GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 500,000 Max Cl/Cd: 94.71 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe408-il-500000-n5.txt Download as CSV file: xf-goe408-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4100 0.09435 0.09217 -0.0182 1.0000 0.0073
-8.250 -0.4128 0.09137 0.08922 -0.0184 1.0000 0.0075
-8.000 -0.4204 0.08827 0.08616 -0.0182 1.0000 0.0074
-7.750 -0.4134 0.08412 0.08202 -0.0227 0.9974 0.0077
-7.500 -0.4001 0.07817 0.07607 -0.0298 0.9940 0.0085
-7.250 -0.3856 0.07030 0.06815 -0.0389 0.9894 0.0088
-7.000 -0.3743 0.05929 0.05703 -0.0498 0.9837 0.0091
-6.750 -0.3548 0.05119 0.04877 -0.0574 0.9791 0.0098
-6.500 -0.3388 0.04590 0.04333 -0.0599 0.9729 0.0102
-6.250 -0.3174 0.03983 0.03701 -0.0632 0.9685 0.0111
-6.000 -0.3409 0.02555 0.02170 -0.0577 0.9509 0.0123
-5.750 -0.3451 0.01795 0.01317 -0.0521 0.9388 0.0132
-5.500 -0.3225 0.01619 0.01124 -0.0512 0.9317 0.0155
-5.000 -0.2623 0.01643 0.01159 -0.0519 0.9140 0.0202
-4.750 -0.2320 0.01408 0.00880 -0.0525 0.9054 0.0248
-4.500 -0.1821 0.01520 0.01009 -0.0571 0.8946 0.0264
-4.250 -0.1368 0.01366 0.00813 -0.0609 0.8852 0.0305
-4.000 -0.0828 0.01352 0.00789 -0.0668 0.8725 0.0320
-3.750 -0.0267 0.01394 0.00830 -0.0733 0.8538 0.0337
-3.500 0.0226 0.01361 0.00773 -0.0782 0.8301 0.0360
-3.250 0.0619 0.01301 0.00681 -0.0808 0.8048 0.0374
-3.000 0.0918 0.01277 0.00632 -0.0811 0.7797 0.0382
-2.750 0.1168 0.01207 0.00540 -0.0805 0.7595 0.0390
-2.500 0.1413 0.01168 0.00488 -0.0798 0.7420 0.0397
-2.250 0.1656 0.01144 0.00453 -0.0790 0.7268 0.0403
-2.000 0.1900 0.01122 0.00422 -0.0781 0.7135 0.0410
-1.750 0.2145 0.01099 0.00389 -0.0773 0.7019 0.0415
-1.500 0.2388 0.01077 0.00358 -0.0765 0.6907 0.0420
-1.250 0.2631 0.01059 0.00334 -0.0756 0.6792 0.0427
-1.000 0.2871 0.01041 0.00310 -0.0747 0.6680 0.0432
-0.750 0.3108 0.01023 0.00285 -0.0737 0.6571 0.0438
-0.250 0.3584 0.01002 0.00255 -0.0717 0.6357 0.0456
0.000 0.3819 0.00992 0.00240 -0.0707 0.6249 0.0464
0.250 0.4052 0.00984 0.00228 -0.0696 0.6136 0.0469
0.500 0.4283 0.00978 0.00217 -0.0685 0.6015 0.0473
0.750 0.4513 0.00966 0.00202 -0.0674 0.5898 0.0484
1.000 0.4739 0.00958 0.00189 -0.0661 0.5762 0.0496
1.250 0.4964 0.00956 0.00183 -0.0649 0.5600 0.0512
1.500 0.5181 0.00959 0.00179 -0.0635 0.5407 0.0527
1.750 0.5404 0.00965 0.00178 -0.0622 0.5199 0.0537
2.000 0.5625 0.00972 0.00177 -0.0609 0.4998 0.0554
2.250 0.5847 0.00983 0.00180 -0.0597 0.4801 0.0573
2.500 0.6072 0.00993 0.00183 -0.0585 0.4612 0.0592
2.750 0.6298 0.01003 0.00188 -0.0574 0.4436 0.0643
3.000 0.6526 0.01014 0.00197 -0.0563 0.4276 0.0696
3.250 0.6760 0.01018 0.00208 -0.0554 0.4162 0.1143
3.750 0.9272 0.00979 0.00339 -0.1023 0.3568 1.0000
4.000 0.9488 0.01007 0.00354 -0.1010 0.3312 1.0000
4.250 0.9714 0.01029 0.00370 -0.0999 0.3133 1.0000
