ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: ONERA OA213 AIRFOIL (oa213-il) Reynolds number: 50,000 Max Cl/Cd: 29.79 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa213-il-50000-n5.txt Download as CSV file: xf-oa213-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3656 0.10170 0.09599 -0.0204 1.0000 0.1187
-8.500 -0.3636 0.09775 0.09209 -0.0237 1.0000 0.1180
-8.250 -0.3955 0.08637 0.08056 -0.0376 1.0000 0.0571
-8.000 -0.3965 0.08393 0.07817 -0.0361 1.0000 0.0560
-7.750 -0.3992 0.08074 0.07499 -0.0367 0.9952 0.0548
-7.500 -0.3909 0.07573 0.06987 -0.0413 0.9857 0.0529
-7.250 -0.3841 0.07029 0.06423 -0.0458 0.9764 0.0508
-7.000 -0.3810 0.06401 0.05742 -0.0498 0.9664 0.0478
-6.750 -0.3667 0.06020 0.05339 -0.0514 0.9586 0.0475
-6.500 -0.3517 0.05628 0.04909 -0.0529 0.9512 0.0477
-6.250 -0.3395 0.05296 0.04539 -0.0530 0.9423 0.0483
-6.000 -0.3210 0.05072 0.04308 -0.0533 0.9349 0.0498
-5.750 -0.3024 0.04807 0.04011 -0.0534 0.9274 0.0507
-5.500 -0.2860 0.04547 0.03713 -0.0527 0.9190 0.0510
-5.250 -0.2637 0.04287 0.03409 -0.0525 0.9124 0.0514
-5.000 -0.2453 0.04075 0.03159 -0.0514 0.9038 0.0520
-4.750 -0.2208 0.03881 0.02921 -0.0510 0.8973 0.0542
-4.500 -0.1987 0.03711 0.02698 -0.0499 0.8889 0.0569
-4.250 -0.1721 0.03547 0.02512 -0.0496 0.8826 0.0593
-4.000 -0.1484 0.03420 0.02369 -0.0489 0.8744 0.0618
-3.750 -0.1190 0.03306 0.02225 -0.0486 0.8684 0.0671
-3.500 -0.0946 0.03200 0.02110 -0.0479 0.8599 0.0718
-3.250 -0.0640 0.03112 0.02007 -0.0476 0.8539 0.0793
-3.000 -0.0386 0.03034 0.01927 -0.0471 0.8454 0.0876
-2.750 -0.0104 0.02960 0.01844 -0.0466 0.8389 0.1005
-2.500 0.0120 0.02900 0.01784 -0.0457 0.8299 0.1175
-2.250 0.0353 0.02825 0.01719 -0.0446 0.8230 0.1472
-2.000 0.0525 0.02728 0.01670 -0.0433 0.8135 0.2166
-1.750 0.2117 0.02526 0.01670 -0.0598 0.8163 1.0000
-1.500 0.2310 0.02529 0.01648 -0.0583 0.8067 1.0000
-1.250 0.2497 0.02538 0.01636 -0.0571 0.7948 1.0000
-1.000 0.2683 0.02538 0.01617 -0.0554 0.7837 1.0000
-0.750 0.2870 0.02526 0.01584 -0.0532 0.7733 1.0000
-0.500 0.3052 0.02526 0.01568 -0.0516 0.7599 1.0000
-0.250 0.3236 0.02522 0.01549 -0.0498 0.7470 1.0000
0.000 0.3422 0.02512 0.01524 -0.0479 0.7349 1.0000
0.250 0.3613 0.02485 0.01482 -0.0455 0.7247 1.0000
0.500 0.3801 0.02483 0.01468 -0.0438 0.7110 1.0000
1.000 0.4181 0.02466 0.01430 -0.0402 0.6845 1.0000
1.250 0.4377 0.02449 0.01403 -0.0382 0.6717 1.0000
1.500 0.4578 0.02423 0.01365 -0.0361 0.6595 1.0000
1.750 0.4779 0.02407 0.01339 -0.0342 0.6457 1.0000
2.000 0.4980 0.02396 0.01319 -0.0324 0.6304 1.0000
2.250 0.5183 0.02384 0.01299 -0.0307 0.6147 1.0000
2.500 0.5390 0.02371 0.01277 -0.0289 0.5983 1.0000
2.750 0.5601 0.02359 0.01253 -0.0272 0.5812 1.0000
3.000 0.5807 0.02364 0.01251 -0.0257 0.5609 1.0000
3.250 0.6019 0.02366 0.01243 -0.0242 0.5405 1.0000
3.500 0.6237 0.02366 0.01229 -0.0227 0.5200 1.0000
3.750 0.6453 0.02379 0.01227 -0.0214 0.4977 1.0000
4.000 0.6667 0.02401 0.01235 -0.0202 0.4747 1.0000
4.250 0.6886 0.02424 0.01241 -0.0190 0.4537 1.0000
4.500 0.7097 0.02467 0.01270 -0.0180 0.4313 1.0000
4.750 0.7309 0.02512 0.01299 -0.0171 0.4113 1.0000
5.000 0.7522 0.02564 0.01334 -0.0162 0.3935 1.0000
5.250 0.7735 0.02622 0.01380 -0.0154 0.3772 1.0000
5.500 0.7948 0.02685 0.01431 -0.0147 0.3622 1.0000
5.750 0.8162 0.02752 0.01489 -0.0141 0.3486 1.0000
6.000 0.8380 0.02821 0.01550 -0.0135 0.3368 1.0000
6.250 0.8604 0.02888 0.01605 -0.0129 0.3264 1.0000
6.500 0.8819 0.02968 0.01689 -0.0124 0.3155 1.0000
6.750 0.9044 0.03044 0.01761 -0.0120 0.3065 1.0000
7.000 0.9270 0.03123 0.01842 -0.0115 0.2981 1.0000
7.250 0.9493 0.03208 0.01929 -0.0112 0.2903 1.0000
7.500 0.9713 0.03294 0.02018 -0.0108 0.2827 1.0000
7.750 0.9939 0.03382 0.02106 -0.0104 0.2762 1.0000
8.000 1.0145 0.03485 0.02225 -0.0101 0.2695 1.0000
8.250 1.0386 0.03570 0.02306 -0.0098 0.2644 1.0000
8.500 1.0581 0.03692 0.02445 -0.0094 0.2589 1.0000
8.750 1.0774 0.03811 0.02580 -0.0090 0.2535 1.0000
9.000 1.1006 0.03904 0.02673 -0.0088 0.2490 1.0000
9.250 1.1177 0.04045 0.02833 -0.0083 0.2444 1.0000
9.500 1.1324 0.04203 0.03015 -0.0078 0.2399 1.0000
9.750 1.1507 0.04342 0.03168 -0.0074 0.2363 1.0000
10.000 1.1730 0.04460 0.03292 -0.0072 0.2334 1.0000
10.250 1.1864 0.04641 0.03493 -0.0067 0.2303 1.0000
10.500 1.1879 0.04892 0.03780 -0.0057 0.2270 1.0000
10.750 1.1911 0.05129 0.04040 -0.0049 0.2238 1.0000
11.000 1.1982 0.05331 0.04259 -0.0042 0.2209 1.0000
11.250 1.2136 0.05485 0.04423 -0.0037 0.2184 1.0000
11.500 1.2239 0.05685 0.04634 -0.0031 0.2163 1.0000
11.750 1.1774 0.06300 0.05285 -0.0019 0.2143 1.0000
12.000 0.9468 0.09838 0.08849 -0.0166 0.2068 1.0000
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Polar data table (+)
Polar graphs
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