XFOIL Version 6.96 Calculated polar for: NACA 66 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.4693 0.11027 0.10310 -0.0658 1.0000 0.0605 -12.500 -0.4819 0.10573 0.09863 -0.0667 1.0000 0.0601 -12.250 -0.4990 0.10156 0.09453 -0.0669 1.0000 0.0597 -12.000 -0.5214 0.09754 0.09057 -0.0667 1.0000 0.0591 -11.750 -0.5469 0.09382 0.08689 -0.0661 1.0000 0.0584 -11.500 -0.5779 0.08999 0.08307 -0.0652 1.0000 0.0579 -11.250 -0.6062 0.08573 0.07877 -0.0651 0.9981 0.0572 -11.000 -0.6292 0.08033 0.07320 -0.0675 0.9918 0.0568 -10.750 -0.6510 0.07585 0.06851 -0.0683 0.9855 0.0565 -10.500 -0.6705 0.07234 0.06477 -0.0675 0.9791 0.0561 -10.250 -0.6883 0.06928 0.06145 -0.0657 0.9731 0.0561 -10.000 -0.7045 0.06683 0.05877 -0.0624 0.9668 0.0561 -9.750 -0.7133 0.06394 0.05557 -0.0600 0.9618 0.0561 -9.500 -0.7194 0.06128 0.05260 -0.0573 0.9572 0.0561 -9.250 -0.7249 0.05888 0.04989 -0.0540 0.9522 0.0562 -9.000 -0.7226 0.05626 0.04688 -0.0518 0.9483 0.0566 -8.750 -0.7156 0.05385 0.04408 -0.0500 0.9450 0.0573 -8.500 -0.7160 0.05213 0.04204 -0.0463 0.9408 0.0582 -8.250 -0.7104 0.05027 0.03975 -0.0435 0.9376 0.0596 -8.000 -0.6987 0.04843 0.03745 -0.0415 0.9349 0.0608 -7.750 -0.6778 0.04633 0.03506 -0.0411 0.9331 0.0620 -7.500 -0.6500 0.04443 0.03298 -0.0417 0.9315 0.0633 -7.250 -0.6292 0.04306 0.03146 -0.0408 0.9292 0.0651 -7.000 -0.6089 0.04195 0.03018 -0.0398 0.9267 0.0679 -6.750 -0.5807 0.04088 0.02885 -0.0398 0.9248 0.0713 -6.500 -0.5387 0.03967 0.02757 -0.0420 0.9240 0.0746 -6.250 -0.5022 0.03883 0.02667 -0.0434 0.9230 0.0791 -6.000 -0.4757 0.03824 0.02589 -0.0432 0.9214 0.0852 -5.750 -0.4562 0.03750 0.02519 -0.0422 0.9197 0.0903 -5.500 -0.4384 0.03686 0.02446 -0.0409 0.9177 0.0966 -5.250 -0.4241 0.03618 0.02377 -0.0392 0.9155 0.1054 -5.000 -0.4258 0.03573 0.02329 -0.0345 0.9119 0.1146 -4.500 -0.4240 0.03405 0.02210 -0.0266 0.9066 0.1668 -4.250 -0.3920 0.03365 0.02471 -0.0232 0.9063 0.6163 -4.000 -0.4048 0.03350 0.02441 -0.0165 0.9026 0.6801 -3.750 -0.3978 0.03479 0.02555 -0.0108 0.9002 0.7447 -3.500 -0.2614 0.04074 0.03099 -0.0206 0.9030 0.8382 -3.250 -0.2350 0.04086 0.03087 -0.0208 0.9014 0.8507 -3.000 -0.1972 0.04096 0.03070 -0.0233 0.9002 0.8600 -2.750 -0.1844 0.04095 0.03056 -0.0212 0.8971 0.8697 -2.500 -0.1703 0.04094 0.03041 -0.0195 0.8941 0.8795 -2.250 -0.1432 0.04092 0.03022 -0.0203 0.8919 0.8864 -2.000 -0.1196 0.04091 0.03007 -0.0205 0.8894 0.8939 -1.750 -0.0957 0.04091 0.02994 -0.0208 0.8869 0.9005 -1.500 -0.0615 0.04093 0.02982 -0.0231 0.8850 0.9055 -1.250 -0.0567 0.04096 0.02978 -0.0198 0.8814 0.9133 -1.000 -0.0339 0.04095 0.02969 -0.0201 0.8780 0.9179 -0.750 -0.0109 0.04098 0.02965 -0.0203 0.8748 0.9229 -0.500 0.0069 0.04106 0.02965 -0.0195 0.8716 0.9284 -0.250 0.0385 0.04116 0.02969 -0.0213 0.8690 0.9320 0.000 0.0587 0.04124 0.02973 -0.0212 0.8652 0.9364 0.250 0.0713 0.04133 0.02980 -0.0195 0.8605 0.9418 0.500 0.0914 0.04145 