MRC-20 (mrc-20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 100,000 Max Cl/Cd: 50.31 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-20-il-100000-n5.txt Download as CSV file: xf-mrc-20-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3848 0.09716 0.09240 -0.0572 0.9874 0.0559
-9.000 -0.3848 0.09128 0.08653 -0.0633 0.9836 0.0567
-8.750 -0.3946 0.08549 0.08071 -0.0689 0.9772 0.0570
-8.500 -0.4076 0.08080 0.07595 -0.0726 0.9707 0.0572
-8.000 -0.4419 0.06849 0.06298 -0.0740 0.9521 0.0364
-7.750 -0.4330 0.06480 0.05915 -0.0749 0.9477 0.0358
-7.500 -0.4315 0.06172 0.05590 -0.0735 0.9406 0.0353
-7.000 -0.4155 0.05319 0.04650 -0.0719 0.9299 0.0308
-6.750 -0.4094 0.05087 0.04403 -0.0696 0.9222 0.0304
-6.500 -0.3906 0.04786 0.04075 -0.0696 0.9182 0.0298
-6.250 -0.3748 0.04515 0.03772 -0.0686 0.9132 0.0292
-6.000 -0.3619 0.04275 0.03501 -0.0666 0.9065 0.0288
-5.750 -0.3375 0.04004 0.03190 -0.0665 0.9029 0.0283
-5.500 -0.3084 0.03749 0.02892 -0.0671 0.9005 0.0281
-5.250 -0.2979 0.03594 0.02711 -0.0639 0.8919 0.0281
-5.000 -0.2689 0.03400 0.02484 -0.0642 0.8884 0.0283
-4.750 -0.2359 0.03231 0.02286 -0.0652 0.8861 0.0293
-4.500 -0.2194 0.03124 0.02153 -0.0629 0.8784 0.0305
-4.250 -0.1897 0.02990 0.02000 -0.0632 0.8744 0.0318
-4.000 -0.1557 0.02860 0.01865 -0.0644 0.8718 0.0327
-3.750 -0.1331 0.02769 0.01769 -0.0634 0.8658 0.0335
-3.500 -0.1080 0.02677 0.01671 -0.0628 0.8603 0.0347
-3.250 -0.0762 0.02578 0.01565 -0.0635 0.8571 0.0365
-3.000 -0.0530 0.02506 0.01499 -0.0628 0.8517 0.0392
-2.750 -0.0325 0.02451 0.01441 -0.0615 0.8447 0.0424
-2.500 -0.0023 0.02368 0.01350 -0.0619 0.8413 0.0457
-2.250 0.0169 0.02326 0.01301 -0.0604 0.8338 0.0505
-2.000 0.0437 0.02267 0.01236 -0.0603 0.8284 0.0600
-1.500 0.0826 0.01971 0.01138 -0.0581 0.8170 0.5514
-1.250 0.1059 0.01930 0.01135 -0.0562 0.8121 0.6687
-1.000 0.1324 0.01902 0.01132 -0.0544 0.8091 0.7507
-0.750 0.1465 0.01913 0.01148 -0.0511 0.7993 0.7852
-0.500 0.1807 0.01887 0.01112 -0.0520 0.7953 0.7985
-0.250 0.2083 0.01875 0.01092 -0.0517 0.7887 0.8116
0.000 0.2362 0.01863 0.01074 -0.0516 0.7817 0.8258
0.250 0.2742 0.01833 0.01035 -0.0532 0.7781 0.8405
0.500 0.2959 0.01838 0.01038 -0.0519 0.7684 0.8579
0.750 0.3341 0.01815 0.01008 -0.0536 0.7636 0.8742
1.000 0.3651 0.01813 0.01003 -0.0542 0.7555 0.8920
1.250 0.4039 0.01799 0.00984 -0.0562 0.7489 0.9086
1.500 0.4444 0.01788 0.00968 -0.0586 0.7421 0.9246
1.750 0.4837 0.01784 0.00960 -0.0610 0.7337 0.9404
2.000 0.5285 0.01774 0.00944 -0.0645 0.7261 0.9531
2.250 0.5715 0.01768 0.00934 -0.0677 0.7169 0.9657
2.500 0.6145 0.01765 0.00928 -0.0710 0.7071 0.9775
2.750 0.6624 0.01749 0.00906 -0.0752 0.6983 0.9861
3.000 0.7041 0.01754 0.00910 -0.0785 0.6861 0.9970
3.250 0.7301 0.01752 0.00904 -0.0784 0.6747 1.0000
3.500 0.7539 0.01746 0.00891 -0.0778 0.6640 1.0000
3.750 0.7711 0.01753 0.00893 -0.0759 0.6517 1.0000
