XFOIL Version 6.96 Calculated polar for: NACA 65(1)-212 a=0.6 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.5422 0.08996 0.08643 -0.0349 1.0000 0.0188 -10.750 -0.5552 0.08122 0.07774 -0.0408 1.0000 0.0187 -10.500 -0.5776 0.07089 0.06738 -0.0491 1.0000 0.0184 -10.250 -0.6001 0.06419 0.06058 -0.0537 1.0000 0.0181 -10.000 -0.6225 0.05902 0.05530 -0.0559 1.0000 0.0179 -9.750 -0.6448 0.05482 0.05095 -0.0553 1.0000 0.0179 -9.500 -0.6558 0.05028 0.04616 -0.0554 0.9729 0.0179 -9.250 -0.6555 0.04506 0.04050 -0.0566 0.9520 0.0181 -9.000 -0.6539 0.04075 0.03575 -0.0557 0.9363 0.0184 -8.750 -0.6504 0.03711 0.03163 -0.0539 0.9228 0.0188 -8.500 -0.6429 0.03410 0.02809 -0.0518 0.9115 0.0197 -8.250 -0.6320 0.03165 0.02516 -0.0500 0.9024 0.0205 -8.000 -0.6160 0.02966 0.02296 -0.0489 0.8940 0.0210 -7.750 -0.5980 0.02806 0.02113 -0.0479 0.8869 0.0215 -7.500 -0.5784 0.02661 0.01944 -0.0469 0.8794 0.0221 -7.250 -0.5579 0.02524 0.01783 -0.0459 0.8736 0.0226 -7.000 -0.5354 0.02397 0.01636 -0.0453 0.8669 0.0234 -6.750 -0.5128 0.02297 0.01516 -0.0445 0.8611 0.0246 -6.500 -0.4892 0.02199 0.01397 -0.0439 0.8555 0.0258 -6.250 -0.4650 0.02096 0.01275 -0.0433 0.8496 0.0264 -6.000 -0.4410 0.02009 0.01173 -0.0426 0.8448 0.0269 -5.750 -0.4184 0.01871 0.01031 -0.0420 0.8396 0.0280 -5.500 -0.3955 0.01788 0.00945 -0.0414 0.8339 0.0290 -5.250 -0.3724 0.01727 0.00877 -0.0407 0.8293 0.0307 -5.000 -0.3486 0.01673 0.00818 -0.0402 0.8245 0.0328 -4.750 -0.3249 0.01617 0.00755 -0.0396 0.8193 0.0344 -4.500 -0.3013 0.01566 0.00694 -0.0389 0.8149 0.0357 -4.250 -0.2787 0.01502 0.00623 -0.0382 0.8105 0.0380 -4.000 -0.2543 0.01458 0.00576 -0.0378 0.8053 0.0415 -3.750 -0.2292 0.01425 0.00535 -0.0374 0.8010 0.0464 -3.500 -0.2046 0.01384 0.00491 -0.0369 0.7975 0.0540 -3.250 -0.1797 0.01343 0.00456 -0.0366 0.7929 0.0740 -3.000 -0.1599 0.01237 0.00413 -0.0359 0.7881 0.2173 -2.750 -0.1447 0.01100 0.00381 -0.0343 0.7840 0.4687 -2.500 -0.1225 0.01069 0.00386 -0.0332 0.7805 0.5863 -2.250 -0.0992 0.01060 0.00401 -0.0320 0.7760 0.6571 -2.000 -0.0750 0.01063 0.00413 -0.0310 0.7719 0.7003 -1.750 -0.0495 0.01068 0.00418 -0.0302 0.7683 0.7237 -1.500 -0.0227 0.01069 0.00414 -0.0299 0.7649 0.7361 -1.250 0.0051 0.01070 0.00408 -0.0300 0.7606 0.7436 -1.000 0.0327 0.01068 0.00403 -0.0300 0.7568 0.7497 -0.750 0.0605 0.01067 0.00395 -0.0300 0.7533 0.7569 -0.500 0.0883 0.01065 0.00387 -0.0301 0.7502 0.7634 -0.250 0.1159 0.01066 0.00386 -0.0302 0.7458 0.7710 0.000 0.1435 0.01064 0.00383 -0.0303 0.7419 0.7777 0.250 0.1713 0.01062 0.00378 -0.0303 0.7384 0.7855 0.500 0.1991 0.01057 0.00373 -0.0303 0.7355 0.7921 0.750 0.2266 0.01056 0.00377 -0.0304 0.7311 0.8000 1.000 