MRC-20 (mrc-20-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 50,000 Max Cl/Cd: 29.35 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-20-il-50000-n5.txt Download as CSV file: xf-mrc-20-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MRC-20
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3754 0.12975 0.12279 -0.0412 1.0000 0.1256
-10.500 -0.3825 0.12724 0.12036 -0.0409 1.0000 0.1295
-10.250 -0.4291 0.12613 0.11947 -0.0437 1.0000 0.1341
-10.000 -0.4113 0.12173 0.11508 -0.0411 1.0000 0.1362
-9.750 -0.4044 0.11879 0.11217 -0.0391 1.0000 0.1389
-9.500 -0.4074 0.11613 0.10957 -0.0378 1.0000 0.1418
-9.250 -0.4178 0.11347 0.10700 -0.0371 1.0000 0.1453
-8.750 -0.3825 0.09908 0.09320 -0.0385 1.0000 0.0696
-8.500 -0.4006 0.09412 0.08828 -0.0395 1.0000 0.0661
-8.250 -0.4334 0.08699 0.08108 -0.0439 0.9973 0.0605
-8.000 -0.4405 0.08216 0.07621 -0.0456 0.9930 0.0588
-7.750 -0.4582 0.07766 0.07164 -0.0461 0.9872 0.0575
-7.500 -0.5711 0.08279 0.07625 -0.0368 0.9981 0.0593
-7.250 -0.5651 0.07801 0.07126 -0.0388 0.9924 0.0564
-7.000 -0.5617 0.07267 0.06533 -0.0406 0.9851 0.0514
-6.750 -0.5490 0.06899 0.06149 -0.0413 0.9794 0.0503
-6.500 -0.5339 0.06527 0.05749 -0.0424 0.9741 0.0492
-6.250 -0.5206 0.06189 0.05378 -0.0425 0.9679 0.0483
-6.000 -0.5021 0.05869 0.05020 -0.0431 0.9623 0.0482
-5.750 -0.4838 0.05589 0.04701 -0.0431 0.9566 0.0485
-5.500 -0.4634 0.05327 0.04398 -0.0432 0.9506 0.0490
-5.250 -0.4362 0.05070 0.04096 -0.0442 0.9463 0.0493
-5.000 -0.4167 0.04852 0.03841 -0.0433 0.9396 0.0492
-4.750 -0.3890 0.04633 0.03582 -0.0438 0.9345 0.0489
-4.500 -0.3564 0.04432 0.03339 -0.0448 0.9305 0.0490
-4.250 -0.3336 0.04273 0.03150 -0.0440 0.9238 0.0493
-4.000 -0.3011 0.04120 0.02965 -0.0448 0.9190 0.0503
-3.750 -0.2664 0.03994 0.02805 -0.0458 0.9148 0.0525
-3.500 -0.2425 0.03883 0.02699 -0.0453 0.9080 0.0550
-3.250 -0.2084 0.03783 0.02592 -0.0461 0.9033 0.0574
-3.000 -0.1775 0.03701 0.02495 -0.0462 0.8982 0.0597
-2.750 -0.1536 0.03630 0.02415 -0.0455 0.8911 0.0634
-2.500 -0.1215 0.03552 0.02330 -0.0465 0.8863 0.0696
-2.250 -0.1019 0.03495 0.02258 -0.0453 0.8779 0.0745
-2.000 -0.0710 0.03418 0.02170 -0.0464 0.8722 0.0856
-1.750 -0.0487 0.03354 0.02099 -0.0459 0.8644 0.1008
-1.250 -0.0150 0.03034 0.02064 -0.0409 0.8525 0.7098
-1.000 -0.0056 0.03058 0.02121 -0.0345 0.8441 0.8142
-0.500 0.0717 0.03153 0.02188 -0.0355 0.8316 0.9236
-0.250 0.1216 0.03159 0.02167 -0.0402 0.8262 0.9369
0.000 0.1630 0.03176 0.02164 -0.0438 0.8179 0.9528
0.250 0.2137 0.03181 0.02148 -0.0489 0.8117 0.9672
0.500 0.2622 0.03189 0.02138 -0.0539 0.8046 0.9826
0.750 0.3116 0.03192 0.02128 -0.0591 0.7969 0.9983
1.250 0.3441 0.03153 0.02062 -0.0564 0.7787 1.0000
1.500 0.3506 0.03164 0.02061 -0.0533 0.7666 1.0000
1.750 0.3853 0.03133 0.02017 -0.0546 0.7614 1.0000
2.000 0.3941 0.03161 0.02036 -0.0519 0.7488 1.0000
2.250 0.4119 0.03180 0.02045 -0.0505 0.7386 1.0000
2.500 0.4430 0.03162 0.02019 -0.0510 0.7317 1.0000
2.750 0.4587 0.03195 0.02045 -0.0494 0.7203 1.0000
3.000 0.4945 0.03160 0.02004 -0.0504 0.7148 1.0000
3.250 0.5091 0.03202 0.02042 -0.0486 0.7027 1.0000
