GOE 703 AIRFOIL (goe703-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 703 AIRFOIL (goe703-il) Reynolds number: 200,000 Max Cl/Cd: 63.26 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe703-il-200000.txt Download as CSV file: xf-goe703-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 703 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7698 0.07321 0.06794 -0.0867 1.0000 0.0593
-15.250 -0.8000 0.06785 0.06240 -0.0874 1.0000 0.0591
-15.000 -0.8229 0.06358 0.05799 -0.0869 1.0000 0.0590
-14.750 -0.8469 0.05980 0.05403 -0.0856 1.0000 0.0588
-14.500 -0.8706 0.05646 0.05051 -0.0834 1.0000 0.0588
-14.250 -0.8911 0.05357 0.04743 -0.0805 1.0000 0.0587
-14.000 -0.9101 0.05109 0.04477 -0.0769 1.0000 0.0587
-13.750 -0.9269 0.04889 0.04239 -0.0730 1.0000 0.0587
-13.500 -0.9401 0.04698 0.04031 -0.0688 1.0000 0.0587
-13.250 -0.9555 0.04536 0.03852 -0.0639 1.0000 0.0588
-13.000 -0.9711 0.04398 0.03698 -0.0584 1.0000 0.0589
-12.750 -0.9884 0.04296 0.03582 -0.0523 1.0000 0.0590
-12.500 -1.0079 0.04221 0.03496 -0.0455 1.0000 0.0591
-12.250 -1.0294 0.04169 0.03434 -0.0382 1.0000 0.0591
-12.000 -1.0392 0.04087 0.03334 -0.0330 0.9985 0.0593
-11.750 -1.0000 0.03835 0.03076 -0.0365 0.9957 0.0601
-11.500 -0.9623 0.03680 0.02920 -0.0396 0.9924 0.0611
-11.250 -0.9306 0.03537 0.02769 -0.0414 0.9875 0.0621
-11.000 -0.8966 0.03400 0.02620 -0.0436 0.9829 0.0633
-10.750 -0.8591 0.03254 0.02457 -0.0463 0.9796 0.0643
-10.500 -0.8300 0.03130 0.02313 -0.0473 0.9725 0.0653
-10.250 -0.7857 0.02976 0.02157 -0.0509 0.9694 0.0665
-10.000 -0.7409 0.02852 0.02042 -0.0547 0.9669 0.0682
-9.750 -0.7074 0.02751 0.01939 -0.0562 0.9598 0.0702
-9.500 -0.6694 0.02652 0.01829 -0.0586 0.9549 0.0723
-9.250 -0.6261 0.02525 0.01714 -0.0621 0.9520 0.0750
-9.000 -0.5940 0.02437 0.01628 -0.0634 0.9446 0.0777
-8.750 -0.5562 0.02330 0.01520 -0.0657 0.9394 0.0812
-8.500 -0.5150 0.02224 0.01421 -0.0690 0.9356 0.0859
-8.250 -0.4811 0.02127 0.01329 -0.0707 0.9274 0.0917
-8.000 -0.4414 0.02027 0.01236 -0.0737 0.9208 0.1009
-7.750 -0.4014 0.01931 0.01149 -0.0768 0.9137 0.1160
-7.500 -0.3683 0.01845 0.01077 -0.0785 0.9025 0.1386
-7.250 -0.3353 0.01780 0.01020 -0.0801 0.8907 0.1637
-7.000 -0.3001 0.01734 0.00971 -0.0820 0.8790 0.1856
-6.750 -0.2792 0.01706 0.00942 -0.0808 0.8633 0.2004
-6.500 -0.2560 0.01678 0.00914 -0.0801 0.8498 0.2143
-6.250 -0.2306 0.01653 0.00881 -0.0798 0.8375 0.2284
-6.000 -0.2151 0.01639 0.00863 -0.0774 0.8229 0.2410
-5.750 -0.1949 0.01614 0.00839 -0.0760 0.8111 0.2543
-5.500 -0.1773 0.01592 0.00817 -0.0740 0.7990 0.2682
