MRC-20 (mrc-20-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 100,000 Max Cl/Cd: 50.82 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-20-il-100000.txt Download as CSV file: xf-mrc-20-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4386 0.10844 0.10395 -0.0375 1.0000 0.0907
-9.000 -0.4423 0.10600 0.10157 -0.0359 1.0000 0.0929
-8.750 -0.4537 0.10322 0.09885 -0.0351 1.0000 0.0948
-8.500 -0.4711 0.10013 0.09583 -0.0348 1.0000 0.0964
-8.250 -0.4956 0.09666 0.09244 -0.0349 1.0000 0.0972
-8.000 -0.5262 0.09346 0.08930 -0.0342 1.0000 0.0970
-7.750 -0.5563 0.09089 0.08675 -0.0319 1.0000 0.0970
-7.500 -0.5812 0.08793 0.08375 -0.0303 1.0000 0.0980
-7.250 -0.6078 0.08520 0.08088 -0.0287 1.0000 0.0999
-7.000 -0.6432 0.08485 0.08004 -0.0261 1.0000 0.1017
-6.750 -0.6377 0.07824 0.07361 -0.0256 1.0000 0.1037
-6.500 -0.6287 0.07491 0.07043 -0.0240 1.0000 0.1065
-6.250 -0.6240 0.07213 0.06759 -0.0233 0.9991 0.1113
-6.000 -0.6068 0.06759 0.06271 -0.0273 0.9922 0.1215
-5.750 -0.5861 0.06449 0.05924 -0.0304 0.9852 0.1363
-4.500 -0.4824 0.04904 0.04349 -0.0369 0.9515 0.2544
-4.250 -0.4494 0.04646 0.04086 -0.0389 0.9464 0.2820
-4.000 -0.4287 0.04382 0.03815 -0.0386 0.9385 0.2955
-3.750 -0.3544 0.04288 0.03516 -0.0428 0.9325 0.1669
-3.500 -0.3041 0.03924 0.03050 -0.0412 0.9270 0.0795
-3.250 -0.2683 0.03863 0.02927 -0.0413 0.9199 0.0735
-3.000 -0.2234 0.03665 0.02713 -0.0442 0.9161 0.0726
-2.750 -0.2008 0.03532 0.02570 -0.0432 0.9072 0.0715
-2.500 -0.1589 0.03407 0.02434 -0.0453 0.9025 0.0711
-2.250 -0.1315 0.03326 0.02348 -0.0450 0.8945 0.0721
-2.000 -0.0962 0.03221 0.02251 -0.0464 0.8887 0.0766
-1.750 -0.0648 0.03153 0.02193 -0.0471 0.8821 0.0830
-1.500 -0.0368 0.03084 0.02121 -0.0472 0.8742 0.0901
-1.250 0.0073 0.02997 0.02030 -0.0502 0.8703 0.1186
-1.000 0.0092 0.02745 0.02044 -0.0449 0.8610 0.7054
-0.750 0.0275 0.02754 0.02087 -0.0394 0.8557 0.8279
-0.500 0.0335 0.02785 0.02126 -0.0335 0.8450 0.8811
-0.250 0.0914 0.02876 0.02207 -0.0354 0.8416 0.9479
0.000 0.1445 0.02903 0.02215 -0.0411 0.8339 0.9611
0.250 0.2078 0.02906 0.02199 -0.0485 0.8281 0.9715
0.500 0.2822 0.02883 0.02159 -0.0577 0.8252 0.9780
0.750 0.3361 0.02896 0.02162 -0.0640 0.8159 0.9896
1.000 0.4070 0.02853 0.02109 -0.0727 0.8119 0.9974
1.250 0.4650 0.02773 0.02019 -0.0787 0.8090 1.0000
1.500 0.4457 0.02752 0.01993 -0.0715 0.7947 1.0000
1.750 0.4369 0.02745 0.01978 -0.0658 0.7814 1.0000
2.000 0.4874 0.02665 0.01890 -0.0695 0.7783 1.0000
2.250 0.4888 0.02681 0.01898 -0.0651 0.7653 1.0000
2.500 0.5434 0.02584 0.01797 -0.0693 0.7628 1.0000
2.750 0.5510 0.02602 0.01809 -0.0658 0.7503 1.0000
3.000 0.6086 0.02497 0.01703 -0.0704 0.7475 1.0000
3.250 0.6215 0.02506 0.01708 -0.0677 0.7357 1.0000
3.500 0.6790 0.02398 0.01600 -0.0723 0.7320 1.0000
3.750 0.6977 0.02397 0.01599 -0.0705 0.7206 1.0000
4.000 0.7545 0.02290 0.01492 -0.0750 0.7157 1.0000
4.250 0.7739 0.02290 0.01491 -0.0733 0.7037 1.0000
4.500 0.8365 0.02178 0.01381 -0.0788 0.6979 1.0000
4.750 0.8533 0.02188 0.01390 -0.0767 0.6846 1.0000
5.000 0.8772 0.02185 0.01387 -0.0757 0.6720 1.0000
