MRC-16 (mrc-16-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 100,000 Max Cl/Cd: 50.51 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-16-il-100000.txt Download as CSV file: xf-mrc-16-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MRC-16
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3483 0.10731 0.10243 -0.0444 1.0000 0.1206
-9.750 -0.3838 0.10515 0.10045 -0.0477 1.0000 0.1233
-9.500 -0.4197 0.10304 0.09851 -0.0487 1.0000 0.1237
-9.250 -0.3670 0.09876 0.09413 -0.0428 1.0000 0.1288
-9.000 -0.3741 0.09675 0.09219 -0.0409 1.0000 0.1323
-8.750 -0.3971 0.09499 0.09055 -0.0392 1.0000 0.1357
-8.500 -0.4385 0.09369 0.08941 -0.0375 1.0000 0.1374
-8.250 -0.4788 0.09233 0.08821 -0.0350 1.0000 0.1378
-8.000 -0.5193 0.09045 0.08640 -0.0332 1.0000 0.1381
-7.750 -0.5632 0.08820 0.08410 -0.0323 1.0000 0.1387
-7.500 -0.5273 0.08494 0.08099 -0.0274 1.0000 0.1426
-7.250 -0.5335 0.08296 0.07906 -0.0247 1.0000 0.1456
-7.000 -0.5520 0.08030 0.07640 -0.0237 1.0000 0.1496
-6.750 -0.5422 0.07443 0.07042 -0.0299 0.9934 0.1585
-6.500 -0.5304 0.06932 0.06511 -0.0357 0.9851 0.1721
-6.250 -0.5308 0.05157 0.04558 -0.0433 0.9756 0.0956
-6.000 -0.5019 0.04437 0.03777 -0.0450 0.9713 0.0786
-5.750 -0.4782 0.04095 0.03386 -0.0455 0.9643 0.0782
-5.500 -0.4461 0.03758 0.02995 -0.0471 0.9587 0.0776
-5.250 -0.4138 0.03484 0.02668 -0.0483 0.9531 0.0774
-5.000 -0.3824 0.03301 0.02432 -0.0490 0.9462 0.0798
-4.750 -0.3417 0.03086 0.02191 -0.0517 0.9419 0.0844
-4.500 -0.3134 0.02963 0.02055 -0.0519 0.9342 0.0884
-4.250 -0.2747 0.02839 0.01907 -0.0539 0.9286 0.0962
-4.000 -0.2382 0.02729 0.01799 -0.0556 0.9228 0.1057
-3.750 -0.2084 0.02635 0.01712 -0.0561 0.9152 0.1186
-3.500 -0.1667 0.02521 0.01611 -0.0588 0.9108 0.1421
-3.250 -0.1450 0.02442 0.01555 -0.0579 0.9016 0.1745
-3.000 -0.1142 0.02218 0.01481 -0.0591 0.8967 0.4027
-2.750 -0.0978 0.02131 0.01517 -0.0558 0.8891 0.6814
-2.500 -0.0718 0.02140 0.01553 -0.0532 0.8822 0.8059
-2.250 -0.0258 0.02174 0.01580 -0.0540 0.8789 0.8869
-1.750 0.1844 0.02238 0.01578 -0.0801 0.8801 0.9724
-1.500 0.2871 0.02177 0.01490 -0.0946 0.8798 0.9921
-1.250 0.3335 0.02150 0.01449 -0.0992 0.8707 1.0000
-1.000 0.3663 0.02109 0.01394 -0.1005 0.8639 1.0000
-0.750 0.3789 0.02114 0.01392 -0.0985 0.8515 1.0000
-0.500 0.3967 0.02112 0.01381 -0.0971 0.8410 1.0000
-0.250 0.4252 0.02081 0.01340 -0.0973 0.8334 1.0000
0.000 0.4381 0.02095 0.01348 -0.0950 0.8216 1.0000
0.250 0.4656 0.02069 0.01313 -0.0948 0.8143 1.0000
0.500 0.4828 0.02073 0.01311 -0.0931 0.8036 1.0000
0.750 0.4982 0.02086 0.01319 -0.0910 0.7929 1.0000
1.000 0.5287 0.02051 0.01276 -0.0910 0.7863 1.0000
1.250 0.5415 0.02076 0.01297 -0.0885 0.7747 1.0000
1.500 0.5676 0.02059 0.01274 -0.0879 0.7670 1.0000
1.750 0.5878 0.02062 0.01273 -0.0864 0.7571 1.0000
2.000 0.6052 0.02078 0.01286 -0.0844 0.7467 1.0000
2.250 0.6367 0.02044 0.01246 -0.0845 0.7398 1.0000
2.500 0.6515 0.02073 0.01274 -0.0822 0.7283 1.0000
2.750 0.6785 0.02060 0.01256 -0.0816 0.7202 1.0000
3.000 0.7016 0.02060 0.01254 -0.0805 0.7103 1.0000
3.250 0.7201 0.02081 0.01274 -0.0787 0.6995 1.0000
3.500 0.7546 0.02043 0.01231 -0.0792 0.6924 1.0000
3.750 0.7703 0.02075 0.01264 -0.0770 0.6803 1.0000
4.000 0.7916 0.02089 0.01278 -0.0757 0.6697 1.0000
