GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 500,000 Max Cl/Cd: 87.85 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe617-il-500000.txt Download as CSV file: xf-goe617-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 617 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8467 0.08089 0.07771 -0.0598 1.0000 0.0238
-16.000 -0.8886 0.06962 0.06622 -0.0677 1.0000 0.0237
-15.750 -0.9189 0.06120 0.05759 -0.0735 1.0000 0.0237
-15.500 -0.9417 0.05477 0.05097 -0.0773 1.0000 0.0237
-15.250 -0.9629 0.04928 0.04527 -0.0801 1.0000 0.0239
-15.000 -0.9806 0.04483 0.04066 -0.0812 1.0000 0.0241
-14.750 -0.9895 0.04174 0.03746 -0.0811 1.0000 0.0244
-14.500 -0.9886 0.03994 0.03564 -0.0804 1.0000 0.0248
-14.250 -0.9892 0.03818 0.03382 -0.0793 1.0000 0.0251
-14.000 -0.9866 0.03693 0.03253 -0.0779 1.0000 0.0255
-13.750 -0.9914 0.03507 0.03054 -0.0757 1.0000 0.0258
-13.500 -0.9927 0.03376 0.02913 -0.0731 1.0000 0.0262
-13.250 -0.9945 0.03249 0.02774 -0.0701 1.0000 0.0267
-13.000 -0.9969 0.03131 0.02642 -0.0665 1.0000 0.0271
-12.750 -0.9996 0.03034 0.02531 -0.0625 1.0000 0.0275
-12.500 -1.0038 0.02959 0.02443 -0.0577 1.0000 0.0279
-12.250 -1.0097 0.02895 0.02368 -0.0523 1.0000 0.0280
-12.000 -1.0188 0.02741 0.02201 -0.0467 1.0000 0.0286
-11.750 -1.0198 0.02659 0.02117 -0.0421 1.0000 0.0290
-11.500 -1.0205 0.02610 0.02067 -0.0375 1.0000 0.0295
-11.250 -1.0198 0.02588 0.02045 -0.0330 1.0000 0.0300
-11.000 -0.9960 0.02513 0.01962 -0.0331 0.9982 0.0309
-10.750 -0.9658 0.02427 0.01863 -0.0343 0.9955 0.0319
-10.500 -0.9347 0.02346 0.01765 -0.0357 0.9929 0.0328
-10.250 -0.9081 0.02200 0.01608 -0.0364 0.9893 0.0339
-10.000 -0.8756 0.02127 0.01535 -0.0380 0.9861 0.0350
-9.750 -0.8409 0.02065 0.01468 -0.0399 0.9837 0.0362
-9.500 -0.8085 0.02000 0.01395 -0.0412 0.9811 0.0375
-9.250 -0.7800 0.01944 0.01328 -0.0416 0.9764 0.0384
-9.000 -0.7500 0.01828 0.01207 -0.0426 0.9734 0.0398
-8.750 -0.7158 0.01775 0.01154 -0.0443 0.9712 0.0413
-8.500 -0.6804 0.01720 0.01096 -0.0462 0.9697 0.0428
-8.250 -0.6547 0.01674 0.01044 -0.0459 0.9637 0.0441
-8.000 -0.6223 0.01616 0.00978 -0.0470 0.9606 0.0454
-7.750 -0.5894 0.01539 0.00905 -0.0484 0.9583 0.0475
-7.500 -0.5525 0.01495 0.00860 -0.0504 0.9566 0.0495
-7.250 -0.5206 0.01455 0.00815 -0.0514 0.9527 0.0515
-7.000 -0.4919 0.01400 0.00757 -0.0517 0.9471 0.0539
-6.750 -0.4578 0.01359 0.00718 -0.0531 0.9433 0.0566
-6.500 -0.4210 0.01324 0.00680 -0.0550 0.9402 0.0599
-6.250 -0.3973 0.01282 0.00635 -0.0542 0.9318 0.0631
-6.000 -0.3653 0.01246 0.00601 -0.0551 0.9264 0.0672
