XFOIL Version 6.96 Calculated polar for: NACA 65(4)-221 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -0.8042 0.11512 0.11016 -0.0541 1.0000 0.0271 -19.250 -0.8304 0.10671 0.10150 -0.0588 1.0000 0.0272 -19.000 -0.8505 0.09979 0.09436 -0.0625 1.0000 0.0273 -18.750 -0.8662 0.09390 0.08825 -0.0654 1.0000 0.0274 -18.500 -0.8799 0.08853 0.08267 -0.0678 1.0000 0.0276 -18.250 -0.8910 0.08375 0.07768 -0.0697 1.0000 0.0277 -18.000 -0.8996 0.07949 0.07320 -0.0713 1.0000 0.0279 -17.750 -0.9075 0.07547 0.06897 -0.0726 1.0000 0.0280 -17.500 -0.9070 0.07251 0.06588 -0.0733 1.0000 0.0282 -17.250 -0.8997 0.07034 0.06367 -0.0737 1.0000 0.0285 -17.000 -0.8934 0.06812 0.06140 -0.0741 1.0000 0.0287 -16.750 -0.8872 0.06593 0.05912 -0.0745 1.0000 0.0289 -16.500 -0.8800 0.06387 0.05700 -0.0748 1.0000 0.0291 -16.250 -0.8721 0.06192 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0.00747 -0.0314 0.6668 0.6288 -1.750 -0.0446 0.01524 0.00745 -0.0316 0.6639 0.6309 -1.500 -0.0170 0.01522 0.00740 -0.0319 0.6613 0.6330 -1.250 0.0107 0.01518 0.00733 -0.0321 0.6591 0.6354 -1.000 0.0385 0.01514 0.00724 -0.0324 0.6570 0.6380 -0.750 0.0665 0.01510 0.00712 -0.0328 0.6552 0.6410 -0.500 0.0942 0.01508 0.00704 -0.0332 0.6532 0.6437 -0.250 0.1208 0.01512 0.00714 -0.0333 0.6504 0.6454 0.000 0.1478 0.01516 0.00721 -0.0334 0.6475 0.6472 0.250 0.1751 0.01519 0.00726 -0.0336 0.6449 0.6492 0.500 0.2027 0.01522 0.00730 -0.0338 0.6427 0.6515 0.750 0.2306 0.01525 0.00732 -0.0341 0.6407 0.6542 1.000 0.2588 0.01526 0.00732 -0.0345 0.6388 0.6571 1.250 0.2875 0.01527 0.00728 -0.0350 0.6370 0.6599 1.500 0.3148 0.01532 0.00734 -0.0353 0.6348 0.6623 1.750 0.3401 0.01542 0.00754 -0.0351 0.6319 0.6642 2.000 0.3662 0.01553 0.00771 -0.0351 0.6293 0.6663 2.250 0.3929 0.01563 0.00786 -0.0353 0.6270 0.6686 2.500 0.4201 0.01570 0.00797 -0.0354 0.6247 0.6713 2.750 0.4480 0.01576 0.00804 -0.0358 0.6225 0.6743 3.000 0.4767 0.01580 0.00809 -0.0362 0.6205 0.6775 3.250 0.5059 0.01586 0.00813 -0.0368 0.6189 0.6805 3.500 0.5306 0.01602 0.00841 -0.0366 0.6163 0.6826 3.750 0.5537 0.01621 0.00872 -0.0361 0.6131 0.6849 4.000 0.5784 0.01636 0.00895 -0.0359 0.6101 0.6876 4.250 0.6047 0.01646 0.00912 -0.0359 0.6073 0.6904 4.500 0.6327 0.01651 0.00921 -0.0362 0.6046 0.6937 4.750 0.6628 0.01651 0.00922 -0.0368 0.6020 0.6973 5.000 0.6874 0.01663 0.00943 -0.0366 0.5985 0.7004 5.250 0.7071 0.01684 0.00978 -0.0355 0.5938 0.7032 5.500 0.7321 0.01686 0.00989 -0.0352 0.5891 0.7061 5.750 0.7638 0.01664 0.00967 -0.0358 0.5841 0.7093 6.000 0.7800 0.01674 0.00990 -0.0340 0.5759 0.7130 6.250 0.8064 0.01656 