MRC-20 (mrc-20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.08 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-20-il-1000000-n5.txt Download as CSV file: xf-mrc-20-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2735 0.09326 0.09135 -0.0874 0.9568 0.0070
-11.250 -0.2767 0.08832 0.08641 -0.0898 0.9534 0.0070
-9.750 -0.5393 0.02222 0.01796 -0.0993 0.9093 0.0070
-9.500 -0.5223 0.02064 0.01615 -0.0982 0.9054 0.0071
-9.250 -0.5027 0.01948 0.01480 -0.0974 0.9021 0.0072
-9.000 -0.4817 0.01850 0.01365 -0.0967 0.8987 0.0072
-8.750 -0.4604 0.01754 0.01256 -0.0961 0.8947 0.0073
-8.500 -0.4404 0.01632 0.01118 -0.0952 0.8905 0.0074
-8.250 -0.4178 0.01558 0.01033 -0.0946 0.8869 0.0076
-8.000 -0.3944 0.01499 0.00966 -0.0942 0.8831 0.0077
-7.750 -0.3707 0.01446 0.00908 -0.0938 0.8786 0.0078
-7.500 -0.3465 0.01401 0.00856 -0.0934 0.8741 0.0079
-7.250 -0.3223 0.01353 0.00801 -0.0930 0.8700 0.0080
-7.000 -0.2981 0.01308 0.00752 -0.0926 0.8653 0.0081
-6.750 -0.2739 0.01265 0.00703 -0.0921 0.8601 0.0083
-6.500 -0.2496 0.01224 0.00655 -0.0917 0.8552 0.0084
-6.250 -0.2253 0.01185 0.00611 -0.0912 0.8500 0.0086
-6.000 -0.2010 0.01149 0.00569 -0.0907 0.8441 0.0088
-5.750 -0.1763 0.01117 0.00531 -0.0903 0.8387 0.0090
-5.500 -0.1514 0.01088 0.00497 -0.0899 0.8325 0.0093
-5.250 -0.1265 0.01062 0.00466 -0.0895 0.8261 0.0095
-5.000 -0.1024 0.01028 0.00427 -0.0889 0.8198 0.0097
-4.750 -0.0783 0.00997 0.00391 -0.0884 0.8124 0.0101
-4.500 -0.0533 0.00975 0.00366 -0.0880 0.8054 0.0104
-4.250 -0.0281 0.00955 0.00343 -0.0876 0.7974 0.0108
-4.000 -0.0029 0.00938 0.00320 -0.0872 0.7897 0.0112
-3.750 0.0223 0.00921 0.00300 -0.0868 0.7808 0.0116
-3.500 0.0477 0.00907 0.00281 -0.0864 0.7719 0.0120
-3.250 0.0724 0.00893 0.00261 -0.0858 0.7620 0.0125
-3.000 0.0977 0.00880 0.00245 -0.0854 0.7518 0.0132
-2.750 0.1229 0.00871 0.00232 -0.0850 0.7414 0.0142
-2.500 0.1479 0.00864 0.00219 -0.0845 0.7303 0.0155
-2.250 0.1732 0.00856 0.00209 -0.0841 0.7197 0.0174
-2.000 0.1983 0.00850 0.00199 -0.0836 0.7094 0.0200
-1.750 0.2231 0.00845 0.00191 -0.0831 0.6982 0.0252
-1.500 0.2483 0.00837 0.00184 -0.0827 0.6875 0.0361
-1.250 0.2726 0.00828 0.00178 -0.0821 0.6765 0.0621
-1.000 0.2951 0.00806 0.00172 -0.0813 0.6653 0.1348
-0.750 0.3072 0.00686 0.00149 -0.0788 0.6545 0.4644
-0.500 0.3308 0.00676 0.00150 -0.0781 0.6435 0.5157
-0.250 0.3542 0.00669 0.00152 -0.0774 0.6321 0.5633
0.000 0.3783 0.00665 0.00156 -0.0767 0.6202 0.6011
0.250 0.4040 0.00671 0.00158 -0.0764 0.6089 0.6106
0.500 0.4293 0.00678 0.00160 -0.0760 0.5973 0.6170
0.750 0.4545 0.00686 0.00163 -0.0756 0.5853 0.6239
1.000 0.4802 0.00693 0.00167 -0.0753 0.5733 0.6305
1.250 0.5054 0.00701 0.00171 -0.0749 0.5615 0.6385
2.000 0.5802 0.00729 0.00190 -0.0736 0.5239 0.6648
2.250 0.6049 0.00738 0.00197 -0.0731 0.5116 0.6747
2.500 0.6295 0.00749 0.00205 -0.0726 0.4993 0.6848
2.750 0.6536 0.00761 0.00215 -0.0721 0.4862 0.6971
3.000 0.6778 0.00772 0.00225 -0.0715 0.4731 0.7104
3.250 0.7019 0.00782 0.00235 -0.0710 0.4600 0.7243
3.500 0.7253 0.00794 0.00247 -0.0703 0.4475 0.7390
3.750 0.7480 0.00806 0.00259 -0.0694 0.4347 0.7551
4.000 0.7704 0.00819 0.00272 -0.0685 0.4222 0.7737
4.250 0.7932 0.00831 0.00287 -0.0677 0.4093 0.7946
