MRC-20 (mrc-20-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 200,000 Max Cl/Cd: 73.06 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-20-il-200000.txt Download as CSV file: xf-mrc-20-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4346 0.08987 0.08659 -0.0585 0.9889 0.0431
-8.750 -0.4538 0.08431 0.08091 -0.0650 0.9828 0.0433
-8.500 -0.4773 0.08025 0.07655 -0.0679 0.9735 0.0437
-8.250 -0.4942 0.07737 0.07330 -0.0673 0.9633 0.0439
-8.000 -0.4723 0.07088 0.06700 -0.0698 0.9619 0.0447
-7.750 -0.4599 0.06759 0.06373 -0.0703 0.9575 0.0454
-7.500 -0.4520 0.06468 0.06075 -0.0702 0.9511 0.0464
-7.250 -0.4348 0.06128 0.05719 -0.0721 0.9474 0.0482
-7.000 -0.4413 0.06149 0.05661 -0.0679 0.9360 0.0521
-6.750 -0.3763 0.04170 0.03745 -0.0722 0.9201 0.0545
-6.500 -0.3957 0.05168 0.04688 -0.0724 0.9316 0.0549
-6.250 -0.3916 0.04989 0.04500 -0.0694 0.9224 0.0567
-6.000 -0.3705 0.04784 0.04230 -0.0691 0.9180 0.0631
-5.750 -0.3406 0.04423 0.03878 -0.0716 0.9164 0.0655
-5.500 -0.3341 0.04279 0.03724 -0.0684 0.9069 0.0683
-5.250 -0.3081 0.04052 0.03457 -0.0689 0.9034 0.0764
-4.750 -0.2671 0.03683 0.03066 -0.0680 0.8923 0.0919
-4.500 -0.2387 0.03502 0.02864 -0.0688 0.8889 0.1060
-4.250 -0.2056 0.03297 0.02646 -0.0706 0.8869 0.1224
-4.000 -0.1645 0.03092 0.02360 -0.0685 0.8827 0.0724
-3.750 -0.1313 0.02662 0.01872 -0.0664 0.8780 0.0418
-3.500 -0.0953 0.02499 0.01696 -0.0675 0.8750 0.0407
-3.250 -0.0562 0.02371 0.01558 -0.0693 0.8731 0.0414
-3.000 -0.0151 0.02285 0.01458 -0.0715 0.8715 0.0438
-2.750 -0.0011 0.02196 0.01375 -0.0688 0.8628 0.0448
-2.500 0.0322 0.02089 0.01275 -0.0698 0.8595 0.0472
-2.250 0.0696 0.01996 0.01180 -0.0715 0.8574 0.0513
-2.000 0.1076 0.01894 0.01078 -0.0735 0.8559 0.0610
-1.750 0.1211 0.01854 0.01036 -0.0707 0.8461 0.0731
-1.500 0.1358 0.01573 0.00967 -0.0686 0.8428 0.6294
-1.250 0.1684 0.01525 0.00938 -0.0684 0.8408 0.7027
-1.000 0.1857 0.01523 0.00946 -0.0658 0.8320 0.7394
-0.750 0.2145 0.01494 0.00926 -0.0649 0.8282 0.7819
-0.500 0.2495 0.01455 0.00888 -0.0653 0.8257 0.8068
-0.250 0.2730 0.01442 0.00873 -0.0644 0.8177 0.8207
0.000 0.3060 0.01408 0.00836 -0.0650 0.8129 0.8339
0.250 0.3443 0.01366 0.00791 -0.0666 0.8098 0.8472
0.500 0.3670 0.01359 0.00785 -0.0653 0.8009 0.8634
0.750 0.4023 0.01329 0.00753 -0.0664 0.7958 0.8791
1.000 0.4352 0.01312 0.00733 -0.0670 0.7894 0.8953
1.250 0.4678 0.01301 0.00720 -0.0677 0.7813 0.9115
1.500 0.5082 0.01285 0.00698 -0.0699 0.7749 0.9258
1.750 0.5440 0.01283 0.00693 -0.0714 0.7654 0.9406
2.000 0.5903 0.01279 0.00684 -0.0751 0.7567 0.9492
2.250 0.6349 0.01272 0.00671 -0.0786 0.7474 0.9588
2.500 0.6800 0.01274 0.00670 -0.0823 0.7361 0.9671
2.750 0.7272 0.01271 0.00661 -0.0865 0.7252 0.9742
3.000 0.7738 0.01267 0.00649 -0.0906 0.7138 0.9817
3.250 0.8191 0.01268 0.00648 -0.0946 0.6999 0.9890
3.500 0.8643 0.01271 0.00647 -0.0986 0.6857 0.9964
3.750 0.8956 0.01274 0.00646 -0.0999 0.6715 1.0000
4.000 0.9107 0.01280 0.00646 -0.0977 0.6581 1.0000
4.250 0.9265 0.01289 0.00648 -0.0956 0.6448 1.0000
4.500 0.9432 0.01301 0.00652 -0.0936 0.6315 1.0000
4.750 0.9588 0.01315 0.00662 -0.0914 0.6177 1.0000
