GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 500,000 Max Cl/Cd: 74.18 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe627-il-500000.txt Download as CSV file: xf-goe627-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4118 0.10936 0.10709 -0.0397 0.9997 0.0340
-11.750 -0.3934 0.10717 0.10490 -0.0416 0.9983 0.0343
-11.500 -0.6066 0.05455 0.05155 -0.0835 0.9893 0.0295
-11.250 -0.5948 0.05160 0.04854 -0.0853 0.9861 0.0288
-11.000 -0.6106 0.04676 0.04339 -0.0866 0.9820 0.0287
-10.750 -0.6275 0.04331 0.03968 -0.0833 0.9734 0.0286
-10.500 -0.6290 0.03844 0.03430 -0.0832 0.9697 0.0288
-10.250 -0.6364 0.03599 0.03151 -0.0789 0.9613 0.0290
-10.000 -0.6288 0.03249 0.02757 -0.0779 0.9577 0.0296
-9.750 -0.6001 0.03095 0.02604 -0.0791 0.9564 0.0301
-9.500 -0.5637 0.03093 0.02618 -0.0812 0.9555 0.0310
-9.250 -0.5588 0.02972 0.02482 -0.0774 0.9478 0.0314
-9.000 -0.5383 0.02779 0.02262 -0.0768 0.9445 0.0319
-8.750 -0.5125 0.02595 0.02051 -0.0771 0.9425 0.0324
-8.500 -0.4831 0.02443 0.01871 -0.0778 0.9411 0.0330
-8.250 -0.4507 0.02355 0.01757 -0.0788 0.9401 0.0336
-8.000 -0.4431 0.02222 0.01611 -0.0750 0.9317 0.0340
-7.750 -0.4108 0.02090 0.01481 -0.0762 0.9297 0.0349
-7.500 -0.3755 0.01994 0.01382 -0.0778 0.9283 0.0355
-7.250 -0.3378 0.01898 0.01280 -0.0798 0.9272 0.0362
-7.000 -0.2963 0.01804 0.01180 -0.0825 0.9261 0.0371
-6.750 -0.2550 0.01719 0.01086 -0.0851 0.9248 0.0381
-6.500 -0.2345 0.01670 0.01031 -0.0832 0.9176 0.0386
-6.250 -0.2033 0.01570 0.00928 -0.0838 0.9134 0.0392
-6.000 -0.1680 0.01473 0.00834 -0.0853 0.9103 0.0400
-5.750 -0.1309 0.01401 0.00761 -0.0872 0.9074 0.0409
-5.500 -0.1170 0.01364 0.00724 -0.0840 0.8974 0.0416
-5.250 -0.0837 0.01310 0.00668 -0.0849 0.8925 0.0428
-5.000 -0.0636 0.01274 0.00628 -0.0831 0.8832 0.0436
-4.750 -0.0330 0.01229 0.00579 -0.0834 0.8761 0.0444
-4.500 -0.0146 0.01180 0.00529 -0.0812 0.8650 0.0454
-4.250 0.0126 0.01139 0.00485 -0.0809 0.8546 0.0467
-4.000 0.0398 0.01107 0.00448 -0.0805 0.8418 0.0484
-3.750 0.0632 0.01084 0.00420 -0.0793 0.8268 0.0501
-3.500 0.0865 0.01058 0.00389 -0.0781 0.8113 0.0527
-3.250 0.1103 0.01039 0.00365 -0.0770 0.7948 0.0559
-3.000 0.1334 0.01022 0.00342 -0.0758 0.7774 0.0611
-2.750 0.1545 0.01000 0.00319 -0.0742 0.7590 0.0775
-2.500 0.1672 0.00933 0.00295 -0.0712 0.7410 0.1989
-2.250 0.1820 0.00891 0.00285 -0.0686 0.7231 0.3074
-2.000 0.1979 0.00866 0.00276 -0.0660 0.7047 0.3768
-1.750 0.2114 0.00836 0.00270 -0.0630 0.6868 0.4644
-1.500 0.2225 0.00807 0.00266 -0.0593 0.6689 0.5594
-1.250 0.2331 0.00782 0.00265 -0.0555 0.6521 0.6497
-1.000 0.2444 0.00763 0.00270 -0.0516 0.6352 0.7356
-0.750 0.2611 0.00759 0.00277 -0.0489 0.6184 0.7948
-0.500 0.2820 0.00764 0.00287 -0.0470 0.6013 0.8394
-0.250 0.3059 0.00776 0.00298 -0.0458 0.5832 0.8727
0.000 0.3322 0.00794 0.00309 -0.0451 0.5641 0.8980
0.250 0.3614 0.00817 0.00325 -0.0451 0.5435 0.9204
0.500 0.3977 0.00852 0.00349 -0.0466 0.5196 0.9376
0.750 0.4388 0.00892 0.00372 -0.0493 0.4937 0.9438
1.000 0.4671 0.00921 0.00387 -0.0493 0.4717 0.9519
1.250 0.5064 0.00958 0.00409 -0.0517 0.4492 0.9559
1.500 0.5468 0.00997 0.00434 -0.0543 0.4283 0.9597
1.750 0.5778 0.01030 0.00454 -0.0550 0.4107 0.9668
2.000 0.6183 0.01064 0.00476 -0.0577 0.3932 0.9705
2.250 0.6590 0.01096 0.00495 -0.0605 0.3765 0.9739
2.500 0.6945 0.01125 0.00514 -0.0623 0.3618 0.9791
2.750 0.7324 0.01152 0.00531 -0.0645 0.3485 0.9831
3.000 0.7731 0.01179 0.00546 -0.0675 0.3358 0.9861