-5.750 -0.3366 0.01229 0.00579 -0.0553 0.9194 0.0710
-5.500 -0.3120 0.01179 0.00528 -0.0547 0.9115 0.0759
-5.250 -0.2851 0.01153 0.00500 -0.0544 0.9041 0.0801
-5.000 -0.2595 0.01137 0.00477 -0.0538 0.8957 0.0833
-4.750 -0.2362 0.01096 0.00437 -0.0529 0.8877 0.0888
-4.500 -0.2127 0.01074 0.00413 -0.0519 0.8788 0.0932
-4.250 -0.1875 0.01057 0.00390 -0.0513 0.8706 0.0970
-4.000 -0.1649 0.01030 0.00365 -0.0501 0.8613 0.1033
-3.750 -0.1410 0.01011 0.00345 -0.0491 0.8521 0.1097
-3.500 -0.1173 0.00987 0.00325 -0.0481 0.8427 0.1235
-3.250 -0.0964 0.00955 0.00311 -0.0467 0.8320 0.1633
-3.000 -0.0737 0.00927 0.00294 -0.0455 0.8214 0.2066
-2.750 -0.0526 0.00897 0.00275 -0.0441 0.8092 0.2457
-2.500 -0.0358 0.00845 0.00260 -0.0419 0.7965 0.3407
-2.250 -0.0174 0.00809 0.00248 -0.0399 0.7846 0.4242
-2.000 0.0018 0.00781 0.00237 -0.0380 0.7725 0.4858
-1.750 0.0196 0.00753 0.00228 -0.0358 0.7594 0.5488
-1.500 0.0359 0.00724 0.00222 -0.0332 0.7457 0.6190
-1.250 0.0520 0.00697 0.00217 -0.0304 0.7321 0.6921
-1.000 0.0707 0.00674 0.00220 -0.0281 0.7181 0.7682
-0.750 0.0974 0.00671 0.00229 -0.0274 0.7043 0.8289
-0.500 0.1271 0.00679 0.00237 -0.0274 0.6903 0.8619
-0.250 0.1581 0.00692 0.00246 -0.0278 0.6767 0.8829
0.000 0.1898 0.00706 0.00256 -0.0283 0.6634 0.8981
0.250 0.2191 0.00722 0.00265 -0.0283 0.6493 0.9103
0.500 0.2504 0.00741 0.00276 -0.0288 0.6348 0.9202
0.750 0.2882 0.00769 0.00295 -0.0306 0.6203 0.9285
1.000 0.3246 0.00797 0.00315 -0.0322 0.6087 0.9362
1.250 0.3577 0.00815 0.00328 -0.0331 0.5973 0.9411
1.500 0.4004 0.00840 0.00347 -0.0361 0.5854 0.9434
1.750 0.4413 0.00867 0.00366 -0.0387 0.5719 0.9471
2.000 0.4662 0.00888 0.00381 -0.0379 0.5602 0.9551
2.250 0.5061 0.00903 0.00392 -0.0404 0.5482 0.9566
2.500 0.5452 0.00920 0.00405 -0.0428 0.5372 0.9589
2.750 0.5832 0.00941 0.00419 -0.0450 0.5260 0.9626
3.000 0.6094 0.00958 0.00435 -0.0445 0.5143 0.9692
3.250 0.6505 0.00973 0.00443 -0.0474 0.4980 0.9712
3.500 0.6920 0.00990 0.00453 -0.0504 0.4802 0.9744
3.750 0.7278 0.01006 0.00465 -0.0521 0.4649 0.9791
4.000 0.7604 0.01021 0.00474 -0.0533 0.4481 0.9831
4.250 0.7965 0.01030 0.00476 -0.0552 0.4311 0.9853
4.500 0.8300 0.01042 0.00482 -0.0566 0.4140 0.9880
4.750 0.8614 0.01055 0.00491 -0.0576 0.3979 0.9911
5.000 0.8918 0.01072 0.00502 -0.0584 0.3810 0.9939
5.250 0.9249 0.01084 0.00507 -0.0598 0.3619 0.9960
5.500 0.9570 0.01100 0.00516 -0.0610 0.3420 0.9985
5.750 0.9848 0.01121 0.00530 -0.0614 0.3217 1.0000
6.000 1.0006 0.01148 0.00550 -0.0592 0.3024 1.0000
6.250 1.0157 0.01178 0.00571 -0.0569 0.2783 1.0000
