GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 407 AIRFOIL (goe407-il) Reynolds number: 200,000 Max Cl/Cd: 75.19 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe407-il-200000-n5.txt Download as CSV file: xf-goe407-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 407 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3175 0.10387 0.10031 -0.0308 1.0000 0.0328
-8.750 -0.3260 0.10169 0.09819 -0.0315 1.0000 0.0330
-8.500 -0.3298 0.09898 0.09552 -0.0336 0.9989 0.0332
-8.250 -0.3170 0.09429 0.09085 -0.0387 0.9947 0.0335
-8.000 -0.2969 0.09073 0.08728 -0.0386 0.9925 0.0340
-7.750 -0.2801 0.08748 0.08403 -0.0412 0.9882 0.0350
-7.500 -0.2650 0.08393 0.08048 -0.0456 0.9828 0.0358
-7.250 -0.2510 0.08029 0.07684 -0.0500 0.9749 0.0368
-7.000 -0.2341 0.07607 0.07259 -0.0561 0.9650 0.0386
-6.750 -0.2129 0.07045 0.06682 -0.0682 0.9509 0.0398
-6.250 -0.1278 0.04995 0.04657 -0.0693 0.9039 0.0427
-6.000 -0.1098 0.04593 0.04247 -0.0731 0.8910 0.0442
-5.750 -0.1512 0.05805 0.05434 -0.0721 0.9049 0.0432
-5.500 -0.1275 0.05455 0.05072 -0.0754 0.8917 0.0451
-5.250 -0.0904 0.04912 0.04476 -0.0828 0.8780 0.0476
-5.000 -0.0627 0.04560 0.04125 -0.0854 0.8694 0.0482
-4.750 -0.0307 0.04315 0.03874 -0.0883 0.8593 0.0495
-4.500 0.0037 0.04058 0.03599 -0.0916 0.8478 0.0527
-4.250 0.0321 0.03320 0.02783 -0.0931 0.8353 0.0403
-4.000 0.0617 0.03136 0.02586 -0.0946 0.8241 0.0387
-3.750 0.0873 0.02901 0.02322 -0.0949 0.8122 0.0377
-3.500 0.1098 0.02672 0.02060 -0.0941 0.8003 0.0370
-3.250 0.1326 0.02471 0.01825 -0.0931 0.7896 0.0374
-3.000 0.1554 0.02290 0.01607 -0.0920 0.7786 0.0377
-2.750 0.1764 0.02129 0.01412 -0.0904 0.7655 0.0372
-2.500 0.1983 0.01985 0.01234 -0.0889 0.7520 0.0369
-2.250 0.2211 0.01863 0.01079 -0.0876 0.7390 0.0367
-2.000 0.2456 0.01761 0.00947 -0.0866 0.7283 0.0369
-1.750 0.2698 0.01678 0.00842 -0.0856 0.7180 0.0371
-1.500 0.2952 0.01608 0.00752 -0.0848 0.7089 0.0373
-1.250 0.3207 0.01554 0.00682 -0.0841 0.7000 0.0381
-1.000 0.3462 0.01512 0.00625 -0.0834 0.6914 0.0392
-0.750 0.3719 0.01474 0.00575 -0.0827 0.6829 0.0398
-0.500 0.3970 0.01429 0.00525 -0.0820 0.6745 0.0401
-0.250 0.4218 0.01391 0.00482 -0.0813 0.6662 0.0407
0.000 0.4460 0.01363 0.00453 -0.0804 0.6580 0.0413
0.250 0.4703 0.01341 0.00429 -0.0795 0.6500 0.0423
0.500 0.4941 0.01324 0.00411 -0.0785 0.6414 0.0433
0.750 0.5183 0.01313 0.00395 -0.0776 0.6330 0.0445
1.000 0.5420 0.01303 0.00383 -0.0766 0.6242 0.0461
1.250 0.5661 0.01298 0.00375 -0.0757 0.6159 0.0497
1.500 0.5897 0.01292 0.00372 -0.0747 0.6068 0.0545
1.750 0.6135 0.01289 0.00367 -0.0737 0.5981 0.0623
2.000 0.6363 0.01282 0.00365 -0.0725 0.5878 0.0845
2.250 0.6578 0.01254 0.00372 -0.0713 0.5781 0.2146
2.750 0.8499 0.01159 0.00424 -0.1020 0.5392 1.0000
3.000 0.8716 0.01173 0.00432 -0.1006 0.5227 1.0000
