MRC-20 (mrc-20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.48 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-20-il-1000000.txt Download as CSV file: xf-mrc-20-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2415 0.08586 0.08406 -0.0997 0.9851 0.0124
-10.750 -0.2393 0.08135 0.07955 -0.1028 0.9823 0.0125
-10.500 -0.2402 0.07584 0.07405 -0.1071 0.9785 0.0126
-10.250 -0.2557 0.06674 0.06490 -0.1157 0.9734 0.0126
-10.000 -0.2772 0.06103 0.05910 -0.1193 0.9656 0.0126
-9.750 -0.2956 0.05712 0.05509 -0.1200 0.9587 0.0126
-9.500 -0.3094 0.05417 0.05206 -0.1190 0.9511 0.0126
-9.250 -0.3197 0.05179 0.04957 -0.1168 0.9453 0.0127
-9.000 -0.3212 0.04928 0.04696 -0.1156 0.9398 0.0128
-8.750 -0.3197 0.04685 0.04441 -0.1143 0.9349 0.0129
-8.500 -0.3156 0.04440 0.04183 -0.1129 0.9307 0.0131
-8.250 -0.3091 0.04183 0.03912 -0.1116 0.9258 0.0133
-8.000 -0.3010 0.03913 0.03627 -0.1101 0.9212 0.0136
-7.750 -0.2911 0.03628 0.03322 -0.1085 0.9173 0.0140
-7.500 -0.2837 0.03136 0.02768 -0.1045 0.9121 0.0151
-7.250 -0.2774 0.02725 0.02337 -0.1028 0.9072 0.0154
-7.000 -0.2586 0.02587 0.02190 -0.1020 0.9035 0.0156
-6.750 -0.2532 0.01770 0.01270 -0.0972 0.8989 0.0124
-6.500 -0.2305 0.01624 0.01109 -0.0965 0.8947 0.0125
-6.250 -0.2063 0.01516 0.00990 -0.0960 0.8907 0.0126
-6.000 -0.1812 0.01427 0.00892 -0.0957 0.8871 0.0128
-5.750 -0.1564 0.01350 0.00807 -0.0953 0.8831 0.0129
-5.500 -0.1321 0.01282 0.00734 -0.0947 0.8782 0.0130
-5.250 -0.1075 0.01222 0.00668 -0.0942 0.8737 0.0132
-5.000 -0.0825 0.01170 0.00610 -0.0938 0.8692 0.0134
-4.750 -0.0585 0.01129 0.00567 -0.0932 0.8637 0.0138
-4.500 -0.0339 0.01087 0.00521 -0.0927 0.8583 0.0143
-4.250 -0.0093 0.01048 0.00475 -0.0921 0.8530 0.0147
-4.000 0.0150 0.01016 0.00440 -0.0915 0.8467 0.0150
-3.750 0.0371 0.00959 0.00375 -0.0905 0.8406 0.0156
-3.500 0.0615 0.00931 0.00347 -0.0899 0.8339 0.0164
-3.250 0.0868 0.00908 0.00319 -0.0895 0.8270 0.0172
-3.000 0.1123 0.00888 0.00296 -0.0891 0.8201 0.0179
-2.750 0.1371 0.00863 0.00266 -0.0886 0.8123 0.0190
-2.500 0.1628 0.00847 0.00248 -0.0882 0.8049 0.0209
-2.250 0.1882 0.00830 0.00229 -0.0878 0.7966 0.0235
-2.000 0.2139 0.00815 0.00212 -0.0874 0.7888 0.0286
-1.750 0.2381 0.00791 0.00196 -0.0868 0.7800 0.0621
-1.500 0.2487 0.00650 0.00163 -0.0841 0.7710 0.4159
-1.250 0.2701 0.00617 0.00158 -0.0830 0.7617 0.5195
-1.000 0.2950 0.00607 0.00157 -0.0825 0.7521 0.5610
-0.750 0.3201 0.00603 0.00155 -0.0820 0.7425 0.5881
-0.500 0.3455 0.00602 0.00155 -0.0816 0.7321 0.6116
-0.250 0.3700 0.00598 0.00157 -0.0809 0.7217 0.6417
0.000 0.3950 0.00600 0.00158 -0.0804 0.7110 0.6634
0.250 0.4204 0.00602 0.00159 -0.0800 0.6998 0.6734
0.500 0.4462 0.00605 0.00160 -0.0796 0.6887 0.6832
0.750 0.4715 0.00610 0.00162 -0.0792 0.6776 0.6942
1.250 0.5217 0.00619 0.00168 -0.0783 0.6541 0.7184
1.750 0.5710 0.00631 0.00178 -0.0772 0.6305 0.7486
2.000 0.5952 0.00637 0.00185 -0.0766 0.6182 0.7654
2.250 0.6199 0.00642 0.00192 -0.0760 0.6060 0.7832
2.500 0.6441 0.00648 0.00200 -0.0754 0.5940 0.8023
2.750 0.6675 0.00656 0.00209 -0.0746 0.5814 0.8232
3.250 0.7141 0.00672 0.00230 -0.0729 0.5554 0.8683
3.500 0.7373 0.00682 0.00242 -0.0721 0.5425 0.8908
3.750 0.7599 0.00693 0.00255 -0.0710 0.5294 0.9136
