XFOIL Version 6.96 Calculated polar for: ONERA OA213 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5254 0.09059 0.08846 0.0115 0.8335 0.0193 -8.250 -0.5332 0.08293 0.08077 0.0028 0.8290 0.0193 -8.000 -0.5419 0.07795 0.07574 0.0011 0.8254 0.0195 -7.750 -0.5411 0.07453 0.07226 0.0004 0.8223 0.0196 -7.500 -0.5350 0.07127 0.06896 -0.0008 0.8185 0.0198 -7.250 -0.5275 0.06776 0.06540 -0.0022 0.8142 0.0201 -7.000 -0.5191 0.06414 0.06168 -0.0033 0.8105 0.0204 -6.750 -0.5097 0.06027 0.05767 -0.0043 0.8072 0.0210 -6.500 -0.4981 0.05566 0.05289 -0.0054 0.8038 0.0219 -6.250 -0.4908 0.04551 0.04218 -0.0064 0.7999 0.0238 -6.000 -0.4727 0.04349 0.04009 -0.0064 0.7956 0.0241 -5.750 -0.4540 0.04142 0.03790 -0.0062 0.7920 0.0246 -5.500 -0.4344 0.03894 0.03523 -0.0057 0.7887 0.0255 -5.250 -0.4230 0.02501 0.01973 -0.0024 0.7852 0.0197 -5.000 -0.3973 0.02261 0.01714 -0.0020 0.7806 0.0185 -4.750 -0.3722 0.01982 0.01391 -0.0012 0.7767 0.0181 -4.500 -0.3459 0.01802 0.01177 -0.0004 0.7732 0.0183 -4.250 -0.3170 0.01676 0.01029 -0.0003 0.7681 0.0188 -4.000 -0.2885 0.01593 0.00928 -0.0001 0.7631 0.0193 -3.750 -0.2620 0.01467 0.00795 0.0003 0.7588 0.0200 -3.500 -0.2336 0.01417 0.00744 0.0003 0.7538 0.0212 -3.250 -0.2046 0.01369 0.00691 0.0002 0.7479 0.0227 -3.000 -0.1775 0.01296 0.00608 0.0007 0.7418 0.0238 -2.750 -0.1491 0.01237 0.00551 0.0007 0.7325 0.0255 -2.500 -0.1213 0.01196 0.00500 0.0010 0.7244 0.0275 -2.250 -0.0920 0.01142 0.00449 0.0008 0.7158 0.0304 -2.000 -0.0635 0.01108 0.00410 0.0008 0.7089 0.0348 -1.750 -0.0336 0.01075 0.00379 0.0005 0.7002 0.0409 -1.500 -0.0048 0.01040 0.00345 0.0005 0.6928 0.0521 -1.250 0.0251 0.01005 0.00321 0.0001 0.6835 0.0763 -1.000 0.0540 0.00966 0.00299 -0.0002 0.6752 0.1328 -0.750 0.0814 0.00852 0.00276 -0.0009 0.6654 0.3963 -0.500 0.1024 0.00706 0.00274 0.0004 0.6564 0.8057 -0.250 0.1283 0.00702 0.00276 0.0014 0.6464 0.8593 0.000 0.1540 0.00703 0.00279 0.0024 0.6357 0.8915 0.250 0.1767 0.00706 0.00282 0.0042 0.6248 0.9187 0.500 0.1992 0.00711 0.00280 0.0059 0.6135 0.9406 0.750 0.2233 0.00712 0.00277 0.0073 0.6013 0.9563 1.000 0.2515 0.00716 0.00273 0.0076 0.5877 0.9701 1.250 0.2919 0.00730 0.00277 0.0054 0.5717 0.9824 1.500 0.3354 0.00745 0.00281 0.0022 0.5545 0.9858 1.750 0.3724 0.00757 0.00280 0.0001 0.5354 0.9874 2.000 0.4087 0.00770 0.00281 -0.0019 0.5137 0.9893 2.250 0.4445 0.00786 0.00284 -0.0038 0.4892 0.9915 2.500 0.4800 0.00806 0.00290 -0.0057 0.4620 0.9939 2.750 0.5170 0.00832 0.00298 -0.0080 0.4284 0.9954 3.000 0.5536 0.00866 0.00311 -0.0104 0.3911 0.9971 3.250 0.5896 0.00903 0.00327 -0.0126 0.3572 0.9989 3.500 0.6212 0.00933 0.00342 -0.0139 0.3316 1.0000 3.750 0.6468 0.00959 0.00356 -0.0140 0.3122 1.0000 4.000 0.6715 0.00985 0.00370 -0.0140 0.2958 1.0000 