MRC-20 (mrc-20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 200,000 Max Cl/Cd: 68.42 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-20-il-200000-n5.txt Download as CSV file: xf-mrc-20-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2869 0.08592 0.08222 -0.0853 0.9749 0.0287
-9.500 -0.2903 0.07851 0.07480 -0.0932 0.9715 0.0286
-9.000 -0.3615 0.06052 0.05623 -0.1015 0.9519 0.0183
-8.750 -0.3541 0.05760 0.05322 -0.1026 0.9484 0.0181
-8.500 -0.3515 0.05470 0.05019 -0.1022 0.9436 0.0178
-8.250 -0.3531 0.05208 0.04741 -0.1001 0.9363 0.0176
-8.000 -0.3440 0.04857 0.04367 -0.1001 0.9327 0.0173
-7.750 -0.3438 0.04592 0.04081 -0.0971 0.9255 0.0171
-7.500 -0.3360 0.04273 0.03735 -0.0954 0.9202 0.0169
-7.250 -0.3209 0.03927 0.03354 -0.0946 0.9172 0.0167
-7.000 -0.3158 0.03688 0.03089 -0.0912 0.9099 0.0167
-6.750 -0.3007 0.03429 0.02796 -0.0895 0.9053 0.0173
-6.500 -0.2800 0.03113 0.02429 -0.0884 0.9025 0.0179
-6.250 -0.2543 0.02871 0.02149 -0.0884 0.9007 0.0180
-6.000 -0.2454 0.02736 0.01992 -0.0848 0.8921 0.0180
-5.750 -0.2190 0.02553 0.01781 -0.0845 0.8892 0.0181
-5.500 -0.1892 0.02388 0.01586 -0.0849 0.8871 0.0183
-5.250 -0.1582 0.02250 0.01439 -0.0857 0.8854 0.0186
-5.000 -0.1452 0.02183 0.01368 -0.0829 0.8770 0.0190
-4.750 -0.1171 0.02085 0.01263 -0.0830 0.8739 0.0195
-4.500 -0.0871 0.01988 0.01158 -0.0835 0.8715 0.0201
-4.250 -0.0678 0.01925 0.01089 -0.0819 0.8653 0.0211
-4.000 -0.0447 0.01859 0.01017 -0.0810 0.8601 0.0224
-3.750 -0.0168 0.01789 0.00948 -0.0812 0.8569 0.0238
-3.500 0.0056 0.01728 0.00883 -0.0802 0.8517 0.0248
-3.250 0.0257 0.01677 0.00826 -0.0787 0.8451 0.0259
-3.000 0.0532 0.01611 0.00758 -0.0788 0.8413 0.0275
-2.750 0.0750 0.01571 0.00715 -0.0777 0.8349 0.0297
-2.500 0.0993 0.01530 0.00671 -0.0771 0.8287 0.0337
-2.250 0.1295 0.01480 0.00615 -0.0776 0.8247 0.0398
-2.000 0.1498 0.01451 0.00587 -0.0761 0.8165 0.0511
-1.750 0.1749 0.01375 0.00541 -0.0759 0.8108 0.1435
-1.500 0.1826 0.01212 0.00520 -0.0727 0.8029 0.5431
-1.250 0.2072 0.01185 0.00512 -0.0719 0.7960 0.6129
-1.000 0.2318 0.01167 0.00510 -0.0709 0.7890 0.6670
-0.750 0.2568 0.01155 0.00504 -0.0701 0.7809 0.7017
-0.500 0.2856 0.01145 0.00489 -0.0702 0.7734 0.7139
-0.250 0.3135 0.01137 0.00477 -0.0702 0.7648 0.7235
0.000 0.3414 0.01131 0.00466 -0.0702 0.7563 0.7345
0.250 0.3699 0.01124 0.00456 -0.0703 0.7477 0.7464
0.500 0.3963 0.01122 0.00452 -0.0699 0.7382 0.7590
0.750 0.4258 0.01117 0.00442 -0.0702 0.7296 0.7725
1.000 0.4507 0.01118 0.00443 -0.0696 0.7190 0.7871
1.500 0.5051 0.01119 0.00440 -0.0692 0.6987 0.8193
1.750 0.5306 0.01124 0.00446 -0.0687 0.6875 0.8370
2.000 0.5576 0.01129 0.00450 -0.0685 0.6766 0.8549
2.500 0.6139 0.01148 0.00465 -0.0685 0.6533 0.8913
2.750 0.6438 0.01161 0.00476 -0.0690 0.6413 0.9089
3.000 0.6752 0.01176 0.00486 -0.0699 0.6289 0.9251
3.250 0.7074 0.01192 0.00497 -0.0709 0.6163 0.9402
3.500 0.7408 0.01211 0.00512 -0.0723 0.6026 0.9533
