MRC-16 (mrc-16-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 50,000 Max Cl/Cd: 31.22 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-16-il-50000-n5.txt Download as CSV file: xf-mrc-16-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MRC-16
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4046 0.09507 0.08810 -0.0562 1.0000 0.0569
-9.750 -0.4128 0.09107 0.08418 -0.0568 1.0000 0.0566
-9.500 -0.4245 0.08700 0.08020 -0.0575 1.0000 0.0563
-9.250 -0.4418 0.08327 0.07657 -0.0576 1.0000 0.0559
-9.000 -0.4652 0.08041 0.07380 -0.0560 1.0000 0.0556
-8.750 -0.4919 0.07818 0.07165 -0.0528 1.0000 0.0552
-8.500 -0.5159 0.07553 0.06904 -0.0500 1.0000 0.0549
-8.250 -0.5378 0.07270 0.06620 -0.0472 1.0000 0.0546
-8.000 -0.5572 0.06971 0.06313 -0.0445 1.0000 0.0543
-7.750 -0.5731 0.06653 0.05983 -0.0419 1.0000 0.0541
-7.500 -0.5836 0.06304 0.05613 -0.0400 0.9994 0.0540
-7.250 -0.5723 0.05772 0.05030 -0.0425 0.9918 0.0541
-7.000 -0.5566 0.05303 0.04507 -0.0444 0.9846 0.0545
-6.750 -0.5393 0.04892 0.04029 -0.0455 0.9772 0.0560
-6.500 -0.5151 0.04566 0.03654 -0.0470 0.9711 0.0581
-6.250 -0.4912 0.04354 0.03423 -0.0478 0.9642 0.0604
-6.000 -0.4626 0.04101 0.03126 -0.0490 0.9583 0.0625
-5.750 -0.4351 0.03883 0.02858 -0.0497 0.9519 0.0657
-5.500 -0.4058 0.03691 0.02625 -0.0505 0.9455 0.0697
-5.250 -0.3703 0.03532 0.02452 -0.0524 0.9409 0.0741
-5.000 -0.3446 0.03408 0.02296 -0.0522 0.9330 0.0796
-4.750 -0.3104 0.03281 0.02163 -0.0537 0.9277 0.0865
-4.500 -0.2803 0.03182 0.02041 -0.0540 0.9210 0.0951
-4.250 -0.2497 0.03086 0.01945 -0.0548 0.9144 0.1062
-3.750 -0.1899 0.02910 0.01771 -0.0562 0.9008 0.1439
-3.500 -0.1553 0.02800 0.01684 -0.0580 0.8955 0.1897
-3.250 -0.1351 0.02692 0.01631 -0.0574 0.8869 0.2785
-3.000 -0.1108 0.02564 0.01608 -0.0569 0.8808 0.4766
-2.750 -0.0924 0.02520 0.01634 -0.0538 0.8730 0.6445
-2.500 -0.0625 0.02527 0.01664 -0.0520 0.8668 0.7755
-2.250 -0.0113 0.02562 0.01688 -0.0539 0.8636 0.8744
-2.000 0.0581 0.02606 0.01698 -0.0605 0.8597 0.9358
-1.750 0.1362 0.02615 0.01669 -0.0701 0.8560 0.9695
-1.500 0.2095 0.02593 0.01614 -0.0794 0.8518 0.9913
-1.250 0.2551 0.02570 0.01568 -0.0835 0.8455 1.0000
-1.000 0.2712 0.02570 0.01553 -0.0821 0.8345 1.0000
-0.750 0.2854 0.02579 0.01548 -0.0803 0.8234 1.0000
-0.500 0.3147 0.02562 0.01515 -0.0808 0.8164 1.0000
-0.250 0.3253 0.02583 0.01524 -0.0783 0.8044 1.0000
0.000 0.3418 0.02595 0.01525 -0.0766 0.7942 1.0000
0.250 0.3681 0.02590 0.01506 -0.0764 0.7866 1.0000
0.500 0.3805 0.02616 0.01523 -0.0740 0.7752 1.0000
0.750 0.4072 0.02613 0.01509 -0.0738 0.7679 1.0000
1.000 0.4233 0.02635 0.01523 -0.0719 0.7573 1.0000
1.250 0.4400 0.02660 0.01540 -0.0701 0.7472 1.0000
1.500 0.4684 0.02655 0.01526 -0.0700 0.7400 1.0000
1.750 0.4818 0.02692 0.01557 -0.0677 0.7288 1.0000
2.000 0.5130 0.02680 0.01538 -0.0680 0.7224 1.0000
2.250 0.5272 0.02720 0.01574 -0.0658 0.7111 1.0000
2.500 0.5461 0.02749 0.01599 -0.0644 0.7012 1.0000
2.750 0.5751 0.02744 0.01590 -0.0642 0.6937 1.0000
3.000 0.5904 0.02789 0.01633 -0.0623 0.6825 1.0000
3.250 0.6240 0.02769 0.01611 -0.0628 0.6762 1.0000
3.500 0.6384 0.02820 0.01663 -0.0607 0.6645 1.0000
