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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5395 0.10066 0.09885 0.0314 0.8019 0.0112 -8.500 -0.5400 0.09587 0.09407 0.0284 0.7985 0.0114 -7.250 -0.6422 0.03052 0.02701 0.0024 0.7824 0.0101 -6.750 -0.6092 0.02266 0.01822 0.0043 0.7756 0.0099 -6.500 -0.5860 0.02048 0.01568 0.0049 0.7719 0.0100 -6.250 -0.5606 0.01881 0.01372 0.0052 0.7682 0.0100 -6.000 -0.5367 0.01637 0.01098 0.0057 0.7643 0.0104 -5.750 -0.5094 0.01567 0.01020 0.0058 0.7603 0.0107 -5.500 -0.4817 0.01502 0.00945 0.0059 0.7562 0.0110 -5.250 -0.4535 0.01429 0.00863 0.0059 0.7520 0.0113 -5.000 -0.4252 0.01364 0.00791 0.0059 0.7474 0.0117 -4.750 -0.3969 0.01305 0.00721 0.0060 0.7429 0.0121 -4.500 -0.3682 0.01257 0.00665 0.0059 0.7383 0.0125 -4.250 -0.3394 0.01207 0.00608 0.0059 0.7331 0.0128 -4.000 -0.3115 0.01132 0.00528 0.0059 0.7280 0.0134 -3.750 -0.2825 0.01098 0.00491 0.0058 0.7222 0.0140 -3.500 -0.2532 0.01065 0.00454 0.0056 0.7132 0.0147 -3.250 -0.2238 0.01035 0.00419 0.0055 0.7032 0.0154 -3.000 -0.1946 0.00995 0.00373 0.0053 0.6945 0.0165 -2.750 -0.1649 0.00972 0.00350 0.0050 0.6865 0.0179 -2.500 -0.1350 0.00955 0.00328 0.0047 0.6781 0.0193 -2.250 -0.1053 0.00923 0.00295 0.0044 0.6698 0.0216 -1.750 -0.0452 0.00886 0.00253 0.0037 0.6515 0.0282 -1.500 -0.0151 0.00867 0.00234 0.0033 0.6420 0.0359 -1.250 0.0151 0.00851 0.00220 0.0029 0.6312 0.0485 -1.000 0.0453 0.00833 0.00209 0.0024 0.6208 0.0707 -0.750 0.0756 0.00814 0.00199 0.0019 0.6095 0.1077 -0.500 0.1057 0.00783 0.00190 0.0012 0.5973 0.1878 -0.250 0.1345 0.00688 0.00177 0.0003 0.5855 0.4536 0.000 0.1611 0.00578 0.00173 0.0002 0.5728 0.7865 0.250 0.1903 0.00575 0.00177 0.0001 0.5585 0.8319 0.500 0.2196 0.00579 0.00181 0.0000 0.5444 0.8606 0.750 0.2480 0.00584 0.00186 0.0001 0.5292 0.8847 1.000 0.2764 0.00593 0.00191 0.0001 0.5111 0.9030 1.250 0.3048 0.00604 0.00195 0.0002 0.4911 0.9159 1.500 0.3330 0.00618 0.00200 0.0002 0.4700 0.9283 1.750 0.3591 0.00631 0.00206 0.0008 0.4469 0.9427 2.000 0.3874 0.00649 0.00212 0.0006 0.4191 0.9493 2.250 0.4175 0.00673 0.00219 -0.0001 0.3868 0.9541 2.500 0.4472 0.00697 0.00228 -0.0007 0.3560 0.9587 2.750 0.4761 0.00718 0.00237 -0.0010 0.3314 0.9640 3.250 0.5358 0.00759 0.00256 -0.0023 0.2940 0.9749 3.500 0.5668 0.00779 0.00267 -0.0032 0.2783 0.9802 4.000 0.6333 0.00817 0.00290 -0.0059 0.2532 0.9882 4.250 0.6671 0.00836 0.00304 -0.0075 0.2432 0.9920 4.500 0.7014 0.00859 0.00319 -0.0092 0.2331 0.9952 4.750 0.7361 0.00876 0.00333 -0.0109 0.2255 0.9978 5.000 0.7691 0.00900 0.00350 -0.0124 0.2167 1.0000 5.250 0.7958 0.00915 0.00363 -0.0125 0.2111 1.0000 5.500 0.8242 0.00938 0.00380 -0.0130 0.2039 1.0000 5.750 0.8532 