GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 200,000 Max Cl/Cd: 73.55 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe532-il-200000-n5.txt Download as CSV file: xf-goe532-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2893 0.11131 0.10748 -0.0365 1.0000 0.0415
-10.500 -0.2930 0.10736 0.10356 -0.0387 1.0000 0.0417
-10.250 -0.2970 0.10330 0.09955 -0.0408 1.0000 0.0418
-10.000 -0.2886 0.10084 0.09713 -0.0397 1.0000 0.0421
-9.750 -0.2736 0.09980 0.09612 -0.0375 1.0000 0.0432
-9.500 -0.2698 0.09742 0.09379 -0.0374 1.0000 0.0442
-9.000 -0.2961 0.08621 0.08266 -0.0420 0.9993 0.0362
-8.750 -0.2803 0.08254 0.07900 -0.0454 0.9883 0.0358
-8.500 -0.2691 0.07769 0.07415 -0.0506 0.9749 0.0357
-8.250 -0.2601 0.07116 0.06761 -0.0587 0.9583 0.0359
-8.000 -0.2492 0.06376 0.06018 -0.0689 0.9390 0.0358
-7.750 -0.2342 0.05231 0.04858 -0.0863 0.9189 0.0352
-7.500 -0.2285 0.04029 0.03593 -0.1000 0.8980 0.0348
-7.250 -0.2145 0.03407 0.02905 -0.1046 0.8808 0.0354
-7.000 -0.1959 0.02993 0.02424 -0.1064 0.8651 0.0360
-6.750 -0.1736 0.02731 0.02113 -0.1069 0.8502 0.0362
-6.500 -0.1501 0.02532 0.01870 -0.1070 0.8350 0.0365
-6.250 -0.1258 0.02389 0.01706 -0.1069 0.8190 0.0368
-6.000 -0.1014 0.02274 0.01570 -0.1065 0.8020 0.0372
-5.750 -0.0766 0.02185 0.01465 -0.1061 0.7843 0.0377
-5.500 -0.0516 0.02108 0.01370 -0.1056 0.7660 0.0384
-5.250 -0.0265 0.02024 0.01264 -0.1050 0.7472 0.0391
-5.000 -0.0013 0.01939 0.01153 -0.1044 0.7278 0.0397
-4.750 0.0241 0.01860 0.01049 -0.1038 0.7077 0.0401
-4.500 0.0496 0.01791 0.00957 -0.1031 0.6877 0.0406
-4.250 0.0751 0.01733 0.00876 -0.1024 0.6691 0.0411
-4.000 0.1009 0.01683 0.00806 -0.1017 0.6523 0.0416
-3.750 0.1264 0.01633 0.00744 -0.1011 0.6377 0.0422
-3.500 0.1522 0.01592 0.00698 -0.1005 0.6244 0.0431
-3.250 0.1783 0.01561 0.00662 -0.1000 0.6128 0.0444
-3.000 0.2044 0.01533 0.00623 -0.0995 0.6015 0.0455
-2.750 0.2306 0.01502 0.00585 -0.0990 0.5900 0.0465
-2.500 0.2569 0.01476 0.00551 -0.0984 0.5791 0.0474
-2.250 0.2829 0.01451 0.00519 -0.0979 0.5680 0.0485
-2.000 0.3094 0.01427 0.00493 -0.0975 0.5580 0.0499
-1.750 0.3359 0.01413 0.00472 -0.0971 0.5489 0.0518
-1.500 0.3629 0.01401 0.00454 -0.0967 0.5406 0.0545
-1.250 0.3896 0.01386 0.00434 -0.0963 0.5324 0.0578
-1.000 0.4166 0.01376 0.00419 -0.0960 0.5243 0.0620
-0.750 0.4436 0.01363 0.00404 -0.0956 0.5166 0.0692
-0.500 0.4702 0.01345 0.00390 -0.0952 0.5104 0.0936
-0.250 0.4954 0.01273 0.00393 -0.0951 0.5042 0.3046
0.000 0.5212 0.01253 0.00401 -0.0947 0.4981 0.4057
0.250 0.5468 0.01242 0.00409 -0.0941 0.4928 0.4882
0.500 0.5714 0.01221 0.00422 -0.0932 0.4868 0.5871
0.750 0.5939 0.01195 0.00434 -0.0917 0.4809 0.7156
1.000 0.6210 0.01163 0.00434 -0.0909 0.4758 0.8553
1.250 0.6633 0.01164 0.00436 -0.0937 0.4699 1.0000
1.500 0.6905 0.01179 0.00441 -0.0934 0.4646 1.0000
1.750 0.7171 0.01197 0.00446 -0.0930 0.4589 1.0000
2.000 0.7441 0.01210 0.00455 -0.0927 0.4525 1.0000
2.250 0.7709 0.01225 0.00464 -0.0923 0.4468 1.0000
2.750 0.8239 0.01258 0.00485 -0.0915 0.4340 1.0000