4.250 0.6959 0.01009 0.00386 -0.0138 0.2817 1.0000 4.500 0.7203 0.01032 0.00402 -0.0136 0.2696 1.0000 4.750 0.7452 0.01058 0.00421 -0.0134 0.2592 1.0000 5.000 0.7713 0.01086 0.00442 -0.0135 0.2495 1.0000 5.250 0.7984 0.01110 0.00463 -0.0138 0.2414 1.0000 5.500 0.8257 0.01143 0.00488 -0.0142 0.2332 1.0000 5.750 0.8534 0.01167 0.00511 -0.0145 0.2266 1.0000 6.000 0.8809 0.01199 0.00538 -0.0150 0.2196 1.0000 6.250 0.9085 0.01228 0.00565 -0.0154 0.2136 1.0000 6.500 0.9361 0.01257 0.00592 -0.0158 0.2077 1.0000 6.750 0.9627 0.01301 0.00630 -0.0161 0.2018 1.0000 7.000 0.9903 0.01324 0.00656 -0.0165 0.1979 1.0000 7.250 1.0172 0.01355 0.00688 -0.0168 0.1934 1.0000 7.500 1.0433 0.01398 0.00727 -0.0171 0.1889 1.0000 7.750 1.0694 0.01436 0.00767 -0.0174 0.1852 1.0000 8.000 1.0959 0.01466 0.00800 -0.0176 0.1819 1.0000 8.250 1.1217 0.01503 0.00839 -0.0178 0.1784 1.0000 8.500 1.1464 0.01551 0.00884 -0.0180 0.1748 1.0000 8.750 1.1710 0.01595 0.00930 -0.0181 0.1709 1.0000 9.000 1.1970 0.01621 0.00962 -0.0183 0.1670 1.0000 9.250 1.2214 0.01661 0.01003 -0.0185 0.1634 1.0000 9.500 1.2440 0.01718 0.01059 -0.0185 0.1600 1.0000 9.750 1.2673 0.01767 0.01112 -0.0185 0.1569 1.0000 10.000 1.2914 0.01804 0.01156 -0.0187 0.1540 1.0000 10.250 1.3142 0.01850 0.01207 -0.0187 0.1512 1.0000 10.500 1.3349 0.01909 0.01268 -0.0186 0.1484 1.0000 10.750 1.3508 0.01986 0.01344 -0.0178 0.1454 1.0000 11.000 1.3707 0.02034 0.01400 -0.0174 0.1428 1.0000 11.250 1.3909 0.02082 0.01456 -0.0171 0.1400 1.0000 11.500 1.4096 0.02141 0.01521 -0.0167 0.1368 1.0000 11.750 1.4258 0.02221 0.01601 -0.0162 0.1335 1.0000 12.000 1.4426 0.02297 0.01683 -0.0157 0.1305 1.0000 12.250 1.4627 0.02349 0.01745 -0.0155 0.1268 1.0000 12.500 1.4789 0.02432 0.01828 -0.0151 0.1212 1.0000 12.750 1.4964 0.02507 0.01908 -0.0149 0.1150 1.0000 13.000 1.5101 0.02612 0.02010 -0.0144 0.1055 1.0000 13.250 1.5175 0.02773 0.02159 -0.0137 0.0858 1.0000 13.750 1.4882 0.03508 0.02861 -0.0109 0.0330 1.0000 14.000 1.4872 0.03772 0.03134 -0.0104 0.0297 1.0000 14.250 1.4878 0.04026 0.03400 -0.0101 0.0281 1.0000 14.500 1.4854 0.04323 0.03708 -0.0100 0.0269 1.0000 14.750 1.4797 0.04668 0.04065 -0.0101 0.0258 1.0000 15.000 1.4715 0.05067 0.04477 -0.0107 0.0249 1.0000 15.250 1.4683 0.05418 0.04842 -0.0113 0.0244 1.0000 15.500 1.4620 0.05824 0.05261 -0.0123 0.0240 1.0000 15.750 1.4532 0.06278 0.05729 -0.0135 0.0236 1.0000 16.000 1.4415 0.06785 0.06251 -0.0151 0.0233 1.0000 16.250 1.4269 0.07353 0.06833 -0.0170 0.0230 1.0000 16.500 1.4099 0.07977 0.07473 -0.0192 0.0228 1.0000 16.750 1.3903 0.08656 0.08167 -0.0218 0.0226 1.0000 17.000 1.3686 0.09388 0.08915 -0.0246 0.0225 1.0000 17.250 1.3457 0.10153 0.09695 -0.0277 0.0225 1.0000 17.500 1.3225 0.10932 0.10489 -0.0308 0.0224 1.0000