RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 50,000 Max Cl/Cd: 37.5 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32md-il-50000-n5.txt Download as CSV file: xf-raf32md-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 MOD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3856 0.10142 0.09453 -0.0448 1.0000 0.0659
-8.750 -0.3905 0.09863 0.09183 -0.0439 1.0000 0.0654
-8.500 -0.3971 0.09600 0.08929 -0.0427 1.0000 0.0648
-8.250 -0.4068 0.09347 0.08687 -0.0413 1.0000 0.0641
-8.000 -0.4197 0.09113 0.08464 -0.0396 1.0000 0.0635
-7.750 -0.4340 0.08874 0.08237 -0.0380 1.0000 0.0629
-7.500 -0.4456 0.08570 0.07943 -0.0377 1.0000 0.0623
-7.250 -0.4560 0.08217 0.07597 -0.0382 1.0000 0.0616
-7.000 -0.4647 0.07797 0.07182 -0.0398 1.0000 0.0610
-6.750 -0.4707 0.07300 0.06686 -0.0424 1.0000 0.0603
-6.500 -0.4732 0.06758 0.06137 -0.0455 1.0000 0.0603
-6.250 -0.4713 0.06221 0.05583 -0.0486 1.0000 0.0609
-6.000 -0.4567 0.05588 0.04911 -0.0544 0.9975 0.0626
-5.750 -0.4282 0.04895 0.04149 -0.0617 0.9922 0.0641
-5.500 -0.3970 0.04346 0.03522 -0.0668 0.9874 0.0651
-5.250 -0.3661 0.03982 0.03094 -0.0700 0.9826 0.0684
-5.000 -0.3345 0.03791 0.02878 -0.0723 0.9779 0.0723
-4.750 -0.3031 0.03541 0.02569 -0.0741 0.9730 0.0746
-4.500 -0.2692 0.03331 0.02303 -0.0759 0.9686 0.0773
-4.250 -0.2384 0.03193 0.02133 -0.0772 0.9633 0.0823
-4.000 -0.2055 0.03090 0.02009 -0.0786 0.9583 0.0883
-3.750 -0.1749 0.02979 0.01861 -0.0792 0.9529 0.0929
-3.500 -0.1427 0.02884 0.01759 -0.0804 0.9477 0.0985
-3.250 -0.1122 0.02809 0.01662 -0.0811 0.9419 0.1076
-3.000 -0.0801 0.02734 0.01581 -0.0822 0.9364 0.1246
-2.750 -0.0475 0.02654 0.01517 -0.0838 0.9310 0.1645
-2.500 -0.0164 0.02594 0.01487 -0.0851 0.9247 0.2333
-2.250 0.0172 0.02564 0.01488 -0.0867 0.9194 0.3412
-2.000 0.0429 0.02533 0.01486 -0.0867 0.9121 0.4256
-1.750 0.0759 0.02510 0.01489 -0.0876 0.9071 0.5045
-1.500 0.0984 0.02502 0.01491 -0.0865 0.8988 0.5749
-1.250 0.1291 0.02480 0.01483 -0.0867 0.8934 0.6581
-1.000 0.1486 0.02446 0.01481 -0.0845 0.8856 0.7622
-0.750 0.1933 0.02410 0.01450 -0.0876 0.8798 1.0000
-0.500 0.2233 0.02437 0.01447 -0.0885 0.8723 1.0000
-0.250 0.2559 0.02461 0.01445 -0.0898 0.8654 1.0000
0.000 0.2855 0.02490 0.01450 -0.0905 0.8581 1.0000
0.250 0.3162 0.02516 0.01458 -0.0914 0.8508 1.0000
0.500 0.3456 0.02545 0.01471 -0.0920 0.8435 1.0000
0.750 0.3751 0.02573 0.01485 -0.0926 0.8360 1.0000
1.000 0.4043 0.02602 0.01503 -0.0931 0.8287 1.0000
1.250 0.4329 0.02631 0.01523 -0.0934 0.8210 1.0000
1.500 0.4619 0.02660 0.01545 -0.0939 0.8137 1.0000
1.750 0.4898 0.02691 0.01570 -0.0941 0.8058 1.0000
2.000 0.5178 0.02721 0.01599 -0.0943 0.7982 1.0000
2.250 0.5462 0.02750 0.01626 -0.0945 0.7905 1.0000
2.500 0.5716 0.02787 0.01663 -0.0943 0.7820 1.0000