-5.250 -0.1587 0.01575 0.00796 -0.0722 0.7883 0.2835
-5.000 -0.1413 0.01549 0.00772 -0.0702 0.7776 0.3004
-4.750 -0.1251 0.01521 0.00751 -0.0680 0.7676 0.3199
-4.500 -0.1107 0.01490 0.00727 -0.0654 0.7579 0.3444
-4.250 -0.0981 0.01449 0.00703 -0.0625 0.7498 0.3750
-4.000 -0.0932 0.01407 0.00685 -0.0580 0.7404 0.4158
-3.750 -0.0915 0.01351 0.00660 -0.0528 0.7333 0.4838
-3.500 -0.0929 0.01303 0.00661 -0.0467 0.7249 0.5785
-3.250 -0.0258 0.01325 0.00736 -0.0535 0.7175 0.7114
-3.000 0.0269 0.01395 0.00801 -0.0572 0.7112 0.7539
-2.750 0.0593 0.01454 0.00860 -0.0572 0.7028 0.7752
-2.500 0.0855 0.01498 0.00895 -0.0560 0.6958 0.7924
-2.250 0.1080 0.01541 0.00927 -0.0542 0.6895 0.8077
-2.000 0.1549 0.01630 0.01009 -0.0569 0.6815 0.8127
-1.750 0.1980 0.01698 0.01065 -0.0589 0.6749 0.8193
-1.500 0.2248 0.01738 0.01096 -0.0582 0.6686 0.8298
-1.250 0.2699 0.01800 0.01153 -0.0608 0.6610 0.8343
-1.000 0.2878 0.01821 0.01165 -0.0586 0.6549 0.8465
-0.750 0.3401 0.01881 0.01214 -0.0627 0.6483 0.8497
-0.500 0.3819 0.01925 0.01256 -0.0649 0.6411 0.8554
-0.250 0.4060 0.01951 0.01274 -0.0639 0.6352 0.8659
0.000 0.4602 0.01998 0.01310 -0.0685 0.6289 0.8702
0.250 0.4766 0.02028 0.01342 -0.0661 0.6226 0.8827
0.500 0.5297 0.02047 0.01354 -0.0707 0.6158 0.8862
0.750 0.5763 0.02073 0.01367 -0.0741 0.6101 0.8924
1.000 0.6014 0.02091 0.01391 -0.0735 0.6033 0.9026
1.250 0.6478 0.02094 0.01391 -0.0770 0.5964 0.9086
1.500 0.6689 0.02118 0.01406 -0.0758 0.5913 0.9184
1.750 0.7081 0.02103 0.01393 -0.0782 0.5845 0.9218
2.000 0.7395 0.02096 0.01386 -0.0791 0.5779 0.9269
2.250 0.7578 0.02116 0.01399 -0.0774 0.5724 0.9351
2.500 0.7973 0.02095 0.01378 -0.0799 0.5661 0.9384
2.750 0.8277 0.02084 0.01370 -0.0807 0.5587 0.9438
3.000 0.8477 0.02101 0.01382 -0.0793 0.5529 0.9512
3.250 0.8857 0.02070 0.01350 -0.0816 0.5454 0.9549
3.500 0.9146 0.02056 0.01337 -0.0821 0.5375 0.9603
3.750 0.9404 0.02060 0.01333 -0.0819 0.5310 0.9667
4.000 0.9741 0.02025 0.01304 -0.0834 0.5223 0.9713
4.250 1.0020 0.02013 0.01289 -0.0837 0.5145 0.9769
4.500 1.0353 0.01989 0.01264 -0.0851 0.5068 0.9826
4.750 1.0671 0.01955 0.01232 -0.0862 0.4974 0.9881
5.000 1.1077 0.01914 0.01185 -0.0891 0.4891 0.9953
5.250 1.1404 0.01878 0.01156 -0.0906 0.4801 1.0000
5.500 1.1584 0.01885 0.01156 -0.0890 0.4739 1.0000
5.750 1.1723 0.01899 0.01178 -0.0866 0.4666 1.0000
6.000 1.1870 0.01909 0.01190 -0.0844 0.4595 1.0000
6.250 1.2051 0.01922 0.01195 -0.0828 0.4533 1.0000
6.500 1.2163 0.01939 0.01224 -0.0800 0.4455 1.0000
6.750 1.2309 0.01951 0.01234 -0.0777 0.4386 1.0000
