GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 A AIRFOIL (goe802a-il) Reynolds number: 100,000 Max Cl/Cd: 52.59 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802a-il-100000.txt Download as CSV file: xf-goe802a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 A 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3084 0.09401 0.08933 -0.0275 1.0000 0.0633
-7.500 -0.3162 0.09241 0.08783 -0.0278 1.0000 0.0638
-7.250 -0.3253 0.09102 0.08653 -0.0284 1.0000 0.0641
-7.000 -0.3337 0.08956 0.08512 -0.0289 1.0000 0.0643
-6.750 -0.3354 0.08659 0.08222 -0.0255 1.0000 0.0647
-6.500 -0.3388 0.08433 0.08001 -0.0235 1.0000 0.0653
-6.250 -0.3415 0.08220 0.07792 -0.0225 1.0000 0.0661
-6.000 -0.3424 0.08002 0.07577 -0.0221 1.0000 0.0671
-5.750 -0.3407 0.07777 0.07351 -0.0226 1.0000 0.0684
-5.500 -0.3312 0.07572 0.07136 -0.0264 1.0000 0.0697
-5.250 -0.3284 0.07282 0.06850 -0.0254 1.0000 0.0702
-5.000 -0.3085 0.06932 0.06497 -0.0278 0.9967 0.0718
-4.750 -0.2588 0.06524 0.06063 -0.0377 0.9890 0.0745
-4.500 -0.2186 0.06077 0.05603 -0.0442 0.9822 0.0754
-4.250 -0.1818 0.05702 0.05217 -0.0493 0.9738 0.0773
-4.000 -0.1230 0.05416 0.04877 -0.0583 0.9667 0.0794
-3.750 -0.0942 0.05009 0.04475 -0.0610 0.9573 0.0803
-3.500 -0.0448 0.04686 0.04124 -0.0671 0.9509 0.0832
-3.250 -0.0057 0.04424 0.03831 -0.0707 0.9400 0.0844
-3.000 0.0429 0.04089 0.03479 -0.0761 0.9341 0.0864
-2.750 0.0859 0.03965 0.03301 -0.0789 0.9225 0.0884
-2.500 0.1346 0.03598 0.02925 -0.0840 0.9171 0.0901
-2.250 0.1724 0.03436 0.02731 -0.0859 0.9054 0.0927
-2.000 0.2179 0.03201 0.02470 -0.0891 0.8986 0.0949
-1.750 0.2513 0.03120 0.02346 -0.0896 0.8854 0.0984
-1.500 0.2868 0.02892 0.02107 -0.0909 0.8757 0.1016
-1.250 0.3205 0.02767 0.01952 -0.0912 0.8638 0.1042
-1.000 0.3497 0.02689 0.01841 -0.0906 0.8496 0.1082
-0.750 0.3787 0.02519 0.01655 -0.0903 0.8368 0.1140
-0.500 0.4088 0.02324 0.01441 -0.0901 0.8258 0.1249
-0.250 0.4349 0.02207 0.01316 -0.0892 0.8104 0.1307
0.000 0.4615 0.02118 0.01220 -0.0882 0.7954 0.1354
0.250 0.4882 0.02028 0.01130 -0.0873 0.7808 0.1416
0.500 0.5149 0.01947 0.01050 -0.0862 0.7665 0.1487
0.750 0.5416 0.01872 0.00979 -0.0850 0.7528 0.1529
1.000 0.5673 0.01828 0.00931 -0.0838 0.7370 0.1549
1.250 0.5932 0.01799 0.00894 -0.0826 0.7209 0.1556
1.500 0.6201 0.01786 0.00867 -0.0817 0.7049 0.1516
1.750 0.6470 0.01776 0.00844 -0.0808 0.6891 0.1514
2.000 0.6741 0.01767 0.00827 -0.0801 0.6738 0.1580
2.250 0.7058 0.01582 0.00828 -0.0802 0.6595 1.0000
2.500 0.7326 0.01603 0.00820 -0.0794 0.6458 1.0000
2.750 0.7584 0.01630 0.00830 -0.0787 0.6307 1.0000
3.000 0.7840 0.01662 0.00851 -0.0781 0.6157 1.0000
3.250 0.8097 0.01698 0.00875 -0.0776 0.6019 1.0000
3.500 0.8358 0.01732 0.00895 -0.0770 0.5889 1.0000
