ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA213 AIRFOIL (oa213-il) Reynolds number: 500,000 Max Cl/Cd: 75.82 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa213-il-500000-n5.txt Download as CSV file: xf-oa213-il-500000-n5.csv |
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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5653 0.08574 0.08338 0.0186 0.7905 0.0081
-8.250 -0.5820 0.07778 0.07539 0.0103 0.7865 0.0081
-8.000 -0.5948 0.06914 0.06665 0.0043 0.7825 0.0081
-7.750 -0.6005 0.06116 0.05849 0.0007 0.7788 0.0081
-7.500 -0.6035 0.05265 0.04969 -0.0013 0.7756 0.0081
-7.250 -0.6406 0.02792 0.02332 0.0005 0.7737 0.0087
-7.000 -0.6231 0.02366 0.01841 0.0015 0.7702 0.0089
-6.750 -0.5997 0.02138 0.01573 0.0020 0.7660 0.0092
-6.500 -0.5746 0.01977 0.01382 0.0024 0.7620 0.0094
-6.250 -0.5487 0.01855 0.01233 0.0027 0.7582 0.0097
-6.000 -0.5217 0.01758 0.01116 0.0029 0.7544 0.0099
-5.750 -0.4945 0.01663 0.01008 0.0030 0.7497 0.0102
-5.500 -0.4671 0.01596 0.00934 0.0031 0.7452 0.0105
-5.250 -0.4395 0.01542 0.00871 0.0032 0.7412 0.0108
-5.000 -0.4111 0.01489 0.00813 0.0031 0.7364 0.0112
-4.750 -0.3828 0.01436 0.00752 0.0031 0.7312 0.0116
-4.500 -0.3547 0.01385 0.00692 0.0031 0.7265 0.0121
-4.250 -0.3261 0.01342 0.00641 0.0031 0.7216 0.0126
-4.000 -0.2975 0.01297 0.00595 0.0030 0.7158 0.0134
-3.750 -0.2688 0.01266 0.00560 0.0029 0.7104 0.0142
-3.500 -0.2398 0.01231 0.00520 0.0027 0.7047 0.0151
-3.250 -0.2107 0.01196 0.00480 0.0026 0.6982 0.0159
-3.000 -0.1818 0.01163 0.00443 0.0024 0.6905 0.0171
-2.750 -0.1525 0.01137 0.00410 0.0022 0.6777 0.0185
-2.500 -0.1230 0.01111 0.00379 0.0020 0.6630 0.0203
-2.250 -0.0933 0.01091 0.00355 0.0017 0.6512 0.0230
-2.000 -0.0636 0.01071 0.00332 0.0014 0.6404 0.0265
-1.500 -0.0039 0.01036 0.00293 0.0006 0.6175 0.0385
-1.250 0.0261 0.01021 0.00278 0.0002 0.6057 0.0498
-1.000 0.0561 0.01007 0.00265 -0.0003 0.5932 0.0676
-0.750 0.0862 0.00991 0.00254 -0.0008 0.5797 0.0950
-0.250 0.1455 0.00923 0.00233 -0.0020 0.5511 0.2732
0.000 0.1689 0.00753 0.00223 -0.0020 0.5367 0.7438
0.250 0.1951 0.00744 0.00234 -0.0013 0.5199 0.8316
0.500 0.2227 0.00751 0.00239 -0.0010 0.5026 0.8653
0.750 0.2508 0.00762 0.00243 -0.0009 0.4831 0.8859
1.000 0.2784 0.00776 0.00249 -0.0006 0.4598 0.9038
1.250 0.3046 0.00793 0.00256 -0.0001 0.4349 0.9235
1.500 0.3327 0.00811 0.00261 -0.0001 0.4088 0.9324
1.750 0.3628 0.00835 0.00267 -0.0008 0.3793 0.9368
2.000 0.3929 0.00861 0.00276 -0.0015 0.3517 0.9414
2.250 0.4225 0.00885 0.00286 -0.0021 0.3284 0.9456
3.000 0.5120 0.00947 0.00317 -0.0040 0.2806 0.9598
3.250 0.5426 0.00968 0.00329 -0.0048 0.2675 0.9649
3.750 0.6053 0.01010 0.00357 -0.0068 0.2467 0.9744
4.000 0.6375 0.01029 0.00371 -0.0080 0.2381 0.9789
4.250 0.6696 0.01051 0.00387 -0.0092 0.2297 0.9838