6.500 1.0277 0.01221 0.00598 -0.0541 0.2435 1.0000
6.750 1.0368 0.01277 0.00633 -0.0508 0.2065 1.0000
7.000 1.0469 0.01325 0.00669 -0.0476 0.1855 1.0000
7.250 1.0578 0.01365 0.00704 -0.0445 0.1735 1.0000
7.500 1.0673 0.01408 0.00741 -0.0412 0.1638 1.0000
7.750 1.0792 0.01437 0.00772 -0.0383 0.1563 1.0000
8.000 1.0864 0.01481 0.00811 -0.0345 0.1482 1.0000
8.250 1.0979 0.01506 0.00840 -0.0315 0.1414 1.0000
8.500 1.1022 0.01549 0.00878 -0.0272 0.1338 1.0000
8.750 1.1086 0.01570 0.00903 -0.0231 0.1277 1.0000
9.000 1.1103 0.01605 0.00936 -0.0183 0.1214 1.0000
9.250 1.1166 0.01637 0.00969 -0.0144 0.1158 1.0000
9.500 1.1232 0.01676 0.01006 -0.0107 0.1103 1.0000
9.750 1.1288 0.01727 0.01056 -0.0069 0.1056 1.0000
10.000 1.1393 0.01766 0.01098 -0.0041 0.1013 1.0000
10.250 1.1473 0.01820 0.01152 -0.0011 0.0975 1.0000
10.500 1.1523 0.01893 0.01223 0.0023 0.0939 1.0000
10.750 1.1645 0.01940 0.01278 0.0045 0.0916 1.0000
11.000 1.1750 0.02000 0.01341 0.0068 0.0890 1.0000
11.250 1.1840 0.02072 0.01414 0.0092 0.0862 1.0000
11.500 1.1887 0.02172 0.01514 0.0119 0.0830 1.0000
11.750 1.1997 0.02245 0.01593 0.0138 0.0812 1.0000
12.000 1.2116 0.02317 0.01672 0.0155 0.0793 1.0000
12.250 1.2225 0.02398 0.01759 0.0171 0.0772 1.0000
12.500 1.2313 0.02496 0.01860 0.0188 0.0751 1.0000
12.750 1.2357 0.02629 0.01993 0.0208 0.0724 1.0000
13.000 1.2453 0.02733 0.02104 0.0222 0.0707 1.0000
13.250 1.2576 0.02822 0.02202 0.0232 0.0691 1.0000
13.500 1.2690 0.02921 0.02307 0.0243 0.0670 1.0000
13.750 1.2780 0.03042 0.02432 0.0253 0.0651 1.0000
14.000 1.2828 0.03199 0.02592 0.0265 0.0631 1.0000
14.250 1.2892 0.03350 0.02750 0.0275 0.0612 1.0000
14.500 1.3021 0.03453 0.02862 0.0280 0.0589 1.0000
14.750 1.3118 0.03586 0.03000 0.0286 0.0562 1.0000
15.000 1.3161 0.03771 0.03188 0.0292 0.0539 1.0000
15.250 1.3261 0.03911 0.03336 0.0296 0.0506 1.0000
15.500 1.3314 0.04099 0.03524 0.0299 0.0459 1.0000
15.750 1.3369 0.04291 0.03720 0.0302 0.0404 1.0000
16.000 1.3378 0.04534 0.03966 0.0304 0.0362 1.0000
16.250 1.3343 0.04830 0.04263 0.0305 0.0309 1.0000
16.500 1.3279 0.05170 0.04605 0.0304 0.0272 1.0000
16.750 1.3231 0.05504 0.04945 0.0301 0.0255 1.0000
17.000 1.3153 0.05879 0.05326 0.0296 0.0240 1.0000
17.250 1.3088 0.06252 0.05708 0.0289 0.0229 1.0000
17.500 1.3022 0.06636 0.06103 0.0281 0.0222 1.0000
17.750 1.2936 0.07055 0.06531 0.0271 0.0215 1.0000
18.000 1.2853 0.07480 0.06965 0.0259 0.0211 1.0000
18.250 1.2722 0.07984 0.07478 0.0243 0.0206 1.0000
18.500 1.2582 0.08511 0.08014 0.0225 0.0200 1.0000
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