3.000 0.8500 0.01275 0.00496 -0.0911 0.4267 1.0000
3.250 0.8760 0.01292 0.00508 -0.0906 0.4184 1.0000
3.500 0.9018 0.01309 0.00520 -0.0901 0.4098 1.0000
3.750 0.9276 0.01328 0.00535 -0.0896 0.4019 1.0000
4.000 0.9532 0.01346 0.00551 -0.0891 0.3930 1.0000
4.250 0.9786 0.01365 0.00567 -0.0886 0.3835 1.0000
4.500 1.0031 0.01387 0.00583 -0.0879 0.3718 1.0000
4.750 1.0278 0.01408 0.00602 -0.0873 0.3573 1.0000
5.000 1.0520 0.01432 0.00622 -0.0866 0.3414 1.0000
5.250 1.0753 0.01462 0.00644 -0.0857 0.3209 1.0000
5.500 1.0962 0.01505 0.00671 -0.0846 0.2906 1.0000
5.750 1.1149 0.01564 0.00709 -0.0832 0.2596 1.0000
6.000 1.1339 0.01625 0.00756 -0.0819 0.2384 1.0000
6.250 1.1537 0.01679 0.00802 -0.0806 0.2256 1.0000
6.500 1.1736 0.01732 0.00848 -0.0794 0.2171 1.0000
6.750 1.1944 0.01776 0.00893 -0.0783 0.2109 1.0000
7.000 1.2140 0.01826 0.00941 -0.0771 0.2056 1.0000
7.250 1.2331 0.01876 0.00990 -0.0758 0.2011 1.0000
7.500 1.2529 0.01921 0.01037 -0.0746 0.1970 1.0000
7.750 1.2713 0.01970 0.01089 -0.0732 0.1929 1.0000
8.000 1.2880 0.02027 0.01145 -0.0716 0.1889 1.0000
8.250 1.3033 0.02082 0.01201 -0.0697 0.1855 1.0000
8.500 1.3202 0.02127 0.01254 -0.0681 0.1826 1.0000
8.750 1.3358 0.02180 0.01311 -0.0663 0.1794 1.0000
9.000 1.3499 0.02240 0.01375 -0.0644 0.1757 1.0000
9.250 1.3619 0.02312 0.01448 -0.0624 0.1722 1.0000
9.500 1.3748 0.02383 0.01523 -0.0605 0.1689 1.0000
9.750 1.3902 0.02442 0.01592 -0.0591 0.1654 1.0000
10.000 1.4035 0.02514 0.01671 -0.0574 0.1617 1.0000
10.250 1.4147 0.02601 0.01763 -0.0557 0.1579 1.0000
10.500 1.4228 0.02710 0.01874 -0.0538 0.1541 1.0000
10.750 1.4379 0.02781 0.01958 -0.0527 0.1488 1.0000
11.000 1.4483 0.02883 0.02068 -0.0513 0.1428 1.0000
11.250 1.4583 0.02995 0.02186 -0.0500 0.1369 1.0000
11.500 1.4678 0.03115 0.02313 -0.0487 0.1272 1.0000
11.750 1.4750 0.03259 0.02459 -0.0475 0.1130 1.0000
12.000 1.4760 0.03460 0.02654 -0.0463 0.1024 1.0000
12.250 1.4754 0.03689 0.02879 -0.0452 0.0966 1.0000
12.500 1.4756 0.03924 0.03117 -0.0444 0.0938 1.0000
12.750 1.4750 0.04178 0.03376 -0.0438 0.0915 1.0000
13.000 1.4734 0.04454 0.03658 -0.0433 0.0896 1.0000
13.250 1.4700 0.04760 0.03970 -0.0431 0.0878 1.0000
13.500 1.4696 0.05041 0.04260 -0.0430 0.0864 1.0000
13.750 1.4695 0.05325 0.04555 -0.0429 0.0853 1.0000
14.000 1.4685 0.05626 0.04866 -0.0430 0.0842 1.0000
14.250 1.4666 0.05944 0.05193 -0.0432 0.0830 1.0000
14.500 1.4649 0.06266 0.05525 -0.0435 0.0820 1.0000
14.750 1.4628 0.06597 0.05864 -0.0439 0.0811 1.0000
15.000 1.4610 0.06930 0.06203 -0.0444 0.0802 1.0000
15.250 1.4598 0.07254 0.06531 -0.0448 0.0793 1.0000
15.500 1.4605 0.07550 0.06829 -0.0451 0.0784 1.0000
15.750 1.4635 0.07827 0.07116 -0.0454 0.0776 1.0000
16.000 1.4663 0.08117 0.07419 -0.0460 0.0768 1.0000
16.250 1.4696 0.08401 0.07713 -0.0465 0.0759 1.0000
16.500 1.4723 0.08694 0.08017 -0.0471 0.0749 1.0000
16.750 1.4756 0.08978 0.08310 -0.0477 0.0740 1.0000
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Polar data table (+)
Polar graphs
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