3.250 0.8096 0.01198 0.00559 -0.0695 0.3252 0.9896
3.500 0.8420 0.01221 0.00575 -0.0707 0.3161 0.9932
3.750 0.8782 0.01238 0.00585 -0.0728 0.3069 0.9956
4.000 0.9138 0.01255 0.00596 -0.0748 0.2990 0.9982
4.250 0.9436 0.01272 0.00609 -0.0756 0.2919 1.0000
4.500 0.9473 0.01288 0.00620 -0.0710 0.2874 1.0000
4.750 0.9524 0.01295 0.00628 -0.0666 0.2836 1.0000
5.000 0.9588 0.01304 0.00638 -0.0624 0.2799 1.0000
5.250 0.9653 0.01317 0.00649 -0.0583 0.2763 1.0000
5.500 0.9723 0.01336 0.00664 -0.0544 0.2726 1.0000
5.750 0.9812 0.01358 0.00684 -0.0508 0.2690 1.0000
6.000 0.9946 0.01371 0.00700 -0.0481 0.2661 1.0000
6.250 1.0080 0.01389 0.00718 -0.0454 0.2628 1.0000
6.500 1.0211 0.01411 0.00738 -0.0427 0.2591 1.0000
6.750 1.0339 0.01441 0.00763 -0.0400 0.2554 1.0000
7.000 1.0489 0.01467 0.00790 -0.0378 0.2524 1.0000
7.250 1.0656 0.01487 0.00813 -0.0358 0.2499 1.0000
7.500 1.0823 0.01510 0.00838 -0.0339 0.2469 1.0000
7.750 1.0980 0.01537 0.00864 -0.0319 0.2434 1.0000
8.000 1.1131 0.01572 0.00896 -0.0298 0.2404 1.0000
8.250 1.1289 0.01612 0.00934 -0.0280 0.2373 1.0000
8.500 1.1471 0.01635 0.00962 -0.0264 0.2352 1.0000
8.750 1.1648 0.01662 0.00993 -0.0249 0.2326 1.0000
9.000 1.1821 0.01693 0.01027 -0.0234 0.2299 1.0000
9.250 1.1988 0.01728 0.01063 -0.0218 0.2273 1.0000
9.500 1.2149 0.01772 0.01105 -0.0201 0.2247 1.0000
9.750 1.2313 0.01822 0.01154 -0.0186 0.2219 1.0000
10.000 1.2492 0.01853 0.01193 -0.0173 0.2202 1.0000
10.250 1.2669 0.01888 0.01233 -0.0160 0.2180 1.0000
10.500 1.2839 0.01926 0.01276 -0.0147 0.2155 1.0000
10.750 1.3003 0.01970 0.01322 -0.0133 0.2130 1.0000
11.000 1.3157 0.02020 0.01372 -0.0118 0.2103 1.0000
11.250 1.3305 0.02084 0.01434 -0.0104 0.2072 1.0000
11.500 1.3472 0.02127 0.01487 -0.0092 0.2055 1.0000
11.750 1.3635 0.02173 0.01541 -0.0080 0.2030 1.0000
12.000 1.3792 0.02224 0.01598 -0.0067 0.2003 1.0000
12.250 1.3935 0.02282 0.01658 -0.0054 0.1970 1.0000
12.500 1.4050 0.02360 0.01734 -0.0039 0.1932 1.0000
12.750 1.4198 0.02421 0.01804 -0.0028 0.1905 1.0000
13.000 1.4349 0.02481 0.01872 -0.0017 0.1873 1.0000
13.250 1.4484 0.02552 0.01949 -0.0006 0.1835 1.0000
13.500 1.4586 0.02646 0.02042 0.0007 0.1796 1.0000
13.750 1.4714 0.02729 0.02132 0.0018 0.1758 1.0000
14.000 1.4852 0.02808 0.02219 0.0027 0.1720 1.0000
14.250 1.4947 0.02917 0.02330 0.0038 0.1671 1.0000
14.500 1.5044 0.03031 0.02449 0.0048 0.1628 1.0000
14.750 1.5158 0.03138 0.02562 0.0056 0.1576 1.0000
15.000 1.5218 0.03287 0.02712 0.0066 0.1528 1.0000
15.250 1.5303 0.03423 0.02855 0.0074 0.1472 1.0000
15.500 1.5351 0.03594 0.03029 0.0083 0.1418 1.0000
15.750 1.5386 0.03782 0.03221 0.0091 0.1363 1.0000
16.000 1.5403 0.03993 0.03434 0.0097 0.1302 1.0000
16.250 1.5398 0.04230 0.03676 0.0104 0.1260 1.0000
16.500 1.5410 0.04460 0.03911 0.0108 0.1211 1.0000
16.750 1.5366 0.04753 0.04208 0.0111 0.1170 1.0000
17.000 1.5343 0.05033 0.04495 0.0113 0.1134 1.0000
17.250 1.5308 0.05332 0.04800 0.0113 0.1097 1.0000
17.500 1.5244 0.05672 0.05147 0.0111 0.1071 1.0000
17.750 1.5136 0.06071 0.05552 0.0107 0.1042 1.0000
18.000 1.5108 0.06386 0.05877 0.0103 0.1021 1.0000
18.250 1.5034 0.06762 0.06261 0.0097 0.0994 1.0000
18.500 1.4921 0.07196 0.06703 0.0088 0.0972 1.0000
18.750 1.4771 0.07686 0.07200 0.0077 0.0951 1.0000
19.000 1.4654 0.08137 0.07660 0.0066 0.0933 1.0000
19.250 1.4582 0.08539 0.08073 0.0055 0.0916 1.0000
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Polar data table (+)
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