GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 100,000 Max Cl/Cd: 55.1 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe517-il-100000.txt Download as CSV file: xf-goe517-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3633 0.10445 0.09954 -0.0269 1.0000 0.0658
-8.250 -0.3717 0.10345 0.09867 -0.0288 1.0000 0.0662
-8.000 -0.3795 0.10245 0.09776 -0.0325 1.0000 0.0665
-7.750 -0.3501 0.09348 0.08873 -0.0257 1.0000 0.0700
-7.500 -0.3485 0.09089 0.08620 -0.0251 1.0000 0.0721
-7.250 -0.3513 0.08863 0.08403 -0.0246 1.0000 0.0739
-7.000 -0.3523 0.08628 0.08175 -0.0253 1.0000 0.0759
-6.750 -0.3542 0.08426 0.07980 -0.0275 1.0000 0.0782
-6.500 -0.3563 0.08369 0.07924 -0.0335 1.0000 0.0798
-6.250 -0.3551 0.08228 0.07777 -0.0364 1.0000 0.0802
-6.000 -0.3557 0.07636 0.07203 -0.0305 1.0000 0.0815
-5.750 -0.3551 0.07348 0.06921 -0.0272 1.0000 0.0829
-5.500 -0.3543 0.07110 0.06686 -0.0252 1.0000 0.0849
-5.250 -0.3519 0.06873 0.06450 -0.0245 1.0000 0.0878
-5.000 -0.3436 0.06652 0.06221 -0.0263 1.0000 0.0922
-4.750 -0.3293 0.06378 0.05924 -0.0305 1.0000 0.0952
-4.500 -0.3264 0.06034 0.05589 -0.0277 1.0000 0.0967
-4.250 -0.3192 0.05774 0.05330 -0.0262 1.0000 0.0996
-4.000 -0.2941 0.05582 0.05098 -0.0305 1.0000 0.1095
-3.750 -0.2899 0.05229 0.04762 -0.0279 1.0000 0.1121
-3.500 -0.2660 0.05089 0.04583 -0.0302 1.0000 0.1239
-3.250 -0.2419 0.04650 0.04159 -0.0316 0.9956 0.1282
-3.000 -0.1994 0.04313 0.03793 -0.0367 0.9884 0.1415
-2.750 -0.1582 0.04008 0.03467 -0.0410 0.9814 0.1568
-2.500 -0.1195 0.03749 0.03189 -0.0446 0.9731 0.1848
-2.250 -0.0568 0.03061 0.02357 -0.0488 0.9687 0.0964
-2.000 -0.0168 0.02755 0.02002 -0.0507 0.9607 0.0891
-1.750 0.0273 0.02565 0.01737 -0.0529 0.9533 0.0941
-1.500 0.0679 0.02361 0.01514 -0.0554 0.9449 0.1002
-1.250 0.1079 0.02241 0.01369 -0.0575 0.9354 0.1148
-1.000 0.1558 0.02131 0.01231 -0.0608 0.9283 0.1378
-0.750 0.1938 0.02031 0.01138 -0.0627 0.9171 0.1640
-0.500 0.2376 0.01944 0.01053 -0.0654 0.9065 0.1957
-0.250 0.2934 0.01815 0.00948 -0.0701 0.8992 0.2346
0.000 0.3834 0.01491 0.00825 -0.0816 0.8943 1.0000
0.250 0.4273 0.01464 0.00764 -0.0838 0.8821 1.0000
0.500 0.4655 0.01444 0.00724 -0.0850 0.8690 1.0000
0.750 0.4972 0.01434 0.00700 -0.0850 0.8538 1.0000
1.000 0.5257 0.01430 0.00684 -0.0845 0.8378 1.0000
1.250 0.5526 0.01430 0.00675 -0.0836 0.8213 1.0000
1.500 0.5785 0.01433 0.00668 -0.0825 0.8049 1.0000
1.750 0.6039 0.01438 0.00664 -0.0814 0.7885 1.0000
2.000 0.6289 0.01444 0.00662 -0.0802 0.7721 1.0000
2.250 0.6537 0.01450 0.00663 -0.0790 0.7559 1.0000
