ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: ONERA OA213 AIRFOIL (oa213-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.74 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa213-il-1000000-n5.txt Download as CSV file: xf-oa213-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.9864 0.03145 0.02791 0.0024 0.7902 0.0056
-10.250 -0.9766 0.02784 0.02389 0.0035 0.7873 0.0056
-10.000 -0.9595 0.02554 0.02133 0.0043 0.7841 0.0057
-9.750 -0.9388 0.02395 0.01954 0.0049 0.7806 0.0058
-9.500 -0.9163 0.02265 0.01807 0.0054 0.7772 0.0059
-9.250 -0.8927 0.02157 0.01683 0.0058 0.7740 0.0059
-9.000 -0.8681 0.02061 0.01575 0.0061 0.7708 0.0060
-8.750 -0.8428 0.01975 0.01477 0.0064 0.7673 0.0061
-8.500 -0.8172 0.01892 0.01383 0.0066 0.7635 0.0062
-8.250 -0.7911 0.01819 0.01298 0.0069 0.7598 0.0063
-8.000 -0.7646 0.01752 0.01220 0.0070 0.7564 0.0064
-7.750 -0.7376 0.01691 0.01151 0.0071 0.7527 0.0066
-7.500 -0.7104 0.01631 0.01082 0.0072 0.7487 0.0068
-7.250 -0.6831 0.01573 0.01015 0.0073 0.7446 0.0069
-7.000 -0.6556 0.01517 0.00947 0.0074 0.7407 0.0071
-6.750 -0.6279 0.01460 0.00882 0.0075 0.7368 0.0073
-6.500 -0.6000 0.01409 0.00823 0.0075 0.7322 0.0074
-6.250 -0.5718 0.01364 0.00769 0.0075 0.7277 0.0075
-6.000 -0.5436 0.01315 0.00713 0.0075 0.7235 0.0077
-5.750 -0.5156 0.01260 0.00652 0.0075 0.7188 0.0080
-5.500 -0.4870 0.01222 0.00610 0.0074 0.7136 0.0082
-5.000 -0.4292 0.01159 0.00539 0.0071 0.7036 0.0088
-4.750 -0.4002 0.01129 0.00505 0.0070 0.6977 0.0091
-4.500 -0.3710 0.01101 0.00471 0.0068 0.6922 0.0094
-4.250 -0.3417 0.01074 0.00441 0.0066 0.6862 0.0097
-4.000 -0.3123 0.01051 0.00413 0.0064 0.6796 0.0100
-3.750 -0.2829 0.01021 0.00380 0.0062 0.6723 0.0106
-3.500 -0.2531 0.01002 0.00356 0.0059 0.6587 0.0112
-3.250 -0.2231 0.00987 0.00334 0.0055 0.6408 0.0120
-3.000 -0.1930 0.00972 0.00313 0.0051 0.6261 0.0129
-2.500 -0.1327 0.00943 0.00275 0.0043 0.6012 0.0153
-2.250 -0.1025 0.00929 0.00259 0.0038 0.5895 0.0168
-2.000 -0.0722 0.00920 0.00245 0.0034 0.5770 0.0189
-1.750 -0.0418 0.00910 0.00232 0.0029 0.5639 0.0218
-1.500 -0.0113 0.00902 0.00221 0.0023 0.5500 0.0263
-1.250 0.0192 0.00895 0.00211 0.0018 0.5351 0.0326
-1.000 0.0497 0.00888 0.00203 0.0012 0.5206 0.0412
-0.750 0.0803 0.00882 0.00197 0.0006 0.5039 0.0557
-0.500 0.1110 0.00877 0.00192 -0.0001 0.4858 0.0744
-0.250 0.1416 0.00870 0.00188 -0.0007 0.4674 0.1037
0.000 0.1723 0.00862 0.00185 -0.0015 0.4432 0.1525
0.250 0.2028 0.00838 0.00183 -0.0025 0.4160 0.2635
0.500 0.2318 0.00745 0.00176 -0.0036 0.3906 0.5751
0.750 0.2593 0.00691 0.00186 -0.0038 0.3648 0.8008
1.000 0.2888 0.00705 0.00197 -0.0042 0.3380 0.8390
1.250 0.3185 0.00720 0.00206 -0.0046 0.3162 0.8597
1.500 0.3475 0.00733 0.00215 -0.0049 0.3000 0.8785
1.750 0.3763 0.00746 0.00224 -0.0050 0.2864 0.8950
2.000 0.4061 0.00761 0.00231 -0.0055 0.2734 0.8997
2.250 0.4362 0.00777 0.00239 -0.0061 0.2605 0.9035
2.500 0.4663 0.00793 0.00247 -0.0067 0.2487 0.9075
2.750 0.4960 0.00805 0.00255 -0.0072 0.2404 0.9113
3.000 0.5254 0.00821 0.00264 -0.0076 0.2318 0.9155
3.250 0.5549 0.00833 0.00273 -0.0081 0.2243 0.9199
3.500 0.5846 0.00851 0.00284 -0.0086 0.2160 0.9241
3.750 0.6136 0.00863 0.00294 -0.0090 0.2093 0.9283
