GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 685 AIRFOIL (goe685-il) Reynolds number: 200,000 Max Cl/Cd: 71.88 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe685-il-200000-n5.txt Download as CSV file: xf-goe685-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 685 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6827 0.06490 0.06020 -0.0736 1.0000 0.0369
-12.750 -0.7108 0.05838 0.05357 -0.0777 1.0000 0.0370
-12.500 -0.7350 0.05284 0.04795 -0.0809 1.0000 0.0370
-12.250 -0.7592 0.04787 0.04290 -0.0834 1.0000 0.0371
-12.000 -0.7956 0.04281 0.03774 -0.0855 1.0000 0.0369
-11.750 -0.8143 0.03964 0.03443 -0.0853 1.0000 0.0370
-11.500 -0.8229 0.03765 0.03235 -0.0834 1.0000 0.0373
-11.250 -0.8002 0.03528 0.02981 -0.0869 0.9954 0.0379
-11.000 -0.7767 0.03322 0.02758 -0.0896 0.9905 0.0386
-10.750 -0.7517 0.03139 0.02556 -0.0920 0.9857 0.0395
-10.500 -0.7236 0.02969 0.02364 -0.0945 0.9821 0.0403
-10.250 -0.7000 0.02825 0.02200 -0.0955 0.9765 0.0411
-10.000 -0.6714 0.02691 0.02047 -0.0972 0.9725 0.0417
-9.750 -0.6419 0.02559 0.01912 -0.0989 0.9694 0.0424
-9.500 -0.6178 0.02456 0.01803 -0.0993 0.9633 0.0432
-9.250 -0.5876 0.02357 0.01698 -0.1008 0.9594 0.0443
-9.000 -0.5547 0.02261 0.01592 -0.1027 0.9567 0.0455
-8.750 -0.5281 0.02179 0.01499 -0.1031 0.9511 0.0467
-8.500 -0.4990 0.02100 0.01408 -0.1039 0.9460 0.0478
-8.250 -0.4675 0.02013 0.01315 -0.1053 0.9422 0.0491
-8.000 -0.4385 0.01936 0.01232 -0.1060 0.9374 0.0505
-7.750 -0.4121 0.01871 0.01161 -0.1061 0.9307 0.0522
-7.500 -0.3805 0.01808 0.01087 -0.1071 0.9261 0.0544
-7.250 -0.3511 0.01744 0.01016 -0.1077 0.9209 0.0572
-7.000 -0.3252 0.01685 0.00952 -0.1075 0.9132 0.0608
-6.750 -0.2942 0.01624 0.00885 -0.1082 0.9077 0.0658
-6.500 -0.2681 0.01569 0.00825 -0.1080 0.8989 0.0731
-6.250 -0.2387 0.01505 0.00762 -0.1083 0.8905 0.0858
-6.000 -0.2128 0.01456 0.00718 -0.1079 0.8787 0.1042
-5.750 -0.1838 0.01421 0.00683 -0.1080 0.8685 0.1235
-5.500 -0.1563 0.01398 0.00654 -0.1077 0.8576 0.1376
-5.250 -0.1287 0.01380 0.00627 -0.1074 0.8476 0.1487
-5.000 -0.1002 0.01360 0.00605 -0.1073 0.8384 0.1575
-4.750 -0.0732 0.01345 0.00579 -0.1069 0.8271 0.1649
-4.500 -0.0454 0.01329 0.00561 -0.1067 0.8167 0.1727
-4.250 -0.0174 0.01317 0.00541 -0.1065 0.8056 0.1822
-4.000 0.0100 0.01311 0.00531 -0.1061 0.7937 0.1933
-3.750 0.0378 0.01304 0.00521 -0.1059 0.7826 0.2019
-3.500 0.0659 0.01297 0.00502 -0.1056 0.7713 0.2096
-3.250 0.0931 0.01288 0.00489 -0.1052 0.7592 0.2152
-3.000 0.1206 0.01281 0.00475 -0.1049 0.7478 0.2211
-2.750 0.1484 0.01274 0.00453 -0.1046 0.7369 0.2268
-2.500 0.1754 0.01266 0.00445 -0.1042 0.7257 0.2314
-2.250 0.2027 0.01263 0.00435 -0.1038 0.7149 0.2374
-2.000 0.2299 0.01260 0.00422 -0.1034 0.7036 0.2438
-1.750 0.2567 0.01257 0.00418 -0.1030 0.6921 0.2490
-1.500 0.2837 0.01256 0.00410 -0.1026 0.6815 0.2552
-1.250 0.3106 0.01255 0.00403 -0.1022 0.6702 0.2611
-1.000 0.3372 0.01254 0.00401 -0.1017 0.6581 0.2670
-0.750 0.3637 0.01257 0.00395 -0.1012 0.6447 0.2742
-0.500 0.3898 0.01259 0.00392 -0.1006 0.6305 0.2802
-0.250 0.4159 0.01261 0.00390 -0.1001 0.6158 0.2866
0.000 0.4421 0.01265 0.00386 -0.0995 0.6014 0.2930
0.250 0.4680 0.01266 0.00387 -0.0990 0.5875 0.2985
0.500 0.4939 0.01272 0.00388 -0.0984 0.5739 0.3049
0.750 0.5197 0.01279 0.00388 -0.0978 0.5602 0.3117
1.000 0.5450 0.01285 0.00392 -0.0972 0.5459 0.3181