3.250 0.8921 0.01191 0.00439 -0.0990 0.5023 1.0000
3.500 0.9120 0.01213 0.00448 -0.0973 0.4792 1.0000
3.750 0.9302 0.01242 0.00461 -0.0953 0.4551 1.0000
4.000 0.9490 0.01272 0.00478 -0.0935 0.4340 1.0000
4.250 0.9683 0.01303 0.00498 -0.0917 0.4176 1.0000
4.500 0.9880 0.01333 0.00521 -0.0901 0.4044 1.0000
4.750 1.0077 0.01364 0.00546 -0.0885 0.3927 1.0000
5.000 1.0280 0.01392 0.00571 -0.0870 0.3813 1.0000
5.250 1.0477 0.01424 0.00598 -0.0854 0.3704 1.0000
5.750 1.0868 0.01486 0.00656 -0.0822 0.3497 1.0000
6.000 1.1058 0.01518 0.00686 -0.0806 0.3404 1.0000
6.250 1.1251 0.01549 0.00717 -0.0790 0.3316 1.0000
6.500 1.1443 0.01581 0.00751 -0.0773 0.3241 1.0000
6.750 1.1629 0.01614 0.00784 -0.0756 0.3153 1.0000
7.000 1.1815 0.01647 0.00819 -0.0739 0.3078 1.0000
7.250 1.1995 0.01680 0.00857 -0.0721 0.2997 1.0000
7.500 1.2169 0.01715 0.00894 -0.0702 0.2908 1.0000
7.750 1.2328 0.01754 0.00933 -0.0681 0.2813 1.0000
8.000 1.2498 0.01788 0.00972 -0.0661 0.2720 1.0000
8.250 1.2643 0.01829 0.01014 -0.0637 0.2631 1.0000
8.500 1.2782 0.01865 0.01057 -0.0612 0.2528 1.0000
8.750 1.2903 0.01905 0.01099 -0.0584 0.2414 1.0000
9.000 1.3004 0.01953 0.01146 -0.0553 0.2264 1.0000
9.250 1.3093 0.02008 0.01198 -0.0521 0.2078 1.0000
9.500 1.3163 0.02077 0.01261 -0.0487 0.1841 1.0000
9.750 1.3195 0.02171 0.01339 -0.0450 0.1533 1.0000
10.000 1.3234 0.02271 0.01428 -0.0415 0.1364 1.0000
10.250 1.3280 0.02374 0.01526 -0.0383 0.1253 1.0000
10.500 1.3330 0.02478 0.01630 -0.0353 0.1173 1.0000
10.750 1.3402 0.02575 0.01732 -0.0327 0.1110 1.0000
11.000 1.3443 0.02695 0.01855 -0.0300 0.1054 1.0000
11.250 1.3532 0.02790 0.01961 -0.0279 0.1011 1.0000
11.500 1.3605 0.02900 0.02079 -0.0258 0.0956 1.0000
11.750 1.3639 0.03043 0.02225 -0.0235 0.0906 1.0000
12.000 1.3736 0.03149 0.02341 -0.0220 0.0841 1.0000
12.250 1.3778 0.03300 0.02497 -0.0202 0.0778 1.0000
12.500 1.3841 0.03442 0.02644 -0.0187 0.0685 1.0000
12.750 1.3881 0.03608 0.02816 -0.0172 0.0610 1.0000
13.000 1.3872 0.03825 0.03029 -0.0156 0.0486 1.0000
13.250 1.3840 0.04074 0.03276 -0.0142 0.0388 1.0000
13.500 1.3806 0.04335 0.03539 -0.0131 0.0321 1.0000
13.750 1.3750 0.04630 0.03837 -0.0121 0.0274 1.0000
14.000 1.3705 0.04926 0.04139 -0.0113 0.0249 1.0000
14.250 1.3660 0.05233 0.04456 -0.0107 0.0232 1.0000
14.500 1.3594 0.05574 0.04806 -0.0104 0.0219 1.0000
14.750 1.3542 0.05911 0.05155 -0.0102 0.0208 1.0000
15.000 1.3486 0.06264 0.05521 -0.0102 0.0200 1.0000
15.250 1.3427 0.06630 0.05901 -0.0104 0.0193 1.0000
15.500 1.3347 0.07040 0.06322 -0.0109 0.0187 1.0000
15.750 1.3260 0.07474 0.06769 -0.0117 0.0183 1.0000
16.000 1.3165 0.07933 0.07242 -0.0127 0.0179 1.0000
16.250 1.3037 0.08459 0.07780 -0.0140 0.0175 1.0000
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Polar data table (+)
Polar graphs
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