4.000 0.6425 0.00879 0.00306 -0.0094 0.2027 0.9333
4.250 0.6715 0.00892 0.00318 -0.0097 0.1982 0.9386
4.500 0.7002 0.00907 0.00330 -0.0101 0.1930 0.9435
4.750 0.7286 0.00924 0.00343 -0.0104 0.1876 0.9491
5.000 0.7572 0.00937 0.00356 -0.0107 0.1839 0.9550
5.250 0.7857 0.00953 0.00370 -0.0110 0.1792 0.9612
5.500 0.8144 0.00972 0.00386 -0.0115 0.1738 0.9686
5.750 0.8445 0.00988 0.00401 -0.0122 0.1701 0.9753
6.000 0.8753 0.01005 0.00418 -0.0131 0.1666 0.9827
6.250 0.9073 0.01026 0.00436 -0.0143 0.1628 0.9896
6.500 0.9390 0.01049 0.00456 -0.0155 0.1587 1.0000
6.750 0.9678 0.01067 0.00476 -0.0161 0.1565 1.0000
7.000 0.9964 0.01087 0.00496 -0.0166 0.1539 1.0000
7.250 1.0248 0.01110 0.00518 -0.0171 0.1510 1.0000
7.500 1.0530 0.01135 0.00541 -0.0176 0.1480 1.0000
7.750 1.0809 0.01162 0.00567 -0.0181 0.1446 1.0000
8.000 1.1089 0.01184 0.00591 -0.0186 0.1417 1.0000
8.250 1.1363 0.01214 0.00617 -0.0190 0.1367 1.0000
8.500 1.1634 0.01245 0.00647 -0.0194 0.1327 1.0000
8.750 1.1907 0.01272 0.00675 -0.0198 0.1303 1.0000
9.000 1.2177 0.01299 0.00704 -0.0202 0.1275 1.0000
9.250 1.2441 0.01332 0.00736 -0.0206 0.1237 1.0000
9.500 1.2700 0.01369 0.00771 -0.0209 0.1201 1.0000
9.750 1.2961 0.01400 0.00805 -0.0212 0.1178 1.0000
10.000 1.3218 0.01434 0.00840 -0.0214 0.1146 1.0000
10.250 1.3464 0.01477 0.00882 -0.0216 0.1101 1.0000
10.500 1.3707 0.01521 0.00926 -0.0218 0.1055 1.0000
10.750 1.3943 0.01569 0.00974 -0.0220 0.1002 1.0000
11.000 1.4167 0.01629 0.01031 -0.0221 0.0941 1.0000
11.250 1.4362 0.01709 0.01106 -0.0221 0.0837 1.0000
11.500 1.4298 0.01961 0.01327 -0.0197 0.0410 1.0000
11.750 1.4322 0.02148 0.01508 -0.0181 0.0243 1.0000
12.000 1.4449 0.02259 0.01621 -0.0173 0.0209 1.0000
12.250 1.4590 0.02358 0.01725 -0.0167 0.0193 1.0000
12.500 1.4723 0.02467 0.01838 -0.0161 0.0181 1.0000
12.750 1.4843 0.02587 0.01963 -0.0155 0.0170 1.0000
13.000 1.4963 0.02709 0.02090 -0.0149 0.0163 1.0000
13.250 1.5085 0.02830 0.02217 -0.0144 0.0157 1.0000
13.500 1.5194 0.02964 0.02357 -0.0139 0.0151 1.0000
13.750 1.5288 0.03115 0.02514 -0.0135 0.0145 1.0000
14.000 1.5367 0.03280 0.02685 -0.0131 0.0140 1.0000
14.250 1.5433 0.03463 0.02874 -0.0127 0.0136 1.0000
14.500 1.5479 0.03670 0.03089 -0.0123 0.0131 1.0000
14.750 1.5542 0.03862 0.03289 -0.0122 0.0129 1.0000
15.000 1.5594 0.04072 0.03506 -0.0121 0.0126 1.0000
15.250 1.5631 0.04303 0.03746 -0.0121 0.0123 1.0000
15.500 1.5656 0.04556 0.04008 -0.0122 0.0120 1.0000
15.750 1.5666 0.04837 0.04297 -0.0126 0.0117 1.0000
16.000 1.5659 0.05147 0.04616 -0.0131 0.0114 1.0000
16.250 1.5630 0.05493 0.04970 -0.0137 0.0110 1.0000
16.500 1.5576 0.05880 0.05366 -0.0146 0.0107 1.0000
16.750 1.5485 0.06333 0.05830 -0.0159 0.0104 1.0000
17.000 1.5399 0.06786 0.06294 -0.0172 0.0102 1.0000
17.250 1.5301 0.07269 0.06789 -0.0187 0.0101 1.0000
17.500 1.5174 0.07807 0.07340 -0.0205 0.0100 1.0000
17.750 1.5008 0.08413 0.07959 -0.0226 0.0099 1.0000
18.000 1.4804 0.09095 0.08656 -0.0252 0.0099 1.0000
18.250 1.4559 0.09862 0.09437 -0.0281 0.0098 1.0000
18.500 1.4273 0.10705 0.10297 -0.0315 0.0099 1.0000
18.750 1.3968 0.11602 0.11209 -0.0352 0.0099 1.0000
19.000 1.3662 0.12516 0.12138 -0.0392 0.0100 1.0000
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