GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 646 AIRFOIL (goe646-il) Reynolds number: 100,000 Max Cl/Cd: 43.61 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe646-il-100000.txt Download as CSV file: xf-goe646-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 646 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3477 0.13563 0.13049 -0.0337 1.0000 0.1778
-11.000 -0.3269 0.13277 0.12765 -0.0310 1.0000 0.1794
-10.750 -0.8388 0.05926 0.05351 -0.0665 1.0000 0.1130
-10.500 -0.6024 0.07934 0.07423 -0.0565 1.0000 0.1239
-10.250 -0.7055 0.06678 0.06165 -0.0602 1.0000 0.1214
-10.000 -0.8247 0.05413 0.04841 -0.0634 0.9969 0.1180
-9.750 -0.8205 0.04876 0.04248 -0.0682 0.9881 0.1213
-9.500 -0.8043 0.04452 0.03763 -0.0723 0.9803 0.1252
-9.250 -0.7720 0.04393 0.03719 -0.0737 0.9722 0.1292
-9.000 -0.7467 0.04145 0.03425 -0.0765 0.9645 0.1345
-8.750 -0.7174 0.04017 0.03296 -0.0781 0.9561 0.1395
-8.500 -0.6876 0.03910 0.03174 -0.0797 0.9481 0.1455
-8.250 -0.6575 0.03771 0.03020 -0.0815 0.9402 0.1518
-8.000 -0.6281 0.03705 0.02948 -0.0826 0.9319 0.1585
-7.750 -0.5952 0.03596 0.02827 -0.0844 0.9240 0.1659
-7.500 -0.5655 0.03543 0.02766 -0.0853 0.9154 0.1737
-7.250 -0.5328 0.03474 0.02697 -0.0867 0.9074 0.1816
-7.000 -0.4985 0.03403 0.02598 -0.0885 0.9008 0.1918
-6.750 -0.4732 0.03386 0.02605 -0.0882 0.8909 0.1988
-6.500 -0.4315 0.03310 0.02513 -0.0910 0.8860 0.2106
-6.250 -0.4132 0.03312 0.02524 -0.0894 0.8743 0.2182
-6.000 -0.3736 0.03262 0.02471 -0.0915 0.8687 0.2304
-5.750 -0.3521 0.03230 0.02415 -0.0908 0.8591 0.2422
-5.500 -0.3197 0.03235 0.02443 -0.0913 0.8519 0.2524
-5.250 -0.2774 0.03200 0.02406 -0.0936 0.8480 0.2663
-5.000 -0.2664 0.03206 0.02392 -0.0912 0.8362 0.2773
-4.750 -0.2283 0.03198 0.02400 -0.0925 0.8309 0.2886
-4.500 -0.1832 0.03153 0.02350 -0.0951 0.8280 0.3029
-4.250 -0.1794 0.03195 0.02389 -0.0914 0.8150 0.3110
-4.000 -0.1413 0.03162 0.02355 -0.0929 0.8109 0.3232
-3.750 -0.0973 0.03112 0.02290 -0.0954 0.8085 0.3380
-3.500 -0.1002 0.03183 0.02370 -0.0908 0.7954 0.3431
-3.250 -0.0614 0.03143 0.02312 -0.0923 0.7916 0.3576
-3.000 -0.0157 0.03096 0.02278 -0.0946 0.7894 0.3708
-2.750 -0.0245 0.03188 0.02354 -0.0896 0.7763 0.3780
-2.500 0.0115 0.03158 0.02337 -0.0905 0.7727 0.3893
-2.250 0.0548 0.03091 0.02261 -0.0927 0.7706 0.4026
-2.000 0.0449 0.03208 0.02382 -0.0875 0.7581 0.4075
-1.750 0.0798 0.03171 0.02327 -0.0885 0.7541 0.4201
-1.500 0.1215 0.03107 0.02275 -0.0902 0.7519 0.4310
-1.250 0.1118 0.03248 0.02411 -0.0854 0.7407 0.4370
-1.000 0.1413 0.03225 0.02388 -0.0855 0.7358 0.4469
-0.750 0.1837 0.03160 0.02317 -0.0873 0.7333 0.4601
-0.500 0.2332 0.03063 0.02226 -0.0899 0.7317 0.4726
-0.250 0.2124 0.03247 0.02409 -0.0835 0.7174 0.4774
0.000 0.2639 0.03116 0.02280 -0.0860 0.7149 0.4915
0.250 0.3244 0.02968 0.02128 -0.0899 0.7132 0.5082
0.500 0.3876 0.02841 0.02001 -0.0947 0.7116 0.5258
0.750 0.3492 0.03057 0.02222 -0.0852 0.6967 0.5288
1.000 0.4033 0.02945 0.02114 -0.0884 0.6948 0.5463
1.250 0.4631 0.02834 0.02009 -0.0926 0.6931 0.5652
1.500 0.4241 0.03067 0.02245 -0.0832 0.6785 0.5702
1.750 0.4797 0.02946 0.02130 -0.0864 0.6764 0.5917
2.000 0.5430 0.02818 0.02011 -0.0910 0.6745 0.6162
2.250 0.5036 0.03049 0.02251 -0.0814 0.6604 0.6236
2.500 0.5588 0.02922 0.02130 -0.0845 0.6579 0.6547
2.750 0.6230 0.02780 0.01997 -0.0891 0.6557 0.6941
