XFOIL Version 6.96 Calculated polar for: NREL's S829 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.4472 0.06094 0.05727 -0.1050 0.9713 0.0253 -12.250 -0.4702 0.05471 0.05088 -0.1066 0.9694 0.0249 -12.000 -0.4938 0.04966 0.04566 -0.1064 0.9649 0.0245 -11.750 -0.5764 0.05835 0.05400 -0.1019 0.9703 0.0253 -11.500 -0.5928 0.05374 0.04918 -0.1010 0.9648 0.0244 -11.250 -0.6050 0.04975 0.04491 -0.0995 0.9595 0.0237 -11.000 -0.6159 0.04616 0.04100 -0.0969 0.9543 0.0229 -10.750 -0.6280 0.04289 0.03737 -0.0929 0.9478 0.0222 -10.500 -0.6312 0.03950 0.03355 -0.0897 0.9436 0.0212 -10.250 -0.6322 0.03638 0.02996 -0.0860 0.9387 0.0206 -10.000 -0.6204 0.03383 0.02704 -0.0841 0.9350 0.0207 -9.750 -0.5974 0.03138 0.02426 -0.0838 0.9328 0.0212 -9.500 -0.5676 0.02936 0.02196 -0.0844 0.9310 0.0218 -9.250 -0.5374 0.02775 0.02015 -0.0849 0.9294 0.0238 -9.000 -0.5119 0.02620 0.01848 -0.0849 0.9269 0.0288 -8.750 -0.4923 0.02540 0.01760 -0.0841 0.9236 0.0327 -8.500 -0.4710 0.02417 0.01631 -0.0833 0.9211 0.0392 -8.250 -0.4531 0.02364 0.01570 -0.0821 0.9184 0.0479 -8.000 -0.4376 0.02276 0.01485 -0.0807 0.9162 0.0595 -7.750 -0.4258 0.02207 0.01419 -0.0786 0.9133 0.0721 -7.500 -0.4164 0.02150 0.01369 -0.0761 0.9098 0.0887 -7.250 -0.4073 0.02087 0.01317 -0.0736 0.9065 0.1124 -7.000 -0.3998 0.02013 0.01267 -0.0707 0.9036 0.1500 -6.750 -0.3961 0.01939 0.01227 -0.0673 0.9012 0.2124 -6.500 -0.4063 0.01920 0.01240 -0.0614 0.8964 0.2695 -6.250 -0.4199 0.01885 0.01239 -0.0546 0.8923 0.3376 -6.000 -0.4351 0.01824 0.01217 -0.0471 0.8889 0.4203 -5.750 -0.4670 0.01883 0.01291 -0.0363 0.8835 0.4445 -5.500 -0.3576 0.01954 0.01475 -0.0481 0.8880 0.7224 -5.250 -0.4037 0.02045 0.01573 -0.0349 0.8813 0.7339 -5.000 -0.4058 0.02130 0.01653 -0.0287 0.8779 0.7527 -4.750 -0.3728 0.02264 0.01773 -0.0285 0.8767 0.7690 -4.500 -0.5097 0.02206 0.01739 0.0014 0.8684 0.7712 -4.250 -0.5228 0.02269 0.01797 0.0094 0.8661 0.7864 -4.000 -0.5159 0.02352 0.01871 0.0140 0.8642 0.8030 -3.750 -0.1649 0.02754 0.02198 -0.0428 0.8759 0.8059 -3.500 -0.0959 0.02840 0.02271 -0.0499 0.8764 0.8103 -3.250 -0.0677 0.02890 0.02314 -0.0500 0.8754 0.8200 -3.000 -0.0129 0.02933 0.02347 -0.0550 0.8753 0.8247 -2.750 0.0149 0.02958 0.02366 -0.0553 0.8742 0.8337 -2.500 0.0312 0.03042 0.02448 -0.0535 0.8713 0.8402 -2.000 0.0086 0.03207 0.02614 -0.0396 0.8633 0.8608 -1.750 0.0567 0.03212 0.02613 -0.0441 0.8628 0.8638 -1.500 0.0910 0.03220 0.02618 -0.0460 0.8618 0.8692 -1.250 0.1220 0.03220 0.02613 -0.0473 0.8607 0.8753 -1.000 0.0461 0.03376 0.02776 -0.0283 0.8521 0.8886 -0.750 0.0872 0.03377 0.02774 -0.0315 0.8507 0.8914 -0.500 0.1214 0.03380 0.02775 -0.0335 0.8490 0.8953 -0.250 0.1367 0.03394 0.02787 -0.0318 0.8471 0.9020 0.000 0.1874 0.03376 0.02769 -0.0369 0.8464 0.9038 0.250 0.2371 0.03361 0.02755 -0.0419 0.8458 0.9060 0.500 0.1657 0.03471 0.02867 -0.0241 0.8352 0.9165 0.750 0.2116 0.03458 0.02854 -0.0283 0.8338 0.9183 1.000 0.2574 0.03444 