2.500 0.6785 0.01456 0.00661 -0.0778 0.7396 1.0000
2.750 0.7019 0.01467 0.00667 -0.0764 0.7219 1.0000
3.000 0.7254 0.01477 0.00674 -0.0751 0.7036 1.0000
3.250 0.7496 0.01486 0.00677 -0.0738 0.6854 1.0000
3.500 0.7745 0.01494 0.00680 -0.0726 0.6672 1.0000
3.750 0.7973 0.01512 0.00696 -0.0713 0.6458 1.0000
4.000 0.8217 0.01529 0.00704 -0.0701 0.6252 1.0000
4.500 0.8691 0.01589 0.00751 -0.0677 0.5809 1.0000
4.750 0.8916 0.01633 0.00792 -0.0664 0.5575 1.0000
5.000 0.9160 0.01683 0.00830 -0.0655 0.5374 1.0000
5.250 0.9383 0.01737 0.00888 -0.0643 0.5163 1.0000
5.500 0.9616 0.01792 0.00946 -0.0633 0.4981 1.0000
5.750 0.9851 0.01847 0.01003 -0.0624 0.4817 1.0000
6.000 1.0084 0.01896 0.01055 -0.0614 0.4657 1.0000
6.250 1.0309 0.01935 0.01098 -0.0603 0.4489 1.0000
6.500 1.0517 0.01967 0.01146 -0.0589 0.4305 1.0000
6.750 1.0721 0.01983 0.01166 -0.0573 0.4100 1.0000
7.000 1.0898 0.01988 0.01174 -0.0552 0.3842 1.0000
7.250 1.1065 0.02008 0.01193 -0.0531 0.3568 1.0000
7.500 1.1235 0.02046 0.01238 -0.0512 0.3311 1.0000
7.750 1.1383 0.02088 0.01288 -0.0489 0.2996 1.0000
8.000 1.1456 0.02144 0.01340 -0.0455 0.2279 1.0000
8.250 1.1365 0.02441 0.01521 -0.0406 0.1055 1.0000
8.500 1.1381 0.02668 0.01730 -0.0368 0.0858 1.0000
8.750 1.1412 0.02873 0.01927 -0.0335 0.0754 1.0000
9.000 1.1502 0.03037 0.02098 -0.0309 0.0677 1.0000
9.250 1.1626 0.03273 0.02323 -0.0288 0.0628 1.0000
9.500 1.1832 0.03467 0.02534 -0.0275 0.0586 1.0000
9.750 1.2057 0.03721 0.02778 -0.0272 0.0533 1.0000
10.000 1.2325 0.04044 0.03121 -0.0271 0.0508 1.0000
10.250 1.2520 0.04325 0.03437 -0.0258 0.0496 1.0000
10.500 1.2662 0.04631 0.03782 -0.0241 0.0488 1.0000
10.750 1.2732 0.04923 0.04113 -0.0218 0.0477 1.0000
11.000 1.2761 0.05206 0.04430 -0.0193 0.0465 1.0000
11.250 1.2749 0.05507 0.04767 -0.0166 0.0457 1.0000
11.500 1.2674 0.05809 0.05101 -0.0134 0.0455 1.0000
11.750 1.2536 0.06141 0.05465 -0.0102 0.0459 1.0000
12.000 1.2371 0.06499 0.05853 -0.0077 0.0463 1.0000
12.250 1.2182 0.06897 0.06279 -0.0061 0.0469 1.0000
12.500 1.1977 0.07332 0.06740 -0.0055 0.0473 1.0000
12.750 1.1754 0.07828 0.07258 -0.0061 0.0478 1.0000
13.000 1.1521 0.08382 0.07833 -0.0077 0.0483 1.0000
13.250 1.1277 0.09010 0.08476 -0.0106 0.0487 1.0000
13.500 1.1024 0.09728 0.09209 -0.0145 0.0493 1.0000
13.750 1.0779 0.10517 0.10011 -0.0193 0.0499 1.0000
14.000 1.0560 0.11358 0.10860 -0.0242 0.0508 1.0000
14.250 1.0386 0.12205 0.11710 -0.0287 0.0516 1.0000
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Polar data table (+)
Polar graphs
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