3.500 0.5482 0.03154 0.01991 -0.0501 0.6978 1.0000
3.750 0.5618 0.03204 0.02039 -0.0481 0.6852 1.0000
4.000 0.5828 0.03228 0.02062 -0.0472 0.6747 1.0000
4.250 0.6166 0.03198 0.02031 -0.0478 0.6676 1.0000
4.500 0.6337 0.03240 0.02076 -0.0463 0.6557 1.0000
4.750 0.6737 0.03182 0.02019 -0.0477 0.6500 1.0000
5.250 0.7104 0.03261 0.02104 -0.0450 0.6264 1.0000
5.500 0.7464 0.03219 0.02066 -0.0458 0.6186 1.0000
5.750 0.7625 0.03271 0.02121 -0.0442 0.6060 1.0000
6.000 0.7885 0.03277 0.02132 -0.0438 0.5957 1.0000
6.250 0.8214 0.03251 0.02113 -0.0441 0.5863 1.0000
6.500 0.8375 0.03305 0.02173 -0.0426 0.5735 1.0000
6.750 0.8609 0.03326 0.02200 -0.0418 0.5621 1.0000
7.000 0.8989 0.03278 0.02159 -0.0428 0.5527 1.0000
7.250 0.9124 0.03345 0.02234 -0.0408 0.5392 1.0000
7.500 0.9298 0.03396 0.02293 -0.0394 0.5264 1.0000
7.750 0.9530 0.03420 0.02325 -0.0386 0.5143 1.0000
8.000 0.9843 0.03404 0.02315 -0.0387 0.5028 1.0000
8.250 1.0009 0.03459 0.02379 -0.0372 0.4894 1.0000
8.500 1.0146 0.03530 0.02459 -0.0354 0.4758 1.0000
8.750 1.0307 0.03590 0.02530 -0.0339 0.4625 1.0000
9.000 1.0491 0.03639 0.02587 -0.0326 0.4493 1.0000
9.250 1.0691 0.03678 0.02633 -0.0314 0.4359 1.0000
9.500 1.0898 0.03713 0.02675 -0.0304 0.4225 1.0000
9.750 1.1016 0.03795 0.02766 -0.0284 0.4084 1.0000
10.000 1.1101 0.03897 0.02879 -0.0263 0.3943 1.0000
10.500 1.1286 0.04098 0.03100 -0.0223 0.3662 1.0000
10.750 1.1377 0.04201 0.03212 -0.0203 0.3521 1.0000
11.000 1.1460 0.04310 0.03329 -0.0184 0.3380 1.0000
11.250 1.1534 0.04426 0.03452 -0.0165 0.3239 1.0000
11.500 1.1595 0.04552 0.03585 -0.0146 0.3097 1.0000
11.750 1.1647 0.04688 0.03726 -0.0127 0.2956 1.0000
12.000 1.1669 0.04850 0.03896 -0.0108 0.2816 1.0000
12.250 1.1656 0.05052 0.04109 -0.0089 0.2678 1.0000
12.500 1.1641 0.05265 0.04330 -0.0073 0.2541 1.0000
12.750 1.1624 0.05488 0.04563 -0.0058 0.2407 1.0000
13.000 1.1604 0.05723 0.04805 -0.0045 0.2276 1.0000
13.250 1.1583 0.05967 0.05055 -0.0033 0.2149 1.0000
13.500 1.1561 0.06220 0.05310 -0.0023 0.2025 1.0000
13.750 1.1543 0.06474 0.05564 -0.0015 0.1906 1.0000
14.000 1.1484 0.06799 0.05901 -0.0010 0.1791 1.0000
14.250 1.1425 0.07142 0.06254 -0.0007 0.1683 1.0000
14.500 1.1381 0.07470 0.06585 -0.0005 0.1582 1.0000
14.750 1.1364 0.07758 0.06869 -0.0003 0.1486 1.0000
15.000 1.1279 0.08179 0.07310 -0.0007 0.1396 1.0000
15.250 1.1233 0.08542 0.07677 -0.0010 0.1316 1.0000
15.500 1.1203 0.08883 0.08020 -0.0013 0.1238 1.0000
15.750 1.1120 0.09338 0.08491 -0.0022 0.1171 1.0000
16.000 1.1120 0.09638 0.08789 -0.0025 0.1105 1.0000
16.250 1.1015 0.10159 0.09331 -0.0040 0.1052 1.0000
16.500 1.0976 0.10556 0.09735 -0.0050 0.0998 1.0000
16.750 1.0935 0.10970 0.10156 -0.0062 0.0953 1.0000
17.000 1.0777 0.11639 0.10851 -0.0089 0.0919 1.0000
17.250 1.0761 0.12015 0.11232 -0.0102 0.0877 1.0000
17.500 1.0698 0.12508 0.11734 -0.0121 0.0844 1.0000
17.750 1.0375 0.13621 0.12874 -0.0180 0.0831 1.0000
18.000 0.9830 0.15435 0.14702 -0.0281 0.0823 1.0000
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Polar data table (+)
Polar graphs
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