7.000 1.2443 0.01970 0.01255 -0.0752 0.4313 1.0000
7.250 1.2547 0.01985 0.01274 -0.0722 0.4230 1.0000
7.500 1.2678 0.02004 0.01287 -0.0697 0.4155 1.0000
7.750 1.2750 0.02024 0.01316 -0.0660 0.4066 1.0000
8.000 1.2865 0.02045 0.01327 -0.0632 0.3989 1.0000
8.250 1.2903 0.02069 0.01363 -0.0590 0.3900 1.0000
8.500 1.2979 0.02094 0.01382 -0.0555 0.3822 1.0000
8.750 1.3004 0.02123 0.01419 -0.0511 0.3743 1.0000
9.000 1.3020 0.02151 0.01446 -0.0465 0.3664 1.0000
9.250 1.2974 0.02180 0.01477 -0.0408 0.3591 1.0000
9.500 1.2904 0.02209 0.01509 -0.0347 0.3516 1.0000
9.750 1.2852 0.02246 0.01542 -0.0291 0.3439 1.0000
10.000 1.2776 0.02287 0.01591 -0.0233 0.3357 1.0000
10.250 1.2739 0.02337 0.01633 -0.0183 0.3281 1.0000
10.500 1.2660 0.02394 0.01700 -0.0128 0.3193 1.0000
11.000 1.2527 0.02535 0.01843 -0.0029 0.3017 1.0000
11.250 1.2457 0.02621 0.01922 0.0018 0.2931 1.0000
11.500 1.2377 0.02716 0.02023 0.0064 0.2831 1.0000
11.750 1.2302 0.02823 0.02127 0.0107 0.2739 1.0000
12.000 1.2223 0.02940 0.02244 0.0148 0.2642 1.0000
12.250 1.2150 0.03066 0.02370 0.0186 0.2547 1.0000
12.500 1.2073 0.03204 0.02502 0.0222 0.2458 1.0000
12.750 1.2017 0.03343 0.02644 0.0254 0.2369 1.0000
13.000 1.1960 0.03490 0.02783 0.0285 0.2296 1.0000
13.250 1.1937 0.03630 0.02928 0.0311 0.2225 1.0000
13.500 1.1905 0.03780 0.03075 0.0336 0.2162 1.0000
13.750 1.1894 0.03925 0.03218 0.0359 0.2105 1.0000
14.000 1.1883 0.04079 0.03376 0.0379 0.2046 1.0000
14.250 1.1877 0.04229 0.03519 0.0399 0.1994 1.0000
14.500 1.1886 0.04381 0.03676 0.0416 0.1945 1.0000
14.750 1.1891 0.04543 0.03842 0.0432 0.1898 1.0000
15.000 1.1911 0.04690 0.03984 0.0447 0.1853 1.0000
15.250 1.1937 0.04842 0.04139 0.0461 0.1811 1.0000
15.500 1.1941 0.05021 0.04326 0.0473 0.1769 1.0000
15.750 1.1955 0.05192 0.04496 0.0485 0.1726 1.0000
16.000 1.2010 0.05325 0.04624 0.0497 0.1685 1.0000
16.250 1.1984 0.05550 0.04863 0.0506 0.1643 1.0000
16.500 1.1979 0.05756 0.05072 0.0514 0.1599 1.0000
16.750 1.2018 0.05911 0.05219 0.0523 0.1551 1.0000
17.000 1.1967 0.06181 0.05504 0.0529 0.1507 1.0000
17.250 1.1938 0.06426 0.05750 0.0534 0.1457 1.0000
17.500 1.1934 0.06646 0.05970 0.0539 0.1409 1.0000
17.750 1.1864 0.06956 0.06291 0.0541 0.1355 1.0000
18.000 1.1866 0.07172 0.06497 0.0545 0.1301 1.0000
18.250 1.1768 0.07535 0.06875 0.0544 0.1248 1.0000
18.500 1.1772 0.07756 0.07084 0.0546 0.1196 1.0000
18.750 1.1675 0.08132 0.07476 0.0543 0.1146 1.0000
19.000 1.1653 0.08406 0.07748 0.0541 0.1104 1.0000
19.250 1.1632 0.08682 0.08027 0.0540 0.1064 1.0000
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