4.500 0.8163 0.00844 0.00303 -0.0670 0.3970 0.8165
4.750 0.8391 0.00859 0.00320 -0.0662 0.3849 0.8389
5.000 0.8613 0.00875 0.00339 -0.0653 0.3730 0.8642
5.250 0.8831 0.00890 0.00359 -0.0643 0.3611 0.8919
5.500 0.9044 0.00907 0.00380 -0.0631 0.3493 0.9220
5.750 0.9277 0.00929 0.00403 -0.0624 0.3372 0.9515
6.000 0.9573 0.00957 0.00427 -0.0633 0.3233 0.9745
6.250 0.9878 0.00987 0.00452 -0.0645 0.3087 0.9915
6.500 1.0132 0.01017 0.00476 -0.0645 0.2947 1.0000
7.000 1.0509 0.01076 0.00525 -0.0617 0.2678 1.0000
7.250 1.0701 0.01109 0.00552 -0.0605 0.2537 1.0000
7.500 1.0889 0.01146 0.00582 -0.0592 0.2391 1.0000
7.750 1.1069 0.01186 0.00616 -0.0578 0.2235 1.0000
8.000 1.1246 0.01231 0.00653 -0.0564 0.2072 1.0000
8.250 1.1417 0.01279 0.00693 -0.0549 0.1902 1.0000
8.500 1.1586 0.01329 0.00736 -0.0534 0.1742 1.0000
8.750 1.1755 0.01380 0.00780 -0.0520 0.1594 1.0000
9.000 1.1920 0.01434 0.00828 -0.0505 0.1448 1.0000
9.250 1.2077 0.01492 0.00879 -0.0490 0.1309 1.0000
9.500 1.2233 0.01553 0.00933 -0.0475 0.1174 1.0000
9.750 1.2384 0.01616 0.00991 -0.0459 0.1052 1.0000
10.000 1.2532 0.01682 0.01052 -0.0444 0.0942 1.0000
10.250 1.2675 0.01752 0.01117 -0.0428 0.0835 1.0000
10.500 1.2813 0.01825 0.01187 -0.0412 0.0742 1.0000
10.750 1.2956 0.01897 0.01257 -0.0398 0.0662 1.0000
11.000 1.3093 0.01973 0.01330 -0.0383 0.0590 1.0000
11.250 1.3224 0.02054 0.01410 -0.0368 0.0522 1.0000
11.500 1.3347 0.02142 0.01496 -0.0352 0.0463 1.0000
11.750 1.3470 0.02231 0.01584 -0.0337 0.0412 1.0000
12.000 1.3597 0.02318 0.01673 -0.0323 0.0373 1.0000
12.250 1.3713 0.02416 0.01771 -0.0309 0.0338 1.0000
12.500 1.3832 0.02513 0.01871 -0.0295 0.0308 1.0000
12.750 1.3940 0.02619 0.01979 -0.0281 0.0281 1.0000
13.000 1.4048 0.02728 0.02090 -0.0268 0.0257 1.0000
13.250 1.4147 0.02846 0.02211 -0.0255 0.0238 1.0000
13.500 1.4254 0.02963 0.02332 -0.0244 0.0223 1.0000
13.750 1.4346 0.03094 0.02467 -0.0231 0.0209 1.0000
14.000 1.4436 0.03228 0.02606 -0.0220 0.0198 1.0000
14.250 1.4528 0.03366 0.02748 -0.0210 0.0187 1.0000
14.500 1.4605 0.03519 0.02907 -0.0199 0.0177 1.0000
14.750 1.4670 0.03689 0.03080 -0.0189 0.0167 1.0000
15.000 1.4748 0.03850 0.03248 -0.0181 0.0161 1.0000
15.250 1.4815 0.04025 0.03429 -0.0173 0.0154 1.0000
15.500 1.4870 0.04214 0.03624 -0.0165 0.0148 1.0000
15.750 1.4913 0.04421 0.03836 -0.0158 0.0142 1.0000
16.000 1.4944 0.04645 0.04067 -0.0151 0.0137 1.0000
16.250 1.4991 0.04859 0.04289 -0.0147 0.0133 1.0000
16.500 1.5025 0.05089 0.04526 -0.0143 0.0130 1.0000
16.750 1.5048 0.05336 0.04781 -0.0139 0.0126 1.0000
17.000 1.5060 0.05600 0.05052 -0.0137 0.0122 1.0000
17.250 1.5060 0.05883 0.05343 -0.0136 0.0119 1.0000
17.500 1.5048 0.06187 0.05654 -0.0135 0.0115 1.0000
17.750 1.5019 0.06515 0.05990 -0.0136 0.0112 1.0000
18.000 1.4996 0.06841 0.06325 -0.0138 0.0110 1.0000
18.250 1.4974 0.07172 0.06666 -0.0141 0.0108 1.0000
18.500 1.4942 0.07522 0.07026 -0.0146 0.0106 1.0000
18.750 1.4899 0.07891 0.07404 -0.0151 0.0104 1.0000
19.000 1.4846 0.08278 0.07800 -0.0158 0.0102 1.0000
19.250 1.4783 0.08681 0.08212 -0.0166 0.0100 1.0000
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Polar data table (+)
Polar graphs
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