1.250 0.5704 0.01294 0.00396 -0.0965 0.5313 0.3250
1.500 0.5957 0.01302 0.00400 -0.0959 0.5172 0.3310
1.750 0.6209 0.01311 0.00408 -0.0952 0.5045 0.3376
2.000 0.6461 0.01324 0.00415 -0.0946 0.4933 0.3452
2.250 0.6713 0.01332 0.00425 -0.0940 0.4825 0.3527
2.500 0.6967 0.01344 0.00436 -0.0934 0.4732 0.3618
2.750 0.7218 0.01354 0.00449 -0.0928 0.4650 0.3710
3.000 0.7472 0.01365 0.00462 -0.0922 0.4580 0.3814
3.250 0.7725 0.01375 0.00477 -0.0916 0.4508 0.3926
3.500 0.7973 0.01387 0.00492 -0.0910 0.4441 0.4055
3.750 0.8224 0.01396 0.00509 -0.0904 0.4362 0.4214
4.000 0.8467 0.01406 0.00527 -0.0897 0.4294 0.4438
4.250 0.8715 0.01407 0.00547 -0.0890 0.4240 0.4911
4.500 0.9115 0.01336 0.00576 -0.0914 0.4161 1.0000
4.750 0.9357 0.01362 0.00595 -0.0906 0.4095 1.0000
5.000 0.9603 0.01382 0.00616 -0.0899 0.4019 1.0000
5.250 0.9839 0.01409 0.00638 -0.0891 0.3947 1.0000
5.500 1.0081 0.01430 0.00662 -0.0883 0.3873 1.0000
5.750 1.0314 0.01456 0.00685 -0.0874 0.3794 1.0000
6.000 1.0550 0.01480 0.00712 -0.0866 0.3724 1.0000
6.250 1.0784 0.01504 0.00738 -0.0857 0.3648 1.0000
6.500 1.1005 0.01531 0.00764 -0.0846 0.3551 1.0000
6.750 1.1211 0.01561 0.00792 -0.0833 0.3423 1.0000
7.000 1.1411 0.01592 0.00820 -0.0819 0.3261 1.0000
7.250 1.1604 0.01626 0.00851 -0.0804 0.3081 1.0000
7.500 1.1789 0.01664 0.00885 -0.0788 0.2892 1.0000
7.750 1.1956 0.01710 0.00925 -0.0770 0.2677 1.0000
8.000 1.2098 0.01767 0.00971 -0.0748 0.2436 1.0000
8.250 1.2199 0.01835 0.01025 -0.0719 0.2184 1.0000
8.500 1.2288 0.01912 0.01090 -0.0690 0.1974 1.0000
8.750 1.2388 0.01989 0.01161 -0.0663 0.1834 1.0000
9.000 1.2487 0.02069 0.01236 -0.0637 0.1719 1.0000
9.250 1.2586 0.02151 0.01317 -0.0613 0.1619 1.0000
9.500 1.2702 0.02229 0.01396 -0.0592 0.1513 1.0000
9.750 1.2806 0.02315 0.01483 -0.0570 0.1382 1.0000
10.000 1.2832 0.02450 0.01601 -0.0542 0.0934 1.0000
10.250 1.2804 0.02628 0.01759 -0.0510 0.0797 1.0000
10.500 1.2838 0.02775 0.01907 -0.0487 0.0733 1.0000
10.750 1.2876 0.02928 0.02065 -0.0466 0.0683 1.0000
11.000 1.2917 0.03086 0.02230 -0.0447 0.0646 1.0000
11.250 1.2978 0.03235 0.02389 -0.0431 0.0612 1.0000
11.500 1.3008 0.03417 0.02578 -0.0415 0.0584 1.0000
11.750 1.3038 0.03607 0.02776 -0.0402 0.0561 1.0000
12.000 1.3089 0.03789 0.02967 -0.0391 0.0536 1.0000
12.250 1.3117 0.03997 0.03183 -0.0381 0.0516 1.0000
12.500 1.3122 0.04237 0.03429 -0.0372 0.0500 1.0000
12.750 1.3124 0.04489 0.03689 -0.0365 0.0486 1.0000
13.000 1.3145 0.04730 0.03942 -0.0360 0.0471 1.0000
13.250 1.3152 0.04994 0.04216 -0.0357 0.0458 1.0000
13.500 1.3152 0.05276 0.04506 -0.0355 0.0446 1.0000
13.750 1.3140 0.05580 0.04817 -0.0354 0.0435 1.0000
14.000 1.3108 0.05917 0.05160 -0.0356 0.0426 1.0000
14.250 1.3096 0.06239 0.05490 -0.0358 0.0417 1.0000
14.500 1.3098 0.06549 0.05811 -0.0360 0.0407 1.0000
14.750 1.3099 0.06868 0.06139 -0.0364 0.0397 1.0000
15.000 1.3098 0.07194 0.06475 -0.0369 0.0388 1.0000
15.250 1.3096 0.07529 0.06817 -0.0375 0.0380 1.0000
15.500 1.3091 0.07869 0.07163 -0.0381 0.0372 1.0000
15.750 1.3076 0.08225 0.07522 -0.0388 0.0364 1.0000
16.000 1.3089 0.08547 0.07852 -0.0394 0.0356 1.0000
16.250 1.3107 0.08867 0.08183 -0.0401 0.0348 1.0000
16.500 1.3125 0.09186 0.08512 -0.0408 0.0340 1.0000
16.750 1.3138 0.09519 0.08853 -0.0417 0.0332 1.0000
17.000 1.3152 0.09852 0.09194 -0.0426 0.0324 1.0000
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