XFOIL Version 6.96 Calculated polar for: NREL's S809 Airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.000 -0.3992 0.16006 0.15751 -0.0156 0.7720 0.0155 -17.750 -0.4079 0.15215 0.14959 -0.0203 0.7665 0.0161 -11.500 -0.6189 0.04377 0.03655 -0.0617 0.6633 0.0097 -11.250 -0.5860 0.04451 0.03728 -0.0603 0.6604 0.0101 -11.000 -0.5621 0.04466 0.03741 -0.0591 0.6580 0.0102 -10.750 -0.5447 0.04405 0.03677 -0.0587 0.6559 0.0105 -10.500 -0.5268 0.04369 0.03639 -0.0577 0.6537 0.0106 -10.250 -0.5115 0.04291 0.03560 -0.0573 0.6518 0.0112 -10.000 -0.4961 0.04213 0.03478 -0.0569 0.6500 0.0117 -9.750 -0.4845 0.04130 0.03392 -0.0557 0.6483 0.0118 -9.500 -0.4724 0.04032 0.03288 -0.0551 0.6467 0.0122 -9.250 -0.4626 0.03919 0.03171 -0.0543 0.6452 0.0121 -9.000 -0.4523 0.03806 0.03053 -0.0537 0.6436 0.0124 -8.750 -0.4464 0.03661 0.02905 -0.0528 0.6425 0.0124 -8.500 -0.4437 0.03492 0.02734 -0.0517 0.6413 0.0129 -8.250 -0.4412 0.03328 0.02568 -0.0506 0.6400 0.0134 -8.000 -0.4363 0.03183 0.02422 -0.0495 0.6387 0.0149 -7.750 -0.4298 0.03055 0.02290 -0.0485 0.6376 0.0150 -7.500 -0.4241 0.02926 0.02156 -0.0474 0.6365 0.0160 -7.250 -0.4247 0.02760 0.01988 -0.0458 0.6354 0.0184 -7.000 -0.4257 0.02592 0.01819 -0.0441 0.6344 0.0240 -6.750 -0.4352 0.02378 0.01612 -0.0417 0.6334 0.0433 -6.500 -0.4597 0.02075 0.01327 -0.0383 0.6325 0.0911 -6.250 -0.4872 0.01788 0.01051 -0.0341 0.6316 0.1316 -6.000 -0.5147 0.01444 0.00733 -0.0314 0.6307 0.2250 -5.750 -0.5255 0.01121 0.00508 -0.0294 0.6298 0.4604 -5.500 -0.4954 0.01172 0.00554 -0.0300 0.6288 0.4870 -5.000 -0.4319 0.01373 0.00765 -0.0307 0.6271 0.5106 -4.750 -0.4013 0.01452 0.00838 -0.0311 0.6265 0.5184 -4.500 -0.3701 0.01496 0.00890 -0.0315 0.6258 0.5212 -4.250 -0.3414 0.01485 0.00874 -0.0321 0.6251 0.5221 -4.000 -0.3126 0.01475 0.00859 -0.0327 0.6244 0.5230 -3.750 -0.2838 0.01465 0.00844 -0.0333 0.6237 0.5239 -3.500 -0.2550 0.01455 0.00830 -0.0340 0.6231 0.5250 -3.250 -0.2262 0.01445 0.00815 -0.0346 0.6222 0.5261 -3.000 -0.1974 0.01435 0.00800 -0.0353 0.6213 0.5272 -2.750 -0.1685 0.01426 0.00787 -0.0359 0.6205 0.5285 -2.500 -0.1395 0.01419 0.00775 -0.0366 0.6198 0.5299 -2.250 -0.1105 0.01414 0.00764 -0.0373 0.6192 0.5311 -2.000 -0.0814 0.01409 0.00754 -0.0380 0.6185 0.5321 -1.750 -0.0524 0.01399 0.00739 -0.0387 0.6179 0.5331 -1.500 -0.0235 0.01383 0.00724 -0.0394 0.6173 0.5341 -1.250 0.0056 0.01377 0.00719 -0.0400 0.6168 0.5350 -1.000 0.0348 0.01376 0.00718 -0.0407 0.6162 0.5359 -0.750 0.0641 0.01376 0.00719 -0.0413 0.6157 0.5368 -0.500 0.0934 0.01378 0.00721 -0.0420 0.6151 0.5377 -0.250 0.1226 0.01381 0.00724 -0.0426 0.6145 0.5387 0.000 0.1519 0.01386 0.00729 -0.0433 0.6137 0.5398 0.250 0.1812 0.01394 0.00738 -0.0439 0.6130 0.5410 0.500 0.2103 0.01404 0.00749 -0.0446 0.6125 0.5423 0.750 0.2394 0.01415 0.00761 -0.0453 0.6119 0.5435 1.000 0.2685 0.01415 0.00764 -0.0459 0.6113 0.5446 1.250 0.2975 0.01414 0.00765 -0.0466 0.6103 0.5457 1.500 0.3265 0.01415 0.00769 -0.0472 0.6092 0.5467 1.750 0.3555 0.01420 0.00776 -0.0478 0.6081 0.5476 2.000 0.3844 0.01419 0.00778 -0.0485 0.6071 0.5485 2.250 0.4131 0.01415 0.00781 -0.0490 0.6059 0.5497 2.500 0.4418 0.01418 0.00791 -0.0496 0.6048 0.5508 2.750 0.4706 0.01423 0.00803 -0.0501 0.6035 0.5519 3.000 0.4996 0.01426 0.00812 -0.0506 0.6019 