3.000 0.5915 0.02967 0.02197 -0.0804 0.6424 0.7134
3.250 0.6518 0.02807 0.02059 -0.0841 0.6393 0.7704
3.500 0.7337 0.02621 0.01908 -0.0914 0.6365 0.8822
3.750 0.7789 0.02667 0.01955 -0.0959 0.6262 1.0000
4.000 0.8268 0.02616 0.01886 -0.0989 0.6195 1.0000
4.250 0.8964 0.02520 0.01767 -0.1052 0.6148 1.0000
4.500 0.8801 0.02646 0.01898 -0.0983 0.6023 1.0000
4.750 0.9445 0.02558 0.01790 -0.1036 0.5962 1.0000
5.000 0.9386 0.02654 0.01890 -0.0982 0.5842 1.0000
5.250 0.9982 0.02577 0.01795 -0.1027 0.5768 1.0000
5.500 0.9963 0.02655 0.01877 -0.0978 0.5646 1.0000
5.750 1.0582 0.02574 0.01773 -0.1027 0.5563 1.0000
6.000 1.0516 0.02653 0.01860 -0.0969 0.5436 1.0000
6.250 1.0953 0.02621 0.01814 -0.0990 0.5344 1.0000
6.500 1.1019 0.02670 0.01865 -0.0954 0.5228 1.0000
6.750 1.1304 0.02680 0.01869 -0.0952 0.5131 1.0000
7.000 1.1475 0.02707 0.01893 -0.0932 0.5025 1.0000
7.250 1.1667 0.02741 0.01924 -0.0916 0.4926 1.0000
7.500 1.1899 0.02755 0.01933 -0.0906 0.4827 1.0000
7.750 1.2017 0.02804 0.01983 -0.0879 0.4729 1.0000
8.000 1.2272 0.02814 0.01985 -0.0873 0.4635 1.0000
8.250 1.2343 0.02874 0.02048 -0.0839 0.4544 1.0000
8.500 1.2563 0.02897 0.02066 -0.0828 0.4455 1.0000
8.750 1.2681 0.02956 0.02126 -0.0803 0.4371 1.0000
9.000 1.2824 0.02999 0.02169 -0.0781 0.4283 1.0000
9.250 1.3027 0.03042 0.02208 -0.0769 0.4201 1.0000
9.500 1.3087 0.03108 0.02278 -0.0736 0.4114 1.0000
9.750 1.3341 0.03132 0.02294 -0.0732 0.4028 1.0000
10.000 1.3358 0.03214 0.02381 -0.0695 0.3941 1.0000
10.250 1.3640 0.03233 0.02390 -0.0694 0.3854 1.0000
10.500 1.3620 0.03335 0.02500 -0.0655 0.3771 1.0000
10.750 1.3930 0.03349 0.02499 -0.0658 0.3681 1.0000
11.000 1.3867 0.03474 0.02637 -0.0615 0.3602 1.0000
11.250 1.4252 0.03477 0.02621 -0.0628 0.3513 1.0000
11.500 1.4108 0.03640 0.02803 -0.0579 0.3444 1.0000
11.750 1.4561 0.03628 0.02768 -0.0599 0.3354 1.0000
12.000 1.4379 0.03816 0.02977 -0.0548 0.3292 1.0000
12.250 1.4508 0.03894 0.03055 -0.0532 0.3214 1.0000
12.500 1.4675 0.03981 0.03138 -0.0522 0.3140 1.0000
12.750 1.4557 0.04167 0.03341 -0.0484 0.3077 1.0000
13.000 1.5085 0.04124 0.03271 -0.0509 0.2992 1.0000
13.250 1.4773 0.04391 0.03569 -0.0455 0.2946 1.0000
13.500 1.4718 0.04572 0.03763 -0.0428 0.2884 1.0000
13.750 1.5130 0.04546 0.03717 -0.0438 0.2807 1.0000
14.000 1.4799 0.04874 0.04076 -0.0394 0.2762 1.0000
14.250 1.4768 0.05058 0.04268 -0.0373 0.2699 1.0000
14.500 1.5044 0.05070 0.04270 -0.0371 0.2627 1.0000
14.750 1.4682 0.05483 0.04713 -0.0337 0.2579 1.0000
15.000 1.4829 0.05545 0.04770 -0.0328 0.2506 1.0000
15.250 1.4772 0.05781 0.05014 -0.0313 0.2444 1.0000
15.500 1.4434 0.06258 0.05516 -0.0294 0.2389 1.0000
15.750 1.4820 0.06110 0.05345 -0.0291 0.2299 1.0000
16.000 1.4304 0.06797 0.06068 -0.0277 0.2248 1.0000
16.250 1.4751 0.06557 0.05799 -0.0271 0.2148 1.0000
16.500 1.4158 0.07395 0.06677 -0.0267 0.2097 1.0000
16.750 1.4580 0.07155 0.06406 -0.0257 0.1994 1.0000
17.000 1.3975 0.08093 0.07384 -0.0265 0.1942 1.0000
17.250 1.4466 0.07764 0.07020 -0.0251 0.1846 1.0000
17.500 1.3839 0.08800 0.08098 -0.0268 0.1802 1.0000
17.750 1.4033 0.08825 0.08112 -0.0262 0.1733 1.0000
18.000 1.3926 0.09264 0.08559 -0.0268 0.1684 1.0000
18.750 1.3580 0.10667 0.09990 -0.0300 0.1558 1.0000
19.000 0.8743 0.21559 0.20930 -0.0892 0.1924 1.0000
19.250 0.8859 0.21804 0.21177 -0.0900 0.1890 1.0000
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