5.000 0.9723 0.01332 0.00675 -0.0887 0.6035 1.0000
5.250 0.9867 0.01351 0.00690 -0.0862 0.5893 1.0000
5.500 1.0017 0.01371 0.00706 -0.0838 0.5753 1.0000
5.750 1.0172 0.01393 0.00724 -0.0815 0.5613 1.0000
6.000 1.0329 0.01416 0.00742 -0.0792 0.5473 1.0000
6.250 1.0487 0.01441 0.00761 -0.0770 0.5334 1.0000
6.500 1.0649 0.01468 0.00782 -0.0748 0.5195 1.0000
6.750 1.0793 0.01495 0.00809 -0.0724 0.5052 1.0000
7.000 1.0938 0.01524 0.00836 -0.0700 0.4908 1.0000
7.250 1.1086 0.01555 0.00865 -0.0676 0.4764 1.0000
7.500 1.1231 0.01587 0.00897 -0.0653 0.4621 1.0000
7.750 1.1366 0.01621 0.00929 -0.0628 0.4481 1.0000
8.000 1.1499 0.01658 0.00963 -0.0603 0.4341 1.0000
8.250 1.1632 0.01698 0.01000 -0.0578 0.4201 1.0000
8.500 1.1763 0.01742 0.01041 -0.0554 0.4059 1.0000
8.750 1.1888 0.01789 0.01086 -0.0530 0.3915 1.0000
9.000 1.2006 0.01838 0.01136 -0.0505 0.3766 1.0000
9.250 1.2121 0.01892 0.01191 -0.0481 0.3616 1.0000
9.500 1.2231 0.01950 0.01249 -0.0456 0.3464 1.0000
9.750 1.2335 0.02013 0.01312 -0.0432 0.3309 1.0000
10.000 1.2434 0.02082 0.01381 -0.0408 0.3153 1.0000
10.250 1.2526 0.02157 0.01457 -0.0384 0.2995 1.0000
10.500 1.2613 0.02240 0.01539 -0.0360 0.2837 1.0000
10.750 1.2692 0.02331 0.01629 -0.0336 0.2678 1.0000
11.000 1.2765 0.02431 0.01728 -0.0313 0.2518 1.0000
11.250 1.2829 0.02541 0.01836 -0.0290 0.2359 1.0000
11.500 1.2890 0.02659 0.01954 -0.0268 0.2199 1.0000
11.750 1.2945 0.02787 0.02082 -0.0247 0.2036 1.0000
12.000 1.2991 0.02927 0.02221 -0.0226 0.1875 1.0000
12.250 1.3025 0.03081 0.02375 -0.0206 0.1716 1.0000
12.500 1.3047 0.03252 0.02543 -0.0186 0.1562 1.0000
12.750 1.3057 0.03439 0.02729 -0.0167 0.1415 1.0000
13.000 1.3056 0.03645 0.02932 -0.0149 0.1277 1.0000
13.250 1.3045 0.03868 0.03155 -0.0132 0.1150 1.0000
13.500 1.3025 0.04110 0.03395 -0.0116 0.1037 1.0000
13.750 1.2990 0.04375 0.03659 -0.0102 0.0942 1.0000
14.000 1.2940 0.04665 0.03945 -0.0090 0.0863 1.0000
14.250 1.2934 0.04925 0.04213 -0.0080 0.0787 1.0000
14.500 1.2883 0.05233 0.04522 -0.0070 0.0733 1.0000
14.750 1.2873 0.05513 0.04809 -0.0064 0.0681 1.0000
15.000 1.2820 0.05835 0.05130 -0.0057 0.0642 1.0000
15.250 1.2825 0.06112 0.05420 -0.0053 0.0603 1.0000
15.500 1.2800 0.06419 0.05728 -0.0050 0.0573 1.0000
15.750 1.2787 0.06711 0.06024 -0.0045 0.0545 1.0000
16.000 1.2794 0.06998 0.06323 -0.0044 0.0518 1.0000
16.250 1.2795 0.07288 0.06618 -0.0043 0.0496 1.0000
16.500 1.2821 0.07512 0.06836 -0.0035 0.0475 1.0000
16.750 1.2827 0.07814 0.07157 -0.0036 0.0458 1.0000
17.000 1.2839 0.08103 0.07458 -0.0037 0.0441 1.0000
17.250 1.2859 0.08376 0.07736 -0.0039 0.0425 1.0000
17.500 1.2935 0.08539 0.07891 -0.0030 0.0407 1.0000
17.750 1.2939 0.08843 0.08212 -0.0032 0.0397 1.0000
18.000 1.2936 0.09166 0.08554 -0.0036 0.0387 1.0000
18.250 1.2929 0.09496 0.08899 -0.0041 0.0377 1.0000
18.500 1.2930 0.09814 0.09230 -0.0047 0.0367 1.0000
18.750 1.2946 0.10105 0.09527 -0.0053 0.0358 1.0000
19.000 1.3038 0.10256 0.09674 -0.0048 0.0346 1.0000
19.250 1.2995 0.10644 0.10080 -0.0056 0.0340 1.0000
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Polar data table (+)
Polar graphs
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