0.5530 3.250 0.5289 0.01426 0.00815 -0.0511 0.5999 0.5541 3.500 0.5584 0.01429 0.00819 -0.0517 0.5978 0.5552 3.750 0.5871 0.01439 0.00833 -0.0522 0.5951 0.5563 4.000 0.6152 0.01425 0.00827 -0.0525 0.5914 0.5575 4.250 0.6442 0.01407 0.00813 -0.0529 0.5870 0.5586 4.500 0.6745 0.01386 0.00790 -0.0534 0.5827 0.5598 4.750 0.7033 0.01378 0.00784 -0.0538 0.5781 0.5611 5.000 0.7310 0.01353 0.00766 -0.0539 0.5719 0.5623 5.250 0.7610 0.01332 0.00744 -0.0544 0.5671 0.5633 5.500 0.7893 0.01315 0.00732 -0.0547 0.5626 0.5645 5.750 0.8160 0.01285 0.00716 -0.0546 0.5560 0.5657 6.000 0.8446 0.01254 0.00685 -0.0548 0.5486 0.5668 6.250 0.8703 0.01229 0.00676 -0.0545 0.5398 0.5679 6.500 0.8970 0.01207 0.00662 -0.0544 0.5305 0.5690 6.750 0.9232 0.01187 0.00654 -0.0541 0.5162 0.5702 7.000 0.9468 0.01166 0.00632 -0.0534 0.4731 0.5715 7.250 0.9485 0.01260 0.00670 -0.0492 0.3779 0.5727 7.500 0.9493 0.01382 0.00754 -0.0451 0.3042 0.5739 7.750 0.9494 0.01493 0.00835 -0.0411 0.2451 0.5751 8.000 0.9473 0.01583 0.00904 -0.0366 0.2033 0.5763 8.250 0.9442 0.01675 0.00980 -0.0320 0.1690 0.5772 8.500 0.9435 0.01782 0.01072 -0.0283 0.1400 0.5781 8.750 0.9435 0.01897 0.01176 -0.0251 0.1163 0.5788 9.000 0.9437 0.02018 0.01290 -0.0223 0.0961 0.5801 9.250 0.9448 0.02155 0.01422 -0.0201 0.0805 0.5812 9.500 0.9477 0.02302 0.01566 -0.0184 0.0669 0.5823 9.750 0.9512 0.02458 0.01721 -0.0169 0.0563 0.5835 10.000 0.9567 0.02611 0.01873 -0.0158 0.0481 0.5846 10.250 0.9638 0.02757 0.02022 -0.0148 0.0423 0.5859 10.500 0.9668 0.02935 0.02200 -0.0136 0.0374 0.5871 10.750 0.9770 0.03062 0.02334 -0.0129 0.0343 0.5884 11.000 0.9827 0.03225 0.02496 -0.0120 0.0310 0.5899 11.250 0.9887 0.03388 0.02664 -0.0112 0.0286 0.5913 11.500 0.9974 0.03533 0.02815 -0.0105 0.0269 0.5926 11.750 1.0044 0.03694 0.02977 -0.0099 0.0250 0.5939 12.000 1.0031 0.03921 0.03208 -0.0088 0.0234 0.5951 12.250 1.0132 0.04059 0.03358 -0.0084 0.0226 0.5966 12.500 1.0220 0.04212 0.03520 -0.0080 0.0215 0.5980 12.750 1.0304 0.04374 0.03688 -0.0076 0.0205 0.5995 13.000 1.0371 0.04554 0.03873 -0.0072 0.0196 0.6009 13.250 1.0364 0.04803 0.04126 -0.0066 0.0185 0.6024 13.500 1.0452 0.04976 0.04308 -0.0064 0.0180 0.6039 13.750 1.0549 0.05145 0.04485 -0.0063 0.0173 0.6057 14.000 1.0626 0.05334 0.04683 -0.0062 0.0167 0.6073 14.250 1.0713 0.05522 0.04876 -0.0062 0.0160 0.6089 14.500 1.0799 0.05712 0.05070 -0.0065 0.0151 0.6107 14.750 1.0838 0.05949 0.05315 -0.0065 0.0147 0.6124 15.000 1.0866 0.06199 0.05576 -0.0063 0.0141 0.6142 15.250 1.0952 0.06406 0.05795 -0.0067 0.0136 0.6163 15.500 1.1021 0.06635 0.06036 -0.0071 0.0131 0.6185 15.750 1.1082 0.06877 0.06286 -0.0076 0.0126 0.6209 16.000 1.1149 0.07120 0.06535 -0.0084 0.0120 0.6232 16.250 1.1188 0.07394 0.06815 -0.0091 0.0116 0.6254 16.500 1.1171 0.07737 0.07165 -0.0098 0.0109 0.6275 16.750 1.1216 0.08027 0.07470 -0.0107 0.0106 0.6300 17.000 1.1255 0.08335 0.07794 -0.0119 0.0102 0.6326 17.250 1.1276 0.08669 0.08141 -0.0131 0.0098 0.6352 17.500 1.1296 0.09009 0.08491 -0.0145 0.0094 0.6381 17.750 1.1308 0.09372 0.08862 -0.0161 0.0091 0.6408 18.000 1.1307 0.09757 0.09259 -0.0178 0.0088 0.6437 18.250 1.1292 0.10166 0.09679 -0.0196 0.0086 0.6466 18.500 1.1243 0.10630 0.10154 -0.0216 0.0084 0.6497 18.750 1.1179 0.11131 0.10668 -0.0239 0.0081 0.6526