0.02990 -0.0192 0.8565 0.9457 0.750 0.1229 0.04160 0.03004 -0.0210 0.8533 0.9482 1.000 0.1431 0.04176 0.03020 -0.0209 0.8488 0.9518 1.250 0.1555 0.04191 0.03036 -0.0192 0.8431 0.9562 1.500 0.1779 0.04210 0.03056 -0.0193 0.8387 0.9593 1.750 0.2138 0.04234 0.03084 -0.0218 0.8353 0.9614 2.000 0.2245 0.04253 0.03108 -0.0201 0.8281 0.9657 2.250 0.2487 0.04276 0.03136 -0.0206 0.8227 0.9690 2.500 0.2797 0.04305 0.03170 -0.0220 0.8187 0.9717 2.750 0.2938 0.04328 0.03202 -0.0210 0.8103 0.9755 3.000 0.3244 0.04354 0.03238 -0.0226 0.8048 0.9785 3.250 0.3467 0.04384 0.03278 -0.0227 0.7981 0.9821 3.500 0.3690 0.04411 0.03316 -0.0229 0.7904 0.9852 3.750 0.4076 0.04433 0.03352 -0.0254 0.7856 0.9872 4.000 0.4207 0.04465 0.03397 -0.0243 0.7749 0.9918 4.250 0.4600 0.04482 0.03433 -0.0269 0.7695 0.9943 4.750 0.4997 0.04527 0.03508 -0.0261 0.7500 1.0000 5.000 0.5123 0.04531 0.03525 -0.0239 0.7397 1.0000 5.250 0.5166 0.04539 0.03546 -0.0205 0.7278 1.0000 5.500 0.5402 0.04520 0.03546 -0.0197 0.7189 1.0000 5.750 0.5510 0.04506 0.03546 -0.0170 0.7069 1.0000 6.000 0.5544 0.04494 0.03548 -0.0133 0.6933 1.0000 6.250 0.5607 0.04471 0.03540 -0.0098 0.6796 1.0000 6.500 0.5694 0.04423 0.03509 -0.0065 0.6648 1.0000 6.750 0.5791 0.04351 0.03453 -0.0029 0.6483 1.0000 7.000 0.5888 0.04177 0.03294 0.0017 0.6218 1.0000 7.250 0.5976 0.03900 0.03024 0.0078 0.5786 1.0000 7.500 0.6022 0.03665 0.02786 0.0142 0.5123 1.0000 7.750 0.6483 0.03330 0.02326 0.0177 0.3069 1.0000 8.000 0.6348 0.03475 0.02394 0.0227 0.2130 1.0000 8.250 0.6261 0.03654 0.02510 0.0265 0.1448 1.0000 8.500 0.6247 0.03827 0.02641 0.0292 0.1095 1.0000 8.750 0.6288 0.03981 0.02776 0.0313 0.0934 1.0000 9.000 0.6372 0.04114 0.02907 0.0329 0.0832 1.0000 9.250 0.6472 0.04246 0.03037 0.0344 0.0767 1.0000 9.500 0.6601 0.04367 0.03163 0.0356 0.0718 1.0000 9.750 0.6749 0.04491 0.03281 0.0368 0.0681 1.0000 10.000 0.6984 0.04577 0.03387 0.0375 0.0650 1.0000 10.250 0.7303 0.04652 0.03475 0.0378 0.0619 1.0000 10.500 0.7715 0.04730 0.03557 0.0372 0.0595 1.0000 10.750 0.8214 0.04867 0.03712 0.0358 0.0575 1.0000 11.000 0.8542 0.05056 0.03934 0.0353 0.0555 1.0000 11.250 0.8773 0.05266 0.04169 0.0354 0.0536 1.0000 11.500 0.8970 0.05487 0.04414 0.0357 0.0523 1.0000 11.750 0.9129 0.05741 0.04691 0.0363 0.0515 1.0000 12.000 0.9241 0.06011 0.04985 0.0371 0.0510 1.0000 12.250 0.9331 0.06292 0.05284 0.0379 0.0503 1.0000 12.500 0.9283 0.06592 0.05612 0.0397 0.0498 1.0000 12.750 0.9192 0.06908 0.05959 0.0414 0.0497 1.0000 13.000 0.9046 0.07251 0.06333 0.0431 0.0494 1.0000 13.250 0.8885 0.07631 0.06741 0.0442 0.0492 1.0000 13.500 0.8720 0.08034 0.07168 0.0448 0.0492 1.0000 13.750 0.8512 0.08497 0.07654 0.0448 0.0492 1.0000 14.000 0.8301 0.08998 0.08176 0.0440 0.0493 1.0000 14.250 0.8057 0.09580 0.08776 0.0424 0.0494 1.0000 14.500 0.7844 0.10193 0.09404 0.0399 0.0497 1.0000 14.750 0.7611 0.10910 0.10133 0.0363 0.0499 1.0000