0.00972 -0.0338 0.5682 0.7168 6.500 0.8237 0.01660 0.00988 -0.0322 0.5592 0.7201 6.750 0.8462 0.01640 0.00971 -0.0311 0.5481 0.7235 7.000 0.8585 0.01642 0.00980 -0.0285 0.5337 0.7276 7.250 0.8670 0.01649 0.00992 -0.0253 0.5177 0.7322 7.500 0.8727 0.01663 0.01005 -0.0217 0.4996 0.7370 7.750 0.8762 0.01702 0.01047 -0.0180 0.4763 0.7408 8.000 0.8797 0.01752 0.01089 -0.0144 0.4434 0.7451 8.250 0.8751 0.01842 0.01156 -0.0101 0.4006 0.7502 8.500 0.8661 0.01975 0.01266 -0.0058 0.3603 0.7558 8.750 0.8541 0.02138 0.01412 -0.0014 0.3223 0.7607 9.000 0.8450 0.02309 0.01569 0.0022 0.2883 0.7662 9.250 0.8376 0.02490 0.01734 0.0053 0.2559 0.7724 9.500 0.8319 0.02673 0.01904 0.0080 0.2250 0.7780 9.750 0.8273 0.02855 0.02076 0.0104 0.1960 0.7834 10.000 0.8251 0.03036 0.02245 0.0125 0.1690 0.7895 10.250 0.8250 0.03214 0.02411 0.0142 0.1425 0.7957 10.500 0.8257 0.03385 0.02574 0.0159 0.1183 0.8015 10.750 0.8262 0.03567 0.02745 0.0173 0.0940 0.8083 11.000 0.8282 0.03748 0.02915 0.0186 0.0740 0.8154 11.250 0.8324 0.03911 0.03074 0.0198 0.0609 0.8226 11.500 0.8388 0.04070 0.03232 0.0207 0.0529 0.8306 11.750 0.8461 0.04218 0.03385 0.0216 0.0479 0.8384 12.000 0.8536 0.04375 0.03545 0.0223 0.0443 0.8471 12.250 0.8616 0.04530 0.03707 0.0230 0.0417 0.8558 12.750 0.8770 0.04852 0.04044 0.0242 0.0382 0.8769 13.000 0.8847 0.05016 0.04218 0.0247 0.0367 0.8903 13.250 0.8918 0.05192 0.04402 0.0251 0.0354 0.9070 13.500 0.8998 0.05388 0.04606 0.0249 0.0344 0.9292 13.750 0.9133 0.05569 0.04801 0.0236 0.0333 0.9730 14.250 0.9288 0.05959 0.05200 0.0234 0.0316 1.0000 14.500 0.9367 0.06165 0.05409 0.0231 0.0310 1.0000 14.750 0.9430 0.06389 0.05634 0.0228 0.0303 1.0000 15.000 0.9500 0.06606 0.05852 0.0226 0.0299 1.0000 15.250 0.9591 0.06804 0.06058 0.0223 0.0293 1.0000 15.500 0.9679 0.07006 0.06266 0.0220 0.0288 1.0000 15.750 0.9768 0.07206 0.06473 0.0217 0.0283 1.0000 16.000 0.9854 0.07414 0.06686 0.0213 0.0276 1.0000 16.250 0.9940 0.07623 0.06899 0.0209 0.0272 1.0000 16.500 1.0025 0.07835 0.07116 0.0205 0.0268 1.0000 16.750 1.0106 0.08050 0.07333 0.0200 0.0263 1.0000 17.000 1.0200 0.08247 0.07532 0.0196 0.0260 1.0000 17.250 1.0283 0.08457 0.07744 0.0191 0.0255 1.0000 17.500 1.0362 0.08687 0.07984 0.0185 0.0251 1.0000 17.750 1.0446 0.08908 0.08216 0.0179 0.0249 1.0000 18.000 1.0517 0.09149 0.08467 0.0173 0.0246 1.0000 18.250 1.0581 0.09402 0.08730 0.0165 0.0242 1.0000 18.500 1.0641 0.09659 0.08998 0.0157 0.0239 1.0000 18.750 1.0694 0.09931 0.09280 0.0147 0.0237 1.0000 19.000 1.0739 0.10214 0.09574 0.0137 0.0235 1.0000 19.250 1.0774 0.10516 0.09886 0.0125 0.0232 1.0000