XFOIL Version 6.96 Calculated polar for: NACA 63-215 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -16.000 -0.8485 0.09431 0.08982 -0.0316 1.0000 0.0214 -15.750 -0.8792 0.08454 0.07978 -0.0378 1.0000 0.0214 -15.500 -0.8944 0.07830 0.07338 -0.0415 1.0000 0.0215 -15.250 -0.9083 0.07262 0.06753 -0.0447 1.0000 0.0216 -15.000 -0.9187 0.06780 0.06255 -0.0472 1.0000 0.0217 -14.750 -0.9262 0.06370 0.05832 -0.0491 1.0000 0.0219 -14.500 -0.9318 0.06002 0.05451 -0.0507 1.0000 0.0222 -14.250 -0.9375 0.05637 0.05069 -0.0520 1.0000 0.0223 -14.000 -0.9395 0.05346 0.04766 -0.0530 1.0000 0.0228 -13.750 -0.9417 0.05045 0.04450 -0.0536 1.0000 0.0230 -13.500 -0.9424 0.04778 0.04167 -0.0541 1.0000 0.0235 -13.250 -0.9418 0.04523 0.03893 -0.0543 1.0000 0.0240 -13.000 -0.9395 0.04290 0.03641 -0.0542 1.0000 0.0245 -12.750 -0.9358 0.04071 0.03402 -0.0540 1.0000 0.0250 -12.500 -0.9299 0.03874 0.03183 -0.0535 1.0000 0.0254 -12.250 -0.9202 0.03704 0.03011 -0.0530 1.0000 0.0259 -12.000 -0.9100 0.03555 0.02858 -0.0525 1.0000 0.0263 -11.750 -0.8996 0.03416 0.02715 -0.0519 1.0000 0.0269 -11.500 -0.8886 0.03281 0.02573 -0.0512 1.0000 0.0275 -11.250 -0.8773 0.03156 0.02440 -0.0505 1.0000 0.0283 -11.000 -0.8653 0.03037 0.02311 -0.0497 1.0000 0.0293 -10.750 -0.8525 0.02924 0.02185 -0.0488 1.0000 0.0302 -10.500 -0.8402 0.02806 0.02063 -0.0477 1.0000 0.0311 -10.250 -0.8292 0.02699 0.01956 -0.0466 1.0000 0.0319 -10.000 -0.8185 0.02605 0.01861 -0.0452 1.0000 0.0328 -9.750 -0.8090 0.02518 0.01772 -0.0435 1.0000 0.0337 -9.500 -0.7960 0.02432 0.01682 -0.0422 0.9938 0.0349 -9.250 -0.7657 0.02335 0.01572 -0.0441 0.9680 0.0365 -9.000 -0.7377 0.02225 0.01460 -0.0458 0.9496 0.0384 -8.750 -0.7112 0.02145 0.01374 -0.0468 0.9334 0.0406 -8.500 -0.6883 0.02075 0.01293 -0.0468 0.9179 0.0427 -8.250 -0.6686 0.02005 0.01215 -0.0461 0.9034 0.0448 -8.000 -0.6497 0.01939 0.01145 -0.0453 0.8907 0.0474 -7.750 -0.6295 0.01884 0.01081 -0.0445 0.8794 0.0503 -7.500 -0.6097 0.01827 0.01017 -0.0436 0.8683 0.0536 -7.250 -0.5897 0.01771 0.00957 -0.0427 0.8583 0.0578 -7.000 -0.5686 0.01722 0.00900 -0.0419 0.8493 0.0626 -6.750 -0.5474 0.01667 0.00844 -0.0412 0.8399 0.0697 -6.500 -0.5259 0.01614 0.00790 -0.0404 0.8319 0.0807 -6.250 -0.5036 0.01560 0.00739 -0.0399 0.8231 0.0978 -6.000 -0.4817 0.01501 0.00689 -0.0393 0.8156 0.1249 -5.750 -0.4597 0.01434 0.00640 -0.0389 0.8073 0.1653 -5.500 -0.4382 0.01362 0.00589 -0.0384 0.8000 0.2207 -5.250 -0.4162 0.01288 0.00544 -0.0381 0.7924 0.2896 -5.000 -0.3930 0.01232 0.00515 -0.0377 0.7850 0.3577 -4.750 -0.3678 0.01202 0.00496 -0.0374 0.7783 0.4094 -4.500 -0.3415 0.01183 0.00486 -0.0372 0.7708 0.4468 -4.250 -0.3150 0.01172 0.00477 -0.0369 0.7648 0.4795 -4.000 -0.2877 0.01165 0.00471 -0.0368 0.7574 0.5068 -3.750 -0.2604 0.01161 0.00466 -0.0366 0.7507 0.5260 -3.500 -0.2326 0.01159 0.00458 -0.0365 0.7444 0.5410 -3.250 -0.2047 0.01156 0.00451 -0.0365 0.7374 0.5544 -3.000 -0.1770 0.01155 0.00447 -0.0363 0.7316 0.5672 -2.750 -0.1489 0.01153 0.00443 -0.0363 0.7245 0.5774 -2.500 -0.1206 0.01150 0.00432 -0.0364 0.7181 0.5858 -2.250 -0.0924 0.01148 0.00425 -0.0364 0.7124 0.5927 -2.000 -0.0640 0.01145 0.00420 -0.0365 0.7054 0.6001 -1.750 -0.0357 0.01143 0.00411 -0.0365 0.6995 0.6071 -1.500 -0.0074 0.01142 0.00409 -0.0366 0.6933 0.6136 -1.250 0.0213 0.01141 0.00403 -0.0367 0.6869 0.6208 -1.000 0.0494 0.01140 0.00399 -0.0367 0.6814 0.6265 -0.750 0.0779 0.01140 0.00399 -0.0368 0.6747 0.6330 -0.500 0.1065 0.01140 0.00395 -0.0370 0.6688 0.6395 -0.250 0.1347 0.01141 0.00396 -0.0370 0.6636 0.6451 0.000 0.1632 0.01142 0.00398 -0.0371 0.6567 0.6519 0.250 0.1916 0.01144 0.00398 -0.0372 0.6510 0.6578 0.500 0.2198 0.01147 0.00401 -0.0372 0.6455 0.6638 0.750 0.2485 0.01150 0.00405 -0.0374 0.6391 0.6710 1.000 0.2765 0.01153 0.00409 -0.0374 0.6335 0.6766 1.250 0.3048 0.01157 0.00416 -0.0375 0.6277 0.6830 1.500 0.3333 0.01161 0.00423 -0.0376 0.6213 0.6899 1.750 0.3612 0.01166 0.00429 -0.0375 0.6159 0.6959 2.000 0.3895 0.01172 0.00439 -0.0377 0.6093 0.7030 2.250 0.4174 0.01177 0.00448 -0.0377 0.6029 0.7091 2.500 0.4453 0.01184 0.00458 -0.0376 0.5970 0.7159 2.750 0.4735 0.01191 0.00470 -0.0377 0.5898 0.7233 3.000 0.5010 0.01197 0.00481 -0.0376 0.5837 0.7293 3.250 0.5289 0.01205 0.00495 -0.0376 0.5765 0.7368 3.500 0.5563 0.01213 0.00507 -0.0375 0.5691 0.7435 3.750 0.5835 0.01220 0.00522 -0.0373 0.5600 0.7506 4.000 0.6107 0.01227 0.00529 -0.0371 0.5491 0.7580 4.250 0.6370 0.01234 0.00543 -0.0368 0.5369 0.7649 4.750 0.6898 0.01251 0.00572 -0.0362 0.5113 0.7797 5.000 0.7157 0.01262 0.00585 -0.0358 0.4943 0.7880 5.250 0.7398 0.01276 0.00598 -0.0351 0.4703 0.7953 5.500 0.7636 0.01295 0.00614 -0.0344 0.4400 0.8038 5.750 0.7860 0.01322 0.00634 -0.0334 0.4068 0.8117 6.000 0.8077 0.01358 0.00662 -0.0325 0.3679 0.8208 6.250 0.8257 0.01414 0.00699 -0.0310 0.3186 0.8293 6.500 0.8421 0.01488 