2.750 0.6024 0.02809 0.01687 -0.0948 0.7750 1.0000
3.000 0.6246 0.02855 0.01737 -0.0940 0.7655 1.0000
3.250 0.6586 0.02866 0.01752 -0.0949 0.7592 1.0000
3.500 0.6779 0.02921 0.01815 -0.0938 0.7488 1.0000
3.750 0.7154 0.02919 0.01821 -0.0951 0.7434 1.0000
4.000 0.7325 0.02980 0.01890 -0.0936 0.7320 1.0000
4.250 0.7580 0.03015 0.01938 -0.0932 0.7231 1.0000
4.500 0.7892 0.03026 0.01963 -0.0934 0.7152 1.0000
4.750 0.8085 0.03080 0.02028 -0.0922 0.7040 1.0000
5.000 0.8488 0.03051 0.02020 -0.0935 0.6982 1.0000
5.250 0.8667 0.03105 0.02089 -0.0919 0.6857 1.0000
5.500 0.8883 0.03140 0.02141 -0.0907 0.6736 1.0000
5.750 0.9164 0.03129 0.02149 -0.0899 0.6609 1.0000
6.000 0.9466 0.03087 0.02130 -0.0891 0.6462 1.0000
6.250 0.9757 0.03045 0.02110 -0.0881 0.6300 1.0000
6.500 1.0048 0.02997 0.02084 -0.0869 0.6124 1.0000
6.750 1.0289 0.02924 0.02025 -0.0845 0.5851 1.0000
7.000 1.0515 0.02837 0.01947 -0.0815 0.5480 1.0000
7.250 1.0608 0.02853 0.01969 -0.0777 0.5109 1.0000
7.500 1.0754 0.02868 0.01987 -0.0747 0.4724 1.0000
7.750 1.0842 0.02921 0.02037 -0.0712 0.4237 1.0000
8.000 1.0910 0.03003 0.02095 -0.0676 0.3593 1.0000
8.250 1.0899 0.03159 0.02202 -0.0636 0.2845 1.0000
8.500 1.0842 0.03381 0.02379 -0.0598 0.2238 1.0000
8.750 1.0803 0.03623 0.02586 -0.0568 0.1831 1.0000
9.000 1.0789 0.03866 0.02807 -0.0542 0.1544 1.0000
9.250 1.0793 0.04106 0.03029 -0.0519 0.1335 1.0000
9.500 1.0835 0.04324 0.03243 -0.0500 0.1162 1.0000
9.750 1.0884 0.04543 0.03459 -0.0484 0.1013 1.0000
10.000 1.0944 0.04761 0.03676 -0.0468 0.0898 1.0000
10.250 1.1019 0.04979 0.03893 -0.0453 0.0797 1.0000
10.500 1.1173 0.05167 0.04099 -0.0438 0.0703 1.0000
10.750 1.1362 0.05361 0.04298 -0.0426 0.0626 1.0000
11.000 1.1608 0.05557 0.04526 -0.0415 0.0560 1.0000
11.250 1.1818 0.05795 0.04756 -0.0409 0.0507 1.0000
11.500 1.2000 0.06080 0.05087 -0.0398 0.0477 1.0000
11.750 1.2107 0.06397 0.05442 -0.0386 0.0453 1.0000
12.000 1.2139 0.06714 0.05788 -0.0374 0.0433 1.0000
12.250 1.2144 0.07028 0.06122 -0.0364 0.0416 1.0000
12.500 1.2158 0.07362 0.06467 -0.0357 0.0400 1.0000
12.750 1.2094 0.07779 0.06909 -0.0349 0.0392 1.0000
13.000 1.1959 0.08238 0.07403 -0.0345 0.0389 1.0000
13.250 1.1803 0.08741 0.07939 -0.0347 0.0387 1.0000
13.500 1.1631 0.09284 0.08511 -0.0357 0.0386 1.0000
13.750 1.1444 0.09876 0.09128 -0.0374 0.0386 1.0000
14.000 1.1245 0.10520 0.09794 -0.0399 0.0387 1.0000
14.250 1.1040 0.11224 0.10518 -0.0433 0.0388 1.0000
14.500 1.0838 0.11993 0.11303 -0.0476 0.0390 1.0000
14.750 1.0643 0.12825 0.12147 -0.0526 0.0392 1.0000
15.000 1.0467 0.13707 0.13038 -0.0580 0.0395 1.0000
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Polar data table (+)
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