4.500 0.7029 0.01074 0.00404 -0.0107 0.2211 0.9880
4.750 0.7357 0.01097 0.00422 -0.0121 0.2140 0.9931
5.000 0.7686 0.01118 0.00441 -0.0135 0.2077 0.9983
5.500 0.8246 0.01164 0.00480 -0.0144 0.1974 1.0000
5.750 0.8523 0.01188 0.00501 -0.0148 0.1925 1.0000
6.000 0.8798 0.01217 0.00526 -0.0152 0.1874 1.0000
6.250 0.9076 0.01240 0.00549 -0.0156 0.1834 1.0000
6.500 0.9352 0.01266 0.00573 -0.0159 0.1788 1.0000
6.750 0.9625 0.01296 0.00601 -0.0163 0.1744 1.0000
7.000 0.9897 0.01325 0.00630 -0.0167 0.1711 1.0000
7.250 1.0169 0.01351 0.00658 -0.0170 0.1680 1.0000
7.500 1.0438 0.01381 0.00689 -0.0174 0.1647 1.0000
7.750 1.0703 0.01415 0.00722 -0.0177 0.1615 1.0000
8.000 1.0962 0.01454 0.00760 -0.0179 0.1583 1.0000
8.250 1.1226 0.01483 0.00794 -0.0182 0.1562 1.0000
8.500 1.1486 0.01515 0.00829 -0.0184 0.1536 1.0000
8.750 1.1739 0.01553 0.00867 -0.0186 0.1495 1.0000
9.000 1.1980 0.01601 0.00912 -0.0188 0.1446 1.0000
9.250 1.2232 0.01634 0.00951 -0.0189 0.1419 1.0000
9.500 1.2477 0.01674 0.00993 -0.0191 0.1388 1.0000
9.750 1.2711 0.01721 0.01042 -0.0192 0.1348 1.0000
10.000 1.2934 0.01778 0.01099 -0.0193 0.1313 1.0000
10.250 1.3165 0.01822 0.01150 -0.0193 0.1291 1.0000
10.500 1.3383 0.01873 0.01206 -0.0193 0.1263 1.0000
10.750 1.3576 0.01931 0.01267 -0.0189 0.1232 1.0000
11.000 1.3739 0.02004 0.01339 -0.0182 0.1190 1.0000
11.250 1.3929 0.02061 0.01402 -0.0178 0.1158 1.0000
11.500 1.4105 0.02131 0.01476 -0.0173 0.1114 1.0000
11.750 1.4262 0.02216 0.01561 -0.0167 0.1069 1.0000
12.000 1.4432 0.02292 0.01642 -0.0162 0.1019 1.0000
12.250 1.4569 0.02395 0.01744 -0.0156 0.0947 1.0000
12.500 1.4659 0.02538 0.01880 -0.0148 0.0786 1.0000
12.750 1.4484 0.02912 0.02223 -0.0128 0.0362 1.0000
13.000 1.4471 0.03158 0.02471 -0.0118 0.0272 1.0000
13.250 1.4520 0.03355 0.02674 -0.0112 0.0240 1.0000
13.500 1.4579 0.03546 0.02874 -0.0108 0.0223 1.0000
13.750 1.4620 0.03761 0.03098 -0.0105 0.0210 1.0000
14.000 1.4660 0.03980 0.03326 -0.0102 0.0201 1.0000
14.250 1.4702 0.04204 0.03562 -0.0102 0.0194 1.0000
14.500 1.4724 0.04455 0.03824 -0.0102 0.0188 1.0000
14.750 1.4727 0.04738 0.04117 -0.0104 0.0182 1.0000
15.000 1.4709 0.05060 0.04450 -0.0109 0.0177 1.0000
15.250 1.4668 0.05420 0.04822 -0.0115 0.0172 1.0000
15.500 1.4595 0.05838 0.05253 -0.0125 0.0168 1.0000
15.750 1.4493 0.06311 0.05740 -0.0139 0.0164 1.0000
16.000 1.4411 0.06769 0.06210 -0.0152 0.0162 1.0000
16.250 1.4302 0.07280 0.06736 -0.0170 0.0161 1.0000
16.500 1.4165 0.07851 0.07321 -0.0190 0.0159 1.0000
16.750 1.3995 0.08485 0.07971 -0.0213 0.0158 1.0000
17.000 1.3794 0.09185 0.08687 -0.0241 0.0157 1.0000
17.250 1.3567 0.09947 0.09465 -0.0271 0.0157 1.0000
17.500 1.3318 0.10754 0.10288 -0.0304 0.0157 1.0000
17.750 1.3066 0.11585 0.11134 -0.0339 0.0157 1.0000
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