0.2539 0.01053 0.00382 -0.0304 0.7270 0.8072 1.250 0.2813 0.01052 0.00386 -0.0302 0.7234 0.8148 1.500 0.3086 0.01054 0.00395 -0.0300 0.7205 0.8229 1.750 0.3349 0.01063 0.00419 -0.0295 0.7161 0.8312 2.000 0.3616 0.01075 0.00442 -0.0291 0.7119 0.8400 2.250 0.3893 0.01085 0.00462 -0.0287 0.7082 0.8499 2.750 0.4360 0.01116 0.00497 -0.0273 0.7000 0.9066 3.000 0.4620 0.01119 0.00507 -0.0269 0.6948 0.9160 3.250 0.4895 0.01115 0.00506 -0.0267 0.6897 0.9241 3.500 0.5158 0.01110 0.00511 -0.0263 0.6787 0.9325 3.750 0.5451 0.01086 0.00486 -0.0261 0.6583 0.9396 4.000 0.5730 0.01066 0.00463 -0.0258 0.6189 0.9475 4.250 0.6029 0.01066 0.00451 -0.0261 0.5652 0.9543 4.500 0.6283 0.01109 0.00451 -0.0258 0.4635 0.9617 4.750 0.6429 0.01280 0.00522 -0.0248 0.2712 0.9717 5.000 0.6608 0.01458 0.00618 -0.0248 0.1127 0.9817 5.250 0.6852 0.01565 0.00693 -0.0253 0.0570 0.9913 5.500 0.7104 0.01635 0.00759 -0.0255 0.0441 1.0000 5.750 0.7238 0.01691 0.00815 -0.0232 0.0387 1.0000 6.000 0.7385 0.01742 0.00872 -0.0211 0.0357 1.0000 6.250 0.7526 0.01803 0.00936 -0.0190 0.0331 1.0000 6.500 0.7638 0.01886 0.01024 -0.0166 0.0307 1.0000 6.750 0.7787 0.01950 0.01093 -0.0147 0.0292 1.0000 7.000 0.7940 0.02014 0.01163 -0.0130 0.0273 1.0000 7.250 0.8076 0.02089 0.01242 -0.0110 0.0261 1.0000 7.500 0.8205 0.02168 0.01326 -0.0090 0.0252 1.0000 7.750 0.8339 0.02255 0.01417 -0.0071 0.0243 1.0000 8.000 0.8482 0.02357 0.01520 -0.0054 0.0235 1.0000 8.250 0.8650 0.02491 0.01656 -0.0042 0.0228 1.0000 8.500 0.8858 0.02611 0.01784 -0.0034 0.0222 1.0000 8.750 0.9082 0.02729 0.01913 -0.0029 0.0218 1.0000 9.000 0.9302 0.02847 0.02047 -0.0023 0.0212 1.0000 9.250 0.9509 0.02970 0.02185 -0.0017 0.0203 1.0000 9.500 0.9704 0.03098 0.02328 -0.0009 0.0196 1.0000 9.750 0.9887 0.03240 0.02486 0.0000 0.0189 1.0000 10.000 1.0064 0.03405 0.02669 0.0009 0.0186 1.0000 10.250 1.0211 0.03574 0.02857 0.0021 0.0182 1.0000 10.500 1.0328 0.03745 0.03048 0.0035 0.0179 1.0000 10.750 1.0424 0.03934 0.03255 0.0051 0.0176 1.0000 11.000 1.0495 0.04137 0.03475 0.0067 0.0173 1.0000 11.250 1.0534 0.04373 0.03734 0.0085 0.0172 1.0000 11.500 1.0534 0.04659 0.04040 0.0103 0.0169 1.0000 11.750 1.0478 0.04952 0.04358 0.0123 0.0168 1.0000 12.000 1.0382 0.05227 0.04663 0.0143 0.0166 1.0000 12.250 1.0254 0.05556 0.05023 0.0159 0.0164 1.0000 12.500 1.0099 0.05930 0.05427 0.0169 0.0161 1.0000 12.750 0.9938 0.06353 0.05873 0.0173 0.0161 1.0000 13.000 0.9736 0.06844 0.06390 0.0168 0.0159 1.0000 13.250 0.9531 0.07381 0.06950 0.0155 0.0159 1.0000 13.500 0.9315 0.07985 0.07573 0.0132 0.0159 1.0000 13.750 0.9063 0.08718 0.08325 0.0096 0.0160 1.0000 14.000 0.8807 0.09572 0.09195 0.0046 0.0161 1.0000