4.000 0.7880 0.01764 0.00899 -0.0739 0.6393 1.0000
4.250 0.8085 0.01772 0.00903 -0.0726 0.6272 1.0000
4.500 0.8314 0.01781 0.00907 -0.0718 0.6152 1.0000
4.750 0.8509 0.01795 0.00918 -0.0703 0.6024 1.0000
5.000 0.8686 0.01815 0.00935 -0.0685 0.5892 1.0000
5.250 0.8880 0.01835 0.00954 -0.0670 0.5762 1.0000
5.500 0.9084 0.01855 0.00971 -0.0657 0.5633 1.0000
5.750 0.9294 0.01877 0.00988 -0.0645 0.5503 1.0000
6.000 0.9489 0.01902 0.01011 -0.0631 0.5369 1.0000
6.250 0.9662 0.01931 0.01042 -0.0614 0.5232 1.0000
6.500 0.9841 0.01961 0.01072 -0.0597 0.5096 1.0000
6.750 1.0019 0.01993 0.01103 -0.0580 0.4961 1.0000
7.000 1.0193 0.02026 0.01136 -0.0563 0.4827 1.0000
7.250 1.0365 0.02062 0.01170 -0.0546 0.4694 1.0000
7.500 1.0529 0.02100 0.01207 -0.0528 0.4559 1.0000
7.750 1.0677 0.02143 0.01252 -0.0507 0.4421 1.0000
8.000 1.0828 0.02188 0.01301 -0.0488 0.4284 1.0000
8.250 1.0976 0.02237 0.01351 -0.0468 0.4147 1.0000
8.500 1.1121 0.02288 0.01404 -0.0449 0.4010 1.0000
8.750 1.1260 0.02343 0.01461 -0.0429 0.3872 1.0000
9.000 1.1393 0.02403 0.01521 -0.0409 0.3734 1.0000
9.250 1.1518 0.02466 0.01585 -0.0388 0.3595 1.0000
9.500 1.1632 0.02536 0.01659 -0.0367 0.3451 1.0000
9.750 1.1739 0.02610 0.01739 -0.0345 0.3307 1.0000
10.000 1.1840 0.02691 0.01823 -0.0323 0.3162 1.0000
10.250 1.1932 0.02778 0.01914 -0.0302 0.3015 1.0000
10.500 1.2015 0.02873 0.02011 -0.0280 0.2867 1.0000
10.750 1.2090 0.02977 0.02119 -0.0258 0.2718 1.0000
11.000 1.2155 0.03090 0.02234 -0.0236 0.2567 1.0000
11.250 1.2211 0.03214 0.02360 -0.0215 0.2418 1.0000
11.500 1.2259 0.03349 0.02497 -0.0195 0.2269 1.0000
11.750 1.2297 0.03496 0.02647 -0.0175 0.2122 1.0000
12.000 1.2328 0.03656 0.02810 -0.0156 0.1978 1.0000
12.250 1.2350 0.03829 0.02985 -0.0138 0.1839 1.0000
12.500 1.2363 0.04017 0.03176 -0.0121 0.1706 1.0000
12.750 1.2369 0.04220 0.03381 -0.0105 0.1580 1.0000
13.000 1.2363 0.04441 0.03605 -0.0091 0.1461 1.0000
13.250 1.2344 0.04685 0.03849 -0.0078 0.1352 1.0000
13.500 1.2336 0.04932 0.04104 -0.0068 0.1244 1.0000
13.750 1.2319 0.05196 0.04374 -0.0059 0.1147 1.0000
14.000 1.2286 0.05486 0.04669 -0.0052 0.1063 1.0000
14.250 1.2242 0.05799 0.04986 -0.0047 0.0986 1.0000
14.500 1.2212 0.06110 0.05306 -0.0043 0.0914 1.0000
14.750 1.2146 0.06469 0.05667 -0.0041 0.0860 1.0000
15.000 1.2118 0.06796 0.06007 -0.0041 0.0800 1.0000
15.250 1.2047 0.07183 0.06398 -0.0043 0.0756 1.0000
15.500 1.2011 0.07537 0.06765 -0.0046 0.0710 1.0000
15.750 1.1953 0.07925 0.07162 -0.0050 0.0672 1.0000
16.000 1.1888 0.08327 0.07567 -0.0056 0.0642 1.0000
16.250 1.1857 0.08694 0.07950 -0.0062 0.0606 1.0000
16.500 1.1805 0.09097 0.08361 -0.0071 0.0579 1.0000
16.750 1.1750 0.09498 0.08763 -0.0080 0.0556 1.0000
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Polar data table (+)
Polar graphs
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