GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 500,000 Max Cl/Cd: 103.03 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe517-il-500000.txt Download as CSV file: xf-goe517-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3657 0.08617 0.08407 -0.0280 1.0000 0.0179
-7.500 -0.3665 0.08330 0.08122 -0.0288 1.0000 0.0179
-7.250 -0.3760 0.07883 0.07681 -0.0291 1.0000 0.0182
-7.000 -0.3815 0.07656 0.07458 -0.0272 1.0000 0.0184
-6.750 -0.3590 0.07281 0.07081 -0.0312 0.9972 0.0188
-6.500 -0.3319 0.06877 0.06674 -0.0369 0.9931 0.0194
-6.250 -0.3027 0.06427 0.06219 -0.0438 0.9876 0.0200
-6.000 -0.2684 0.05916 0.05701 -0.0520 0.9835 0.0219
-5.750 -0.2261 0.05330 0.05098 -0.0616 0.9753 0.0239
-5.500 -0.1883 0.04756 0.04508 -0.0684 0.9713 0.0241
-5.250 -0.1678 0.04124 0.03863 -0.0727 0.9628 0.0254
-5.000 -0.1368 0.03874 0.03603 -0.0756 0.9575 0.0265
-4.500 -0.0827 0.02317 0.01942 -0.0798 0.9354 0.0255
-4.250 -0.0627 0.01606 0.01135 -0.0785 0.9249 0.0214
-4.000 -0.0368 0.01410 0.00895 -0.0779 0.9152 0.0221
-3.750 -0.0106 0.01291 0.00748 -0.0773 0.9054 0.0230
-3.500 0.0163 0.01200 0.00631 -0.0768 0.8965 0.0246
-3.250 0.0417 0.01091 0.00506 -0.0762 0.8866 0.0266
-3.000 0.0677 0.01041 0.00446 -0.0756 0.8758 0.0285
-2.750 0.0937 0.00998 0.00391 -0.0749 0.8645 0.0307
-2.500 0.1191 0.00946 0.00327 -0.0741 0.8535 0.0341
-2.250 0.1449 0.00917 0.00294 -0.0734 0.8425 0.0387
-2.000 0.1704 0.00887 0.00256 -0.0727 0.8313 0.0441
-1.750 0.1965 0.00873 0.00239 -0.0721 0.8198 0.0537
-1.500 0.2222 0.00852 0.00220 -0.0714 0.8087 0.0713
-1.250 0.2484 0.00847 0.00210 -0.0709 0.7966 0.0845
-1.000 0.2747 0.00847 0.00205 -0.0704 0.7833 0.0942
-0.750 0.3004 0.00834 0.00191 -0.0698 0.7699 0.1047
-0.500 0.3263 0.00825 0.00180 -0.0692 0.7562 0.1150
-0.250 0.3522 0.00818 0.00170 -0.0687 0.7410 0.1273
0.000 0.3778 0.00810 0.00161 -0.0681 0.7243 0.1410
0.250 0.4032 0.00801 0.00153 -0.0674 0.7047 0.1615
0.500 0.4277 0.00787 0.00148 -0.0667 0.6827 0.2133
0.750 0.5120 0.00610 0.00155 -0.0795 0.6536 1.0000
1.000 0.5355 0.00623 0.00154 -0.0785 0.6297 1.0000
1.250 0.5588 0.00639 0.00154 -0.0775 0.6079 1.0000
1.500 0.5826 0.00654 0.00157 -0.0765 0.5899 1.0000
1.750 0.6065 0.00669 0.00162 -0.0757 0.5748 1.0000
2.000 0.6306 0.00684 0.00168 -0.0748 0.5614 1.0000
2.250 0.6547 0.00700 0.00176 -0.0740 0.5487 1.0000
2.500 0.6788 0.00716 0.00185 -0.0732 0.5366 1.0000
2.750 0.7032 0.00730 0.00194 -0.0724 0.5250 1.0000
3.000 0.7277 0.00743 0.00204 -0.0717 0.5134 1.0000
3.250 0.7520 0.00758 0.00216 -0.0709 0.5009 1.0000
3.500 0.7763 0.00772 0.00228 -0.0701 0.4872 1.0000
3.750 0.8006 0.00787 0.00239 -0.0694 0.4723 1.0000
4.000 0.8243 0.00804 0.00251 -0.0685 0.4518 1.0000
4.250 0.8479 0.00823 0.00264 -0.0676 0.4258 1.0000