5.250 0.9112 0.02160 0.01363 -0.0765 0.6605 1.0000
5.500 0.9563 0.02113 0.01312 -0.0792 0.6494 1.0000
5.750 0.9751 0.02129 0.01329 -0.0774 0.6350 1.0000
6.000 0.9962 0.02144 0.01346 -0.0761 0.6207 1.0000
6.250 1.0189 0.02159 0.01360 -0.0750 0.6065 1.0000
6.500 1.0424 0.02174 0.01375 -0.0741 0.5921 1.0000
6.750 1.0663 0.02190 0.01392 -0.0732 0.5776 1.0000
7.000 1.0898 0.02209 0.01410 -0.0724 0.5629 1.0000
7.250 1.1128 0.02231 0.01430 -0.0714 0.5480 1.0000
7.500 1.1351 0.02256 0.01455 -0.0703 0.5330 1.0000
7.750 1.1563 0.02285 0.01482 -0.0691 0.5176 1.0000
8.000 1.1764 0.02317 0.01513 -0.0676 0.5021 1.0000
8.250 1.1952 0.02352 0.01548 -0.0660 0.4864 1.0000
8.500 1.2127 0.02390 0.01586 -0.0642 0.4705 1.0000
8.750 1.2288 0.02431 0.01627 -0.0622 0.4544 1.0000
9.000 1.2437 0.02475 0.01672 -0.0600 0.4383 1.0000
9.250 1.2571 0.02522 0.01720 -0.0576 0.4221 1.0000
9.500 1.2688 0.02572 0.01772 -0.0549 0.4058 1.0000
9.750 1.2787 0.02625 0.01825 -0.0520 0.3896 1.0000
10.000 1.2862 0.02680 0.01881 -0.0486 0.3736 1.0000
10.250 1.2924 0.02741 0.01944 -0.0452 0.3575 1.0000
10.500 1.2972 0.02810 0.02013 -0.0417 0.3414 1.0000
10.750 1.3008 0.02886 0.02091 -0.0382 0.3254 1.0000
11.000 1.3032 0.02971 0.02178 -0.0347 0.3092 1.0000
11.250 1.3045 0.03066 0.02275 -0.0312 0.2931 1.0000
11.500 1.3049 0.03174 0.02386 -0.0278 0.2769 1.0000
11.750 1.3046 0.03294 0.02507 -0.0245 0.2606 1.0000
12.000 1.3033 0.03430 0.02644 -0.0214 0.2445 1.0000
12.250 1.3014 0.03581 0.02795 -0.0184 0.2284 1.0000
12.500 1.2987 0.03749 0.02963 -0.0156 0.2125 1.0000
12.750 1.2954 0.03935 0.03147 -0.0129 0.1970 1.0000
13.000 1.2915 0.04138 0.03349 -0.0105 0.1821 1.0000
13.250 1.2875 0.04358 0.03566 -0.0083 0.1678 1.0000
13.500 1.2835 0.04591 0.03798 -0.0063 0.1543 1.0000
13.750 1.2800 0.04836 0.04041 -0.0045 0.1419 1.0000
14.000 1.2778 0.05083 0.04284 -0.0030 0.1307 1.0000
14.250 1.2779 0.05321 0.04514 -0.0016 0.1206 1.0000
14.500 1.2764 0.05578 0.04775 -0.0004 0.1118 1.0000
14.750 1.2773 0.05836 0.05044 0.0007 0.1040 1.0000
15.000 1.2855 0.06034 0.05226 0.0017 0.0965 1.0000
15.250 1.2828 0.06330 0.05547 0.0026 0.0913 1.0000
15.500 1.2979 0.06492 0.05692 0.0035 0.0851 1.0000
15.750 1.2923 0.06826 0.06058 0.0042 0.0817 1.0000
16.000 1.2961 0.07075 0.06314 0.0047 0.0777 1.0000
16.250 1.3108 0.07281 0.06518 0.0055 0.0739 1.0000
16.500 1.3023 0.07665 0.06936 0.0059 0.0720 1.0000
16.750 1.2957 0.08042 0.07336 0.0060 0.0700 1.0000
17.000 1.2920 0.08388 0.07698 0.0060 0.0679 1.0000
17.250 1.3120 0.08563 0.07860 0.0067 0.0647 1.0000
17.500 1.2924 0.09079 0.08409 0.0060 0.0642 1.0000
17.750 1.2715 0.09648 0.09009 0.0048 0.0639 1.0000
18.000 1.2484 0.10279 0.09669 0.0028 0.0637 1.0000
18.250 1.2230 0.10982 0.10399 0.0001 0.0636 1.0000
18.500 1.1946 0.11779 0.11222 -0.0036 0.0637 1.0000
18.750 1.1635 0.12687 0.12153 -0.0085 0.0640 1.0000
19.000 1.1297 0.13722 0.13208 -0.0145 0.0645 1.0000
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Polar data table (+)
Polar graphs
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