3.750 0.7743 0.01230 0.00527 -0.0738 0.5888 0.9654
4.000 0.8077 0.01250 0.00543 -0.0754 0.5749 0.9767
4.250 0.8417 0.01272 0.00561 -0.0771 0.5605 0.9869
4.500 0.8765 0.01296 0.00580 -0.0790 0.5458 0.9956
4.750 0.9018 0.01318 0.00597 -0.0790 0.5317 1.0000
5.000 0.9149 0.01338 0.00611 -0.0762 0.5189 1.0000
5.250 0.9281 0.01358 0.00627 -0.0735 0.5058 1.0000
5.500 0.9418 0.01380 0.00644 -0.0710 0.4927 1.0000
5.750 0.9561 0.01403 0.00664 -0.0685 0.4798 1.0000
6.000 0.9702 0.01429 0.00686 -0.0660 0.4670 1.0000
6.250 0.9838 0.01457 0.00709 -0.0635 0.4542 1.0000
6.500 0.9982 0.01486 0.00735 -0.0611 0.4411 1.0000
6.750 1.0135 0.01517 0.00764 -0.0590 0.4280 1.0000
7.000 1.0291 0.01551 0.00797 -0.0570 0.4150 1.0000
7.250 1.0448 0.01588 0.00831 -0.0551 0.4021 1.0000
7.500 1.0602 0.01629 0.00869 -0.0531 0.3889 1.0000
8.000 1.0911 0.01716 0.00955 -0.0495 0.3619 1.0000
8.250 1.1066 0.01764 0.01001 -0.0477 0.3482 1.0000
8.500 1.1216 0.01814 0.01052 -0.0459 0.3345 1.0000
8.750 1.1361 0.01869 0.01106 -0.0441 0.3206 1.0000
9.000 1.1499 0.01929 0.01165 -0.0423 0.3062 1.0000
9.250 1.1631 0.01993 0.01228 -0.0404 0.2915 1.0000
9.500 1.1757 0.02063 0.01296 -0.0385 0.2763 1.0000
9.750 1.1877 0.02138 0.01370 -0.0366 0.2608 1.0000
10.000 1.1989 0.02220 0.01449 -0.0347 0.2449 1.0000
10.250 1.2095 0.02308 0.01536 -0.0328 0.2288 1.0000
10.500 1.2194 0.02404 0.01630 -0.0309 0.2130 1.0000
10.750 1.2287 0.02507 0.01730 -0.0290 0.1975 1.0000
11.000 1.2374 0.02617 0.01838 -0.0272 0.1824 1.0000
11.250 1.2456 0.02735 0.01954 -0.0254 0.1678 1.0000
11.500 1.2531 0.02861 0.02078 -0.0236 0.1538 1.0000
11.750 1.2600 0.02995 0.02212 -0.0219 0.1405 1.0000
12.000 1.2663 0.03138 0.02354 -0.0202 0.1279 1.0000
12.250 1.2719 0.03290 0.02506 -0.0186 0.1161 1.0000
12.500 1.2768 0.03453 0.02669 -0.0170 0.1053 1.0000
12.750 1.2807 0.03629 0.02846 -0.0155 0.0953 1.0000
13.000 1.2841 0.03816 0.03035 -0.0142 0.0863 1.0000
13.250 1.2882 0.04004 0.03227 -0.0130 0.0781 1.0000
13.500 1.2909 0.04210 0.03437 -0.0118 0.0711 1.0000
14.000 1.2948 0.04658 0.03896 -0.0099 0.0595 1.0000
14.250 1.2948 0.04913 0.04155 -0.0092 0.0551 1.0000
14.500 1.2961 0.05161 0.04413 -0.0085 0.0509 1.0000
15.000 1.2948 0.05722 0.04991 -0.0077 0.0448 1.0000
15.250 1.2931 0.06028 0.05305 -0.0075 0.0423 1.0000
15.500 1.2888 0.06370 0.05653 -0.0075 0.0403 1.0000
15.750 1.2878 0.06681 0.05978 -0.0075 0.0383 1.0000
16.000 1.2849 0.07022 0.06330 -0.0077 0.0365 1.0000
16.250 1.2798 0.07402 0.06718 -0.0082 0.0351 1.0000
16.500 1.2739 0.07797 0.07123 -0.0087 0.0339 1.0000
16.750 1.2707 0.08162 0.07501 -0.0093 0.0326 1.0000
17.000 1.2664 0.08549 0.07901 -0.0101 0.0315 1.0000
17.250 1.2612 0.08955 0.08318 -0.0110 0.0305 1.0000
17.500 1.2549 0.09384 0.08756 -0.0121 0.0297 1.0000
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Polar data table (+)
Polar graphs
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