 -0.0595 0.5316 0.9415 3.750 0.8114 0.02492 0.01564 -0.0582 0.5245 0.9466 4.000 0.8293 0.02507 0.01579 -0.0566 0.5185 0.9515 4.250 0.8626 0.02499 0.01565 -0.0578 0.5134 0.9539 4.500 0.8845 0.02517 0.01594 -0.0572 0.5058 0.9579 4.750 0.9066 0.02527 0.01606 -0.0564 0.4994 0.9618 5.000 0.9286 0.02534 0.01606 -0.0555 0.4939 0.9659 5.250 0.9512 0.02547 0.01631 -0.0550 0.4849 0.9692 5.500 0.9768 0.02540 0.01620 -0.0548 0.4770 0.9721 5.750 0.9942 0.02556 0.01644 -0.0533 0.4674 0.9764 6.000 1.0143 0.02559 0.01641 -0.0520 0.4584 0.9802 6.250 1.0344 0.02566 0.01655 -0.0511 0.4475 0.9832 6.500 1.0578 0.02564 0.01648 -0.0506 0.4390 0.9862 6.750 1.0751 0.02591 0.01685 -0.0493 0.4297 0.9902 7.000 1.0969 0.02602 0.01696 -0.0486 0.4224 0.9931 7.250 1.1157 0.02624 0.01724 -0.0476 0.4141 0.9961 7.500 1.1362 0.02641 0.01745 -0.0468 0.4060 0.9991 7.750 1.1464 0.02671 0.01777 -0.0440 0.3990 1.0000 8.000 1.1467 0.02711 0.01823 -0.0395 0.3919 1.0000 8.250 1.1485 0.02739 0.01848 -0.0350 0.3858 1.0000 8.500 1.1417 0.02783 0.01899 -0.0293 0.3795 1.0000 8.750 1.1363 0.02828 0.01948 -0.0239 0.3729 1.0000 9.000 1.1379 0.02862 0.01977 -0.0197 0.3669 1.0000 9.250 1.1285 0.02933 0.02058 -0.0141 0.3599 1.0000 9.500 1.1253 0.02990 0.02117 -0.0096 0.3531 1.0000 9.750 1.1227 0.03054 0.02181 -0.0052 0.3463 1.0000 10.000 1.1150 0.03142 0.02275 -0.0005 0.3388 1.0000 10.250 1.1161 0.03201 0.02329 0.0031 0.3319 1.0000 10.500 1.1058 0.03319 0.02457 0.0076 0.3240 1.0000 10.750 1.1028 0.03408 0.02542 0.0113 0.3163 1.0000 11.000 1.0951 0.03534 0.02674 0.0152 0.3081 1.0000 11.250 1.0902 0.03648 0.02786 0.0187 0.2996 1.0000 11.500 1.0829 0.03792 0.02933 0.0221 0.2912 1.0000 11.750 1.0773 0.03930 0.03070 0.0252 0.2823 1.0000 12.000 1.0696 0.04098 0.03243 0.0282 0.2735 1.0000 12.250 1.0647 0.04251 0.03392 0.0309 0.2647 1.0000 12.500 1.0575 0.04442 0.03589 0.0333 0.2562 1.0000 12.750 1.0546 0.04601 0.03744 0.0355 0.2483 1.0000 13.000 1.0483 0.04806 0.03954 0.0376 0.2402 1.0000 13.250 1.0458 0.04980 0.04124 0.0394 0.2326 1.0000 13.500 1.0425 0.05178 0.04327 0.0410 0.2256 1.0000 13.750 1.0404 0.05370 0.04519 0.0425 0.2190 1.0000 14.000 1.0393 0.05556 0.04703 0.0439 0.2126 1.0000 14.250 1.0360 0.05779 0.04930 0.0451 0.2063 1.0000 14.500 1.0372 0.05950 0.05094 0.0463 0.2005 1.0000 14.750 1.0342 0.06187 0.05339 0.0473 0.1950 1.0000 15.000 1.0327 0.06407 0.05562 0.0481 0.1896 1.0000 15.250 1.0371 0.06558 0.05705 0.0491 0.1851 1.0000 15.500 1.0318 0.06842 0.06002 0.0496 0.1799 1.0000 15.750 1.0312 0.07070 0.06232 0.0502 0.1753 1.0000 16.000 1.0365 0.07220 0.06375 0.0509 0.1710 1.0000 16.250 1.0313 0.07524 0.06692 0.0512 0.1667 1.0000 16.500 1.0289 0.07792 0.06968 0.0514 0.1625 1.0000 16.750 1.0344 0.07953 0.07125 0.0519 0.1587 1.0000 17.000 1.0309 0.08248 0.07428 0.0519 0.1547 1.0000 17.250 1.0250 0.08580 0.07772 0.0517 0.1505 1.0000 17.500 1.0267 0.08803 0.07994 0.0518 0.1465 1.0000 17.750 1.0265 0.09060 0.08254 0.0518 0.1428 1.0000 18.000 1.0148 0.09495 0.08704 0.0510 0.1383 1.0000 18.250 1.0141 0.09764 0.08977 0.0507 0.1343 1.0000 18.500 1.0134 0.10038 0.09252 0.0504 0.1303 1.0000 18.750 0.9980 0.10551 0.09782 0.0491 0.1258 1.0000 19.000 0.9979 0.10822 0.10053 0.0486 0.1217 1.0000 19.250 0.9917 0.11198 0.10436 0.0476 0.1177 1.0000