3.750 0.6580 0.02854 0.01697 -0.0594 0.6543 1.0000
4.000 0.6890 0.02843 0.01687 -0.0595 0.6468 1.0000
4.250 0.7045 0.02895 0.01742 -0.0576 0.6351 1.0000
4.500 0.7289 0.02913 0.01761 -0.0569 0.6259 1.0000
4.750 0.7552 0.02921 0.01774 -0.0564 0.6166 1.0000
5.000 0.7721 0.02972 0.01829 -0.0547 0.6052 1.0000
5.250 0.7991 0.02978 0.01838 -0.0543 0.5960 1.0000
5.500 0.8229 0.02997 0.01863 -0.0535 0.5857 1.0000
5.750 0.8398 0.03050 0.01924 -0.0518 0.5740 1.0000
6.000 0.8642 0.03068 0.01948 -0.0511 0.5638 1.0000
6.250 0.8917 0.03071 0.01956 -0.0506 0.5539 1.0000
6.500 0.9072 0.03131 0.02027 -0.0489 0.5415 1.0000
6.750 0.9267 0.03174 0.02078 -0.0476 0.5300 1.0000
7.000 0.9540 0.03177 0.02087 -0.0471 0.5196 1.0000
7.250 0.9753 0.03209 0.02130 -0.0459 0.5078 1.0000
7.500 0.9901 0.03273 0.02204 -0.0441 0.4951 1.0000
7.750 1.0075 0.03325 0.02266 -0.0426 0.4828 1.0000
8.000 1.0282 0.03360 0.02309 -0.0414 0.4707 1.0000
8.250 1.0523 0.03377 0.02335 -0.0405 0.4587 1.0000
8.500 1.0697 0.03426 0.02394 -0.0389 0.4457 1.0000
8.750 1.0808 0.03502 0.02481 -0.0367 0.4323 1.0000
9.000 1.0923 0.03576 0.02566 -0.0345 0.4192 1.0000
9.250 1.1051 0.03646 0.02647 -0.0325 0.4059 1.0000
9.500 1.1185 0.03715 0.02725 -0.0306 0.3926 1.0000
9.750 1.1316 0.03785 0.02803 -0.0288 0.3791 1.0000
10.000 1.1443 0.03858 0.02884 -0.0269 0.3655 1.0000
10.250 1.1556 0.03939 0.02972 -0.0250 0.3517 1.0000
10.500 1.1660 0.04028 0.03069 -0.0231 0.3378 1.0000
10.750 1.1697 0.04165 0.03216 -0.0209 0.3239 1.0000
11.000 1.1731 0.04310 0.03372 -0.0188 0.3100 1.0000
11.250 1.1759 0.04466 0.03537 -0.0169 0.2961 1.0000
11.500 1.1782 0.04634 0.03713 -0.0151 0.2824 1.0000
11.750 1.1796 0.04814 0.03902 -0.0134 0.2687 1.0000
12.000 1.1804 0.05007 0.04105 -0.0119 0.2552 1.0000
12.250 1.1802 0.05216 0.04319 -0.0105 0.2418 1.0000
12.500 1.1796 0.05437 0.04546 -0.0093 0.2287 1.0000
12.750 1.1781 0.05672 0.04784 -0.0082 0.2158 1.0000
13.000 1.1766 0.05915 0.05029 -0.0073 0.2033 1.0000
13.250 1.1721 0.06205 0.05326 -0.0066 0.1911 1.0000
13.500 1.1653 0.06542 0.05674 -0.0063 0.1796 1.0000
13.750 1.1593 0.06879 0.06019 -0.0061 0.1684 1.0000
14.000 1.1545 0.07208 0.06351 -0.0060 0.1579 1.0000
14.250 1.1511 0.07515 0.06655 -0.0059 0.1477 1.0000
14.500 1.1421 0.07943 0.07100 -0.0064 0.1382 1.0000
14.750 1.1355 0.08340 0.07504 -0.0069 0.1295 1.0000
15.000 1.1331 0.08659 0.07814 -0.0072 0.1211 1.0000
15.250 1.1223 0.09167 0.08345 -0.0084 0.1137 1.0000
15.500 1.1191 0.09526 0.08701 -0.0091 0.1067 1.0000
15.750 1.1091 0.10041 0.09234 -0.0106 0.1005 1.0000
16.000 1.1076 0.10385 0.09574 -0.0113 0.0945 1.0000
16.250 1.0944 0.10998 0.10212 -0.0136 0.0900 1.0000
16.500 1.0983 0.11239 0.10441 -0.0140 0.0842 1.0000
16.750 1.0818 0.11958 0.11187 -0.0171 0.0811 1.0000
17.000 1.0633 0.12747 0.11999 -0.0208 0.0785 1.0000
17.250 1.0541 0.13339 0.12601 -0.0236 0.0752 1.0000
17.500 1.0565 0.13655 0.12914 -0.0248 0.0714 1.0000
17.750 1.0213 0.14981 0.14262 -0.0322 0.0709 1.0000
18.000 0.9727 0.16897 0.16177 -0.0431 0.0702 1.0000
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Polar data table (+)
Polar graphs
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