0.00957 0.00396 -0.0136 0.1987 1.0000 6.000 0.8822 0.00977 0.00414 -0.0142 0.1935 1.0000 6.250 0.9111 0.01005 0.00436 -0.0148 0.1872 1.0000 6.500 0.9401 0.01022 0.00454 -0.0154 0.1840 1.0000 6.750 0.9688 0.01043 0.00474 -0.0159 0.1798 1.0000 7.000 0.9973 0.01071 0.00498 -0.0165 0.1750 1.0000 7.250 1.0257 0.01096 0.00524 -0.0170 0.1713 1.0000 7.500 1.0541 0.01117 0.00545 -0.0175 0.1685 1.0000 7.750 1.0822 0.01142 0.00569 -0.0180 0.1650 1.0000 8.000 1.1096 0.01177 0.00601 -0.0185 0.1594 1.0000 8.250 1.1375 0.01198 0.00623 -0.0189 0.1561 1.0000 8.500 1.1651 0.01223 0.00649 -0.0194 0.1531 1.0000 8.750 1.1922 0.01253 0.00678 -0.0198 0.1496 1.0000 9.000 1.2184 0.01294 0.00716 -0.0202 0.1451 1.0000 9.250 1.2456 0.01317 0.00743 -0.0205 0.1430 1.0000 9.500 1.2723 0.01343 0.00772 -0.0209 0.1406 1.0000 9.750 1.2984 0.01376 0.00805 -0.0212 0.1377 1.0000 10.000 1.3237 0.01416 0.00844 -0.0214 0.1340 1.0000 10.250 1.3488 0.01454 0.00885 -0.0216 0.1308 1.0000 10.500 1.3745 0.01482 0.00916 -0.0219 0.1282 1.0000 10.750 1.3992 0.01520 0.00955 -0.0221 0.1248 1.0000 11.000 1.4225 0.01571 0.01006 -0.0223 0.1205 1.0000 11.250 1.4465 0.01613 0.01051 -0.0225 0.1172 1.0000 11.500 1.4690 0.01664 0.01101 -0.0227 0.1116 1.0000 11.750 1.4893 0.01728 0.01164 -0.0226 0.1045 1.0000 12.000 1.5023 0.01823 0.01250 -0.0216 0.0907 1.0000 12.250 1.4913 0.02101 0.01493 -0.0189 0.0481 1.0000 12.500 1.4854 0.02360 0.01743 -0.0168 0.0275 1.0000 12.750 1.4944 0.02504 0.01891 -0.0160 0.0240 1.0000 13.000 1.5040 0.02645 0.02037 -0.0152 0.0224 1.0000 13.250 1.5112 0.02810 0.02207 -0.0144 0.0207 1.0000 13.500 1.5208 0.02955 0.02360 -0.0139 0.0199 1.0000 13.750 1.5300 0.03108 0.02521 -0.0134 0.0193 1.0000 14.000 1.5375 0.03278 0.02698 -0.0129 0.0187 1.0000 14.250 1.5430 0.03472 0.02900 -0.0125 0.0181 1.0000 14.500 1.5460 0.03695 0.03131 -0.0121 0.0176 1.0000 14.750 1.5451 0.03964 0.03409 -0.0119 0.0169 1.0000 15.000 1.5408 0.04281 0.03739 -0.0118 0.0164 1.0000 15.250 1.5439 0.04529 0.03995 -0.0120 0.0162 1.0000 15.500 1.5449 0.04809 0.04286 -0.0123 0.0159 1.0000 15.750 1.5443 0.05122 0.04609 -0.0128 0.0156 1.0000 16.000 1.5418 0.05464 0.04960 -0.0135 0.0153 1.0000 16.250 1.5376 0.05838 0.05344 -0.0143 0.0149 1.0000 16.500 1.5308 0.06261 0.05778 -0.0155 0.0146 1.0000 16.750 1.5208 0.06737 0.06264 -0.0169 0.0143 1.0000 17.000 1.5064 0.07290 0.06830 -0.0187 0.0142 1.0000 17.250 1.4887 0.07913 0.07466 -0.0208 0.0140 1.0000 17.500 1.4672 0.08605 0.08172 -0.0233 0.0139 1.0000 17.750 1.4430 0.09363 0.08945 -0.0262 0.0139 1.0000 18.000 1.4163 0.10177 0.09775 -0.0294 0.0139 1.0000 18.250 1.3880 0.11029 0.10642 -0.0328 0.0140 1.0000 18.500 1.3604 0.11889 0.11516 -0.0364 0.0140 1.0000