3.750 0.8620 0.01761 0.00907 -0.0764 0.5755 1.0000
4.000 0.8867 0.01792 0.00931 -0.0758 0.5599 1.0000
4.250 0.9114 0.01825 0.00957 -0.0751 0.5449 1.0000
4.500 0.9365 0.01863 0.00989 -0.0745 0.5317 1.0000
4.750 0.9628 0.01900 0.01013 -0.0741 0.5207 1.0000
5.000 0.9872 0.01941 0.01057 -0.0736 0.5080 1.0000
5.250 1.0120 0.01985 0.01100 -0.0731 0.4964 1.0000
5.500 1.0383 0.02022 0.01126 -0.0727 0.4860 1.0000
5.750 1.0618 0.02066 0.01180 -0.0720 0.4735 1.0000
6.000 1.0864 0.02108 0.01221 -0.0715 0.4620 1.0000
6.250 1.1120 0.02143 0.01246 -0.0710 0.4508 1.0000
6.500 1.1348 0.02187 0.01303 -0.0703 0.4378 1.0000
6.750 1.1587 0.02232 0.01349 -0.0696 0.4257 1.0000
7.000 1.1837 0.02268 0.01376 -0.0690 0.4136 1.0000
7.250 1.2062 0.02303 0.01414 -0.0682 0.3987 1.0000
7.500 1.2278 0.02338 0.01454 -0.0671 0.3826 1.0000
7.750 1.2489 0.02375 0.01491 -0.0660 0.3659 1.0000
8.000 1.2695 0.02417 0.01533 -0.0649 0.3489 1.0000
8.250 1.2894 0.02465 0.01579 -0.0637 0.3317 1.0000
8.500 1.3090 0.02525 0.01642 -0.0625 0.3153 1.0000
8.750 1.3281 0.02592 0.01711 -0.0613 0.2996 1.0000
9.000 1.3469 0.02662 0.01782 -0.0601 0.2849 1.0000
9.250 1.3656 0.02734 0.01852 -0.0588 0.2713 1.0000
9.500 1.3848 0.02807 0.01916 -0.0577 0.2588 1.0000
9.750 1.4003 0.02886 0.02013 -0.0561 0.2459 1.0000
10.000 1.4158 0.02974 0.02106 -0.0545 0.2338 1.0000
10.250 1.4310 0.03058 0.02188 -0.0530 0.2225 1.0000
10.500 1.4448 0.03141 0.02269 -0.0513 0.2114 1.0000
10.750 1.4559 0.03245 0.02385 -0.0494 0.2007 1.0000
11.000 1.4689 0.03352 0.02490 -0.0477 0.1914 1.0000
11.250 1.4784 0.03461 0.02609 -0.0457 0.1824 1.0000
11.500 1.4899 0.03588 0.02738 -0.0440 0.1748 1.0000
11.750 1.4972 0.03710 0.02874 -0.0417 0.1680 1.0000
12.000 1.5151 0.03845 0.02997 -0.0409 0.1616 1.0000
12.250 1.5160 0.03990 0.03175 -0.0380 0.1567 1.0000
12.500 1.5212 0.04122 0.03318 -0.0359 0.1512 1.0000
12.750 1.5298 0.04257 0.03447 -0.0344 0.1452 1.0000
13.000 1.5243 0.04437 0.03659 -0.0318 0.1405 1.0000
13.250 1.5250 0.04599 0.03835 -0.0300 0.1355 1.0000
13.500 1.5342 0.04746 0.03975 -0.0289 0.1305 1.0000
13.750 1.5263 0.04994 0.04261 -0.0272 0.1269 1.0000
14.000 1.5202 0.05238 0.04526 -0.0260 0.1221 1.0000
14.250 1.5192 0.05443 0.04730 -0.0252 0.1170 1.0000
14.500 1.5084 0.05780 0.05095 -0.0247 0.1125 1.0000
14.750 1.4974 0.06137 0.05474 -0.0248 0.1075 1.0000
15.000 1.4914 0.06437 0.05768 -0.0249 0.1019 1.0000
15.250 1.4739 0.06945 0.06311 -0.0260 0.0973 1.0000
15.500 1.4591 0.07428 0.06808 -0.0275 0.0918 1.0000
15.750 1.4446 0.07938 0.07325 -0.0291 0.0865 1.0000
16.000 1.4265 0.08552 0.07959 -0.0314 0.0812 1.0000
16.250 1.4139 0.09061 0.08457 -0.0332 0.0758 1.0000
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Polar data table (+)
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