4.000 0.7828 0.00708 0.00270 -0.0701 0.5162 0.9364
4.250 0.8075 0.00727 0.00286 -0.0696 0.5023 0.9564
4.500 0.8363 0.00749 0.00303 -0.0701 0.4874 0.9710
4.750 0.8693 0.00772 0.00321 -0.0716 0.4723 0.9805
5.000 0.9029 0.00797 0.00340 -0.0733 0.4572 0.9876
5.250 0.9367 0.00823 0.00360 -0.0750 0.4416 0.9935
5.500 0.9721 0.00850 0.00381 -0.0772 0.4257 0.9970
5.750 1.0028 0.00876 0.00401 -0.0783 0.4102 1.0000
6.000 1.0099 0.00889 0.00411 -0.0742 0.3988 1.0000
6.250 1.0220 0.00908 0.00425 -0.0712 0.3869 1.0000
6.500 1.0373 0.00932 0.00443 -0.0689 0.3742 1.0000
6.750 1.0551 0.00956 0.00463 -0.0672 0.3609 1.0000
7.000 1.0742 0.00982 0.00485 -0.0658 0.3477 1.0000
7.250 1.0933 0.01010 0.00509 -0.0645 0.3343 1.0000
7.500 1.1124 0.01041 0.00535 -0.0632 0.3200 1.0000
7.750 1.1314 0.01075 0.00563 -0.0619 0.3047 1.0000
8.000 1.1498 0.01113 0.00594 -0.0605 0.2886 1.0000
8.250 1.1677 0.01154 0.00629 -0.0591 0.2717 1.0000
8.500 1.1858 0.01196 0.00665 -0.0578 0.2556 1.0000
8.750 1.2032 0.01242 0.00704 -0.0564 0.2395 1.0000
9.000 1.2199 0.01292 0.00747 -0.0548 0.2231 1.0000
9.250 1.2364 0.01345 0.00792 -0.0534 0.2068 1.0000
9.500 1.2523 0.01401 0.00842 -0.0518 0.1908 1.0000
9.750 1.2679 0.01459 0.00893 -0.0503 0.1755 1.0000
10.000 1.2832 0.01521 0.00949 -0.0487 0.1603 1.0000
10.250 1.2974 0.01588 0.01009 -0.0470 0.1454 1.0000
10.500 1.3115 0.01657 0.01073 -0.0454 0.1317 1.0000
10.750 1.3248 0.01732 0.01142 -0.0437 0.1185 1.0000
11.000 1.3373 0.01812 0.01217 -0.0419 0.1056 1.0000
11.250 1.3491 0.01897 0.01297 -0.0402 0.0935 1.0000
11.500 1.3606 0.01986 0.01381 -0.0384 0.0827 1.0000
11.750 1.3714 0.02081 0.01472 -0.0366 0.0730 1.0000
12.000 1.3818 0.02181 0.01569 -0.0349 0.0642 1.0000
12.500 1.4011 0.02396 0.01780 -0.0314 0.0497 1.0000
12.750 1.4107 0.02508 0.01892 -0.0298 0.0439 1.0000
13.000 1.4190 0.02631 0.02015 -0.0282 0.0390 1.0000
13.250 1.4265 0.02764 0.02148 -0.0265 0.0350 1.0000
13.500 1.4360 0.02887 0.02275 -0.0252 0.0320 1.0000
13.750 1.4421 0.03040 0.02429 -0.0237 0.0292 1.0000
14.000 1.4511 0.03174 0.02569 -0.0225 0.0274 1.0000
14.250 1.4576 0.03331 0.02729 -0.0212 0.0256 1.0000
14.500 1.4624 0.03508 0.02911 -0.0199 0.0239 1.0000
14.750 1.4705 0.03663 0.03073 -0.0190 0.0228 1.0000
15.000 1.4758 0.03847 0.03261 -0.0180 0.0216 1.0000
15.250 1.4773 0.04070 0.03489 -0.0169 0.0205 1.0000
15.500 1.4812 0.04277 0.03704 -0.0160 0.0198 1.0000
15.750 1.4864 0.04478 0.03913 -0.0154 0.0192 1.0000
16.000 1.4900 0.04700 0.04142 -0.0148 0.0185 1.0000
16.250 1.4915 0.04949 0.04398 -0.0143 0.0179 1.0000
16.500 1.4896 0.05238 0.04694 -0.0138 0.0173 1.0000
16.750 1.4829 0.05591 0.05056 -0.0133 0.0167 1.0000
17.000 1.4856 0.05846 0.05320 -0.0132 0.0164 1.0000
17.250 1.4863 0.06128 0.05611 -0.0132 0.0160 1.0000
17.500 1.4854 0.06434 0.05926 -0.0133 0.0156 1.0000
17.750 1.4829 0.06762 0.06262 -0.0134 0.0152 1.0000
18.000 1.4789 0.07117 0.06625 -0.0137 0.0149 1.0000
18.250 1.4732 0.07500 0.07017 -0.0142 0.0146 1.0000
18.500 1.4651 0.07922 0.07448 -0.0148 0.0143 1.0000
18.750 1.4540 0.08390 0.07927 -0.0157 0.0141 1.0000
19.000 1.4393 0.08919 0.08466 -0.0168 0.0138 1.0000
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Polar data table (+)
Polar graphs
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