4.500 0.8706 0.00848 0.00279 -0.0667 0.3966 1.0000
4.750 0.8929 0.00880 0.00298 -0.0656 0.3699 1.0000
5.000 0.9151 0.00913 0.00322 -0.0646 0.3497 1.0000
5.250 0.9376 0.00945 0.00348 -0.0636 0.3297 1.0000
5.500 0.9597 0.00980 0.00374 -0.0626 0.3096 1.0000
5.750 0.9827 0.01009 0.00399 -0.0617 0.2947 1.0000
6.000 1.0057 0.01038 0.00425 -0.0608 0.2794 1.0000
6.250 1.0287 0.01067 0.00452 -0.0600 0.2630 1.0000
6.500 1.0519 0.01094 0.00478 -0.0592 0.2452 1.0000
6.750 1.0739 0.01132 0.00507 -0.0582 0.2216 1.0000
7.000 1.0950 0.01179 0.00542 -0.0572 0.1869 1.0000
7.250 1.1059 0.01321 0.00626 -0.0547 0.0916 1.0000
7.500 1.1183 0.01454 0.00728 -0.0523 0.0418 1.0000
7.750 1.1362 0.01534 0.00804 -0.0507 0.0298 1.0000
8.000 1.1543 0.01608 0.00881 -0.0491 0.0253 1.0000
8.250 1.1704 0.01698 0.00980 -0.0472 0.0225 1.0000
8.500 1.1887 0.01762 0.01053 -0.0457 0.0207 1.0000
8.750 1.2055 0.01836 0.01134 -0.0440 0.0190 1.0000
9.000 1.2173 0.01945 0.01250 -0.0416 0.0176 1.0000
9.250 1.2226 0.02096 0.01414 -0.0382 0.0165 1.0000
9.500 1.2358 0.02179 0.01508 -0.0360 0.0160 1.0000
9.750 1.2451 0.02272 0.01610 -0.0331 0.0154 1.0000
10.000 1.2527 0.02374 0.01721 -0.0301 0.0148 1.0000
10.250 1.2605 0.02479 0.01834 -0.0274 0.0142 1.0000
10.500 1.2686 0.02585 0.01949 -0.0249 0.0135 1.0000
10.750 1.2746 0.02712 0.02081 -0.0225 0.0129 1.0000
11.000 1.2779 0.02881 0.02257 -0.0199 0.0124 1.0000
11.250 1.2767 0.03176 0.02566 -0.0171 0.0119 1.0000
11.500 1.2837 0.03344 0.02748 -0.0152 0.0117 1.0000
11.750 1.2903 0.03513 0.02931 -0.0135 0.0115 1.0000
12.000 1.2958 0.03689 0.03123 -0.0118 0.0112 1.0000
12.250 1.3000 0.03892 0.03342 -0.0103 0.0110 1.0000
12.500 1.3020 0.04152 0.03620 -0.0088 0.0110 1.0000
12.750 1.3021 0.04400 0.03886 -0.0075 0.0107 1.0000
13.000 1.3001 0.04683 0.04188 -0.0064 0.0105 1.0000
13.250 1.2955 0.05006 0.04533 -0.0056 0.0104 1.0000
13.500 1.2881 0.05374 0.04922 -0.0052 0.0103 1.0000
13.750 1.2791 0.05768 0.05335 -0.0052 0.0102 1.0000
14.000 1.2662 0.06241 0.05830 -0.0058 0.0103 1.0000
14.250 1.2551 0.06692 0.06298 -0.0070 0.0101 1.0000
14.500 1.2394 0.07252 0.06879 -0.0088 0.0102 1.0000
14.750 1.2272 0.07771 0.07413 -0.0111 0.0100 1.0000
15.000 1.2242 0.08148 0.07796 -0.0131 0.0096 1.0000
15.250 1.1891 0.09175 0.08855 -0.0179 0.0100 1.0000
15.500 1.1713 0.09916 0.09613 -0.0221 0.0100 1.0000
15.750 1.1607 0.10545 0.10252 -0.0259 0.0098 1.0000
16.000 1.1225 0.11856 0.11587 -0.0335 0.0105 1.0000
16.250 1.0993 0.12891 0.12636 -0.0399 0.0108 1.0000
16.500 1.0786 0.13938 0.13696 -0.0464 0.0108 1.0000
16.750 1.0507 0.15234 0.15002 -0.0542 0.0113 1.0000
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Polar data table (+)
Polar graphs
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