0.02843 -0.0324 0.8327 0.9202 1.500 0.2471 0.03504 0.02905 -0.0216 0.8204 0.9300 1.750 0.2966 0.03481 0.02886 -0.0263 0.8190 0.9311 2.000 0.3472 0.03459 0.02870 -0.0312 0.8177 0.9324 2.250 0.3279 0.03497 0.02911 -0.0234 0.8070 0.9366 2.500 0.3727 0.03466 0.02886 -0.0269 0.8051 0.9381 2.750 0.3391 0.03503 0.02922 -0.0159 0.7939 0.9429 3.000 0.3957 0.03445 0.02872 -0.0214 0.7918 0.9435 3.250 0.4751 0.03323 0.02762 -0.0305 0.7904 0.9434 3.500 0.4969 0.03265 0.02712 -0.0295 0.7792 0.9452 3.750 0.6481 0.02807 0.02275 -0.0490 0.7783 0.9434 4.000 0.6933 0.02669 0.02149 -0.0516 0.7701 0.9450 4.250 0.7577 0.02429 0.01924 -0.0569 0.7649 0.9463 4.500 0.7907 0.02294 0.01799 -0.0570 0.7539 0.9480 4.750 0.8203 0.02162 0.01676 -0.0564 0.7422 0.9490 5.000 0.8439 0.02055 0.01579 -0.0549 0.7277 0.9503 5.500 0.8696 0.01921 0.01461 -0.0481 0.6791 0.9534 5.750 0.8783 0.01849 0.01370 -0.0434 0.5906 0.9549 6.000 0.8622 0.01921 0.01343 -0.0346 0.4499 0.9574 6.250 0.8380 0.02016 0.01394 -0.0254 0.3734 0.9593 6.500 0.8141 0.02085 0.01439 -0.0163 0.3259 0.9627 6.750 0.7893 0.02163 0.01495 -0.0074 0.2844 0.9658 7.000 0.7665 0.02241 0.01555 0.0011 0.2489 0.9696 7.250 0.7639 0.02355 0.01631 0.0048 0.1860 0.9720 7.500 0.7633 0.02456 0.01706 0.0083 0.1454 0.9743 7.750 0.7644 0.02550 0.01782 0.0118 0.1195 0.9767 8.000 0.7682 0.02636 0.01862 0.0149 0.1004 0.9797 8.250 0.7712 0.02719 0.01940 0.0182 0.0873 0.9825 8.500 0.7856 0.02807 0.02024 0.0192 0.0745 0.9840 8.750 0.7987 0.02908 0.02121 0.0204 0.0653 0.9856 9.000 0.8154 0.02974 0.02193 0.0211 0.0572 0.9874 9.250 0.8315 0.03085 0.02310 0.0222 0.0510 0.9892 9.500 0.8493 0.03165 0.02394 0.0229 0.0458 0.9913 9.750 0.8691 0.03290 0.02522 0.0236 0.0401 0.9928 10.000 0.8895 0.03382 0.02626 0.0240 0.0358 0.9942 10.250 0.9149 0.03556 0.02804 0.0237 0.0304 0.9950 10.500 0.9334 0.03658 0.02928 0.0242 0.0269 0.9966 10.750 0.9468 0.03753 0.03028 0.0248 0.0241 0.9985 11.000 0.9697 0.04038 0.03337 0.0248 0.0210 0.9992 11.250 0.9810 0.04232 0.03561 0.0266 0.0200 1.0000 11.500 0.9808 0.04416 0.03773 0.0302 0.0193 1.0000 11.750 0.9760 0.04608 0.03991 0.0342 0.0187 1.0000 12.000 0.9668 0.04811 0.04218 0.0385 0.0183 1.0000 12.250 0.9545 0.05003 0.04431 0.0431 0.0180 1.0000 12.500 0.9417 0.05147 0.04589 0.0474 0.0174 1.0000 12.750 0.9200 0.05435 0.04906 0.0525 0.0179 1.0000 13.000 0.8973 0.05675 0.05166 0.0575 0.0181 1.0000 13.250 0.8768 0.05848 0.05353 0.0620 0.0179 1.0000 13.500 0.8723 0.05782 0.05274 0.0654 0.0163 1.0000 13.750 0.8498 0.05990 0.05496 0.0698 0.0163 1.0000 14.000 0.8160 0.06399 0.05935 0.0737 0.0169 1.0000 14.250 0.7725 0.07059 0.06630 0.0758 0.0188 1.0000 14.500 0.7488 0.07528 0.07116 0.0759 0.0185 1.0000 14.750 0.6392 0.07870 0.07500 0.0734 0.0197 1.0000 15.000 0.6117 0.08394 0.08035 0.0727 0.0200 1.0000 15.250 0.5809 0.09056 0.08710 0.0702 0.0202 1.0000 15.500 0.5521 0.09759 0.09423 0.0667 0.0207 1.0000 15.750 0.5205 0.10502 0.10174 0.0627 0.0214 1.0000