4.500 0.9934 0.01054 0.00389 -0.0988 0.2926 1.0000
4.750 1.0147 0.01085 0.00411 -0.0975 0.2687 1.0000
5.000 1.0352 0.01122 0.00436 -0.0960 0.2413 1.0000
5.250 1.0547 0.01166 0.00465 -0.0944 0.2104 1.0000
5.500 1.0748 0.01205 0.00495 -0.0929 0.1879 1.0000
5.750 1.0947 0.01243 0.00527 -0.0914 0.1701 1.0000
6.000 1.1143 0.01285 0.00561 -0.0899 0.1510 1.0000
6.250 1.1344 0.01321 0.00593 -0.0884 0.1384 1.0000
6.500 1.1539 0.01360 0.00628 -0.0868 0.1241 1.0000
6.750 1.1726 0.01404 0.00666 -0.0851 0.1061 1.0000
7.000 1.1909 0.01450 0.00705 -0.0834 0.0857 1.0000
7.250 1.2041 0.01530 0.00764 -0.0807 0.0549 1.0000
7.500 1.2217 0.01578 0.00814 -0.0788 0.0456 1.0000
7.750 1.2386 0.01629 0.00865 -0.0768 0.0378 1.0000
8.000 1.2549 0.01682 0.00917 -0.0746 0.0281 1.0000
8.250 1.2682 0.01753 0.00981 -0.0720 0.0169 1.0000
8.500 1.2837 0.01808 0.01040 -0.0697 0.0136 1.0000
8.750 1.2972 0.01865 0.01103 -0.0671 0.0118 1.0000
9.000 1.3085 0.01925 0.01168 -0.0640 0.0106 1.0000
9.250 1.3197 0.01983 0.01234 -0.0609 0.0098 1.0000
9.500 1.3306 0.02044 0.01304 -0.0578 0.0092 1.0000
9.750 1.3422 0.02100 0.01368 -0.0550 0.0084 1.0000
10.000 1.3521 0.02169 0.01445 -0.0520 0.0080 1.0000
10.250 1.3596 0.02254 0.01538 -0.0486 0.0073 1.0000
10.500 1.3652 0.02352 0.01646 -0.0450 0.0070 1.0000
10.750 1.3739 0.02432 0.01736 -0.0421 0.0067 1.0000
11.000 1.3810 0.02525 0.01840 -0.0391 0.0064 1.0000
11.250 1.3867 0.02629 0.01954 -0.0360 0.0062 1.0000
11.500 1.3930 0.02733 0.02068 -0.0332 0.0060 1.0000
11.750 1.3957 0.02866 0.02212 -0.0301 0.0058 1.0000
12.000 1.3992 0.03000 0.02356 -0.0274 0.0056 1.0000
12.250 1.4024 0.03146 0.02511 -0.0251 0.0054 1.0000
12.500 1.4025 0.03327 0.02702 -0.0227 0.0052 1.0000
12.750 1.4020 0.03525 0.02912 -0.0207 0.0049 1.0000
13.000 1.4009 0.03745 0.03142 -0.0191 0.0047 1.0000
13.250 1.3952 0.04030 0.03440 -0.0177 0.0047 1.0000
13.500 1.3957 0.04268 0.03691 -0.0168 0.0046 1.0000
13.750 1.3942 0.04540 0.03978 -0.0161 0.0045 1.0000
14.000 1.3902 0.04854 0.04306 -0.0157 0.0043 1.0000
14.250 1.3875 0.05162 0.04627 -0.0155 0.0042 1.0000
14.500 1.3789 0.05556 0.05035 -0.0156 0.0043 1.0000
14.750 1.3750 0.05905 0.05397 -0.0159 0.0041 1.0000
15.000 1.3663 0.06326 0.05831 -0.0165 0.0041 1.0000
15.250 1.3568 0.06775 0.06294 -0.0173 0.0040 1.0000
15.500 1.3482 0.07226 0.06759 -0.0184 0.0039 1.0000
15.750 1.3365 0.07732 0.07278 -0.0196 0.0041 1.0000
16.000 1.3268 0.08227 0.07786 -0.0211 0.0040 1.0000
16.250 1.3158 0.08764 0.08336 -0.0229 0.0038 1.0000
16.500 1.3105 0.09221 0.08804 -0.0246 0.0037 1.0000
16.750 1.2928 0.09875 0.09474 -0.0268 0.0038 1.0000
17.000 1.2827 0.10426 0.10036 -0.0289 0.0038 1.0000
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Polar data table (+)
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