0.00750 -0.0295 0.2666 0.8396 6.750 0.8560 0.01569 0.00811 -0.0276 0.2177 0.8496 7.000 0.8697 0.01652 0.00876 -0.0258 0.1751 0.8607 7.250 0.8833 0.01731 0.00941 -0.0239 0.1416 0.8733 7.750 0.9087 0.01871 0.01067 -0.0197 0.0948 0.9047 8.000 0.9207 0.01937 0.01132 -0.0175 0.0801 0.9281 8.250 0.9388 0.02010 0.01206 -0.0168 0.0683 0.9702 8.500 0.9530 0.02089 0.01284 -0.0156 0.0612 1.0000 8.750 0.9657 0.02180 0.01372 -0.0142 0.0559 1.0000 9.000 0.9791 0.02269 0.01464 -0.0130 0.0517 1.0000 9.250 0.9911 0.02369 0.01564 -0.0119 0.0478 1.0000 9.500 1.0025 0.02477 0.01674 -0.0107 0.0450 1.0000 9.750 1.0148 0.02582 0.01785 -0.0097 0.0424 1.0000 10.000 1.0254 0.02702 0.01906 -0.0087 0.0401 1.0000 10.250 1.0342 0.02839 0.02046 -0.0077 0.0382 1.0000 10.500 1.0456 0.02963 0.02179 -0.0069 0.0366 1.0000 10.750 1.0557 0.03100 0.02322 -0.0061 0.0351 1.0000 11.000 1.0649 0.03247 0.02474 -0.0054 0.0338 1.0000 11.250 1.0722 0.03415 0.02644 -0.0047 0.0327 1.0000 11.500 1.0798 0.03584 0.02819 -0.0040 0.0316 1.0000 11.750 1.0892 0.03743 0.02988 -0.0034 0.0305 1.0000 12.000 1.0981 0.03909 0.03162 -0.0029 0.0293 1.0000 12.250 1.1064 0.04082 0.03342 -0.0025 0.0284 1.0000 12.500 1.1136 0.04268 0.03531 -0.0022 0.0274 1.0000 12.750 1.1191 0.04476 0.03741 -0.0019 0.0267 1.0000 13.000 1.1272 0.04666 0.03943 -0.0016 0.0260 1.0000 13.250 1.1348 0.04865 0.04155 -0.0014 0.0252 1.0000 13.500 1.1417 0.05074 0.04375 -0.0013 0.0246 1.0000 13.750 1.1479 0.05293 0.04603 -0.0012 0.0239 1.0000 14.000 1.1538 0.05520 0.04839 -0.0013 0.0234 1.0000 14.250 1.1591 0.05758 0.05085 -0.0015 0.0230 1.0000 14.500 1.1640 0.06005 0.05339 -0.0018 0.0226 1.0000 14.750 1.1685 0.06262 0.05601 -0.0021 0.0222 1.0000 15.000 1.1726 0.06534 0.05881 -0.0024 0.0219 1.0000 15.250 1.1750 0.06838 0.06203 -0.0030 0.0216 1.0000 15.500 1.1753 0.07177 0.06561 -0.0038 0.0212 1.0000 15.750 1.1748 0.07535 0.06938 -0.0048 0.0209 1.0000 16.000 1.1720 0.07936 0.07357 -0.0062 0.0206 1.0000 16.250 1.1680 0.08364 0.07804 -0.0078 0.0203 1.0000 16.500 1.1627 0.08826 0.08284 -0.0098 0.0200 1.0000 16.750 1.1561 0.09323 0.08798 -0.0121 0.0198 1.0000 17.000 1.1484 0.09853 0.09345 -0.0148 0.0195 1.0000 17.250 1.1394 0.10423 0.09932 -0.0178 0.0193 1.0000 17.500 1.1291 0.11037 0.10563 -0.0212 0.0191 1.0000 17.750 1.1157 0.11734 0.11278 -0.0253 0.0190 1.0000 18.000 1.1004 0.12503 0.12067 -0.0300 0.0189 1.0000 18.250 1.0767 0.13499 0.13086 -0.0364 0.0189 1.0000