4.250 0.8249 0.02060 0.01245 -0.0760 0.6615 1.0000
4.500 0.8419 0.02091 0.01278 -0.0740 0.6493 1.0000
4.750 0.8633 0.02108 0.01297 -0.0727 0.6381 1.0000
5.000 0.8943 0.02093 0.01278 -0.0727 0.6288 1.0000
5.250 0.9157 0.02111 0.01298 -0.0714 0.6169 1.0000
5.500 0.9359 0.02136 0.01327 -0.0699 0.6047 1.0000
5.750 0.9597 0.02150 0.01341 -0.0689 0.5931 1.0000
6.000 0.9886 0.02147 0.01336 -0.0687 0.5822 1.0000
6.250 1.0112 0.02164 0.01355 -0.0676 0.5696 1.0000
6.500 1.0316 0.02191 0.01387 -0.0662 0.5564 1.0000
6.750 1.0532 0.02215 0.01416 -0.0649 0.5433 1.0000
7.000 1.0760 0.02236 0.01439 -0.0639 0.5301 1.0000
7.250 1.0993 0.02255 0.01459 -0.0629 0.5168 1.0000
7.500 1.1226 0.02276 0.01481 -0.0619 0.5030 1.0000
7.750 1.1455 0.02298 0.01503 -0.0608 0.4889 1.0000
8.000 1.1672 0.02324 0.01530 -0.0596 0.4743 1.0000
8.250 1.1877 0.02354 0.01561 -0.0583 0.4592 1.0000
8.500 1.2068 0.02389 0.01600 -0.0567 0.4436 1.0000
8.750 1.2244 0.02427 0.01641 -0.0549 0.4277 1.0000
9.000 1.2407 0.02469 0.01687 -0.0530 0.4114 1.0000
9.250 1.2559 0.02514 0.01737 -0.0509 0.3949 1.0000
9.500 1.2699 0.02562 0.01790 -0.0487 0.3781 1.0000
9.750 1.2827 0.02614 0.01844 -0.0463 0.3610 1.0000
10.000 1.2941 0.02670 0.01901 -0.0438 0.3440 1.0000
10.250 1.3037 0.02730 0.01962 -0.0411 0.3270 1.0000
10.500 1.3111 0.02797 0.02029 -0.0381 0.3103 1.0000
10.750 1.3154 0.02871 0.02101 -0.0347 0.2941 1.0000
11.000 1.3189 0.02959 0.02185 -0.0314 0.2778 1.0000
11.250 1.3188 0.03065 0.02294 -0.0279 0.2617 1.0000
11.500 1.3178 0.03187 0.02420 -0.0246 0.2456 1.0000
11.750 1.3161 0.03327 0.02562 -0.0216 0.2294 1.0000
12.000 1.3135 0.03486 0.02722 -0.0188 0.2134 1.0000
12.250 1.3100 0.03666 0.02902 -0.0162 0.1976 1.0000
12.500 1.3056 0.03867 0.03104 -0.0139 0.1822 1.0000
12.750 1.3006 0.04091 0.03326 -0.0118 0.1673 1.0000
13.000 1.2949 0.04336 0.03569 -0.0100 0.1531 1.0000
13.250 1.2891 0.04599 0.03830 -0.0084 0.1398 1.0000
13.500 1.2834 0.04876 0.04105 -0.0069 0.1274 1.0000
13.750 1.2784 0.05161 0.04388 -0.0057 0.1163 1.0000
14.000 1.2752 0.05439 0.04658 -0.0046 0.1064 1.0000
14.250 1.2715 0.05730 0.04950 -0.0038 0.0977 1.0000
14.500 1.2690 0.06031 0.05261 -0.0029 0.0898 1.0000
14.750 1.2722 0.06276 0.05494 -0.0020 0.0826 1.0000
15.000 1.2685 0.06601 0.05842 -0.0016 0.0772 1.0000
15.250 1.2771 0.06811 0.06038 -0.0005 0.0714 1.0000
15.500 1.2721 0.07171 0.06426 -0.0003 0.0679 1.0000
15.750 1.2745 0.07440 0.06697 0.0000 0.0640 1.0000
16.000 1.2806 0.07710 0.06971 0.0008 0.0605 1.0000
16.250 1.2734 0.08120 0.07410 0.0006 0.0586 1.0000
16.500 1.2670 0.08532 0.07845 0.0002 0.0568 1.0000
16.750 1.2616 0.08930 0.08260 -0.0003 0.0551 1.0000
17.000 1.2792 0.09099 0.08411 0.0010 0.0519 1.0000
17.250 1.2604 0.09657 0.08999 -0.0007 0.0515 1.0000
17.500 1.2407 0.10267 0.09639 -0.0029 0.0512 1.0000
17.750 1.2193 0.10939 0.10338 -0.0058 0.0509 1.0000
18.000 1.1962 0.11678 0.11103 -0.0094 0.0509 1.0000
18.250 1.1714 0.12496 0.11945 -0.0139 0.0510 1.0000
18.500 1.1449 0.13405 0.12875 -0.0192 0.0513 1.0000
18.750 1.1177 0.14396 0.13884 -0.0252 0.0518 1.0000
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Polar data table (+)
Polar graphs
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