GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 100,000 Max Cl/Cd: 58.34 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe408-il-100000.txt Download as CSV file: xf-goe408-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3827 0.09471 0.08994 -0.0207 1.0000 0.0638
-7.250 -0.3898 0.09251 0.08781 -0.0202 1.0000 0.0653
-7.000 -0.3937 0.09021 0.08558 -0.0221 1.0000 0.0671
-6.750 -0.3946 0.08832 0.08371 -0.0259 1.0000 0.0681
-6.500 -0.3929 0.08686 0.08215 -0.0304 1.0000 0.0687
-6.250 -0.3904 0.08090 0.07633 -0.0272 1.0000 0.0697
-6.000 -0.3863 0.07723 0.07274 -0.0238 1.0000 0.0712
-5.750 -0.3821 0.07436 0.06991 -0.0222 1.0000 0.0735
-5.500 -0.3774 0.07168 0.06723 -0.0218 1.0000 0.0770
-5.250 -0.3643 0.07146 0.06662 -0.0274 1.0000 0.0823
-5.000 -0.3646 0.06601 0.06137 -0.0243 1.0000 0.0839
-4.750 -0.3623 0.06313 0.05857 -0.0213 1.0000 0.0863
-4.500 -0.3575 0.06083 0.05627 -0.0198 1.0000 0.0897
-4.250 -0.3427 0.06102 0.05590 -0.0218 1.0000 0.0968
-4.000 -0.3418 0.05627 0.05139 -0.0193 1.0000 0.0983
-3.750 -0.3389 0.05377 0.04897 -0.0167 1.0000 0.1015
-3.500 -0.3250 0.05328 0.04801 -0.0168 1.0000 0.1114
-3.250 -0.3045 0.04907 0.04401 -0.0177 0.9954 0.1185
-3.000 -0.2659 0.04590 0.04059 -0.0220 0.9866 0.1325
-2.750 -0.2265 0.04368 0.03793 -0.0259 0.9763 0.1555
-2.500 -0.1991 0.04046 0.03477 -0.0274 0.9673 0.1759
-2.250 -0.1676 0.03874 0.03274 -0.0293 0.9569 0.2145
-2.000 -0.1395 0.03569 0.02977 -0.0304 0.9489 0.2493
-1.750 -0.1167 0.03350 0.02764 -0.0301 0.9391 0.3090
-1.500 -0.0937 0.03147 0.02564 -0.0292 0.9285 0.3584
-1.250 -0.0641 0.02982 0.02381 -0.0294 0.9185 0.3945
-1.000 0.0696 0.01148 0.00369 -0.0437 0.8906 0.1527
-0.750 0.0651 0.02648 0.01795 -0.0377 0.9029 0.1419
-0.500 0.1131 0.02490 0.01609 -0.0407 0.8970 0.1350
-0.250 0.1491 0.02382 0.01480 -0.0417 0.8862 0.1339
0.000 0.2021 0.02234 0.01307 -0.0456 0.8816 0.1295
0.250 0.2403 0.02142 0.01202 -0.0469 0.8707 0.1288
0.500 0.2990 0.02004 0.01063 -0.0523 0.8664 0.1317
0.750 0.3407 0.01937 0.00993 -0.0546 0.8548 0.1393
1.000 0.3932 0.01827 0.00899 -0.0592 0.8453 0.1453
1.250 0.4659 0.01722 0.00796 -0.0679 0.8374 0.1604
1.500 0.6532 0.01445 0.00694 -0.1022 0.8283 1.0000
1.750 0.6986 0.01438 0.00671 -0.1055 0.8091 1.0000
2.000 0.7357 0.01448 0.00668 -0.1071 0.7890 1.0000
2.250 0.7659 0.01469 0.00681 -0.1072 0.7681 1.0000
2.500 0.7970 0.01492 0.00693 -0.1075 0.7486 1.0000
2.750 0.8236 0.01521 0.00713 -0.1069 0.7290 1.0000
3.000 0.8465 0.01549 0.00735 -0.1054 0.7070 1.0000
3.250 0.8712 0.01571 0.00745 -0.1042 0.6850 1.0000
3.500 0.8908 0.01596 0.00765 -0.1020 0.6628 1.0000
3.750 0.9135 0.01621 0.00784 -0.1006 0.6437 1.0000
4.000 0.9367 0.01649 0.00810 -0.0993 0.6266 1.0000
4.250 0.9578 0.01678 0.00838 -0.0976 0.6091 1.0000
4.500 0.9785 0.01707 0.00870 -0.0959 0.5917 1.0000
4.750 0.9992 0.01735 0.00899 -0.0942 0.5739 1.0000
5.000 1.0203 0.01763 0.00931 -0.0925 0.5563 1.0000
5.250 1.0416 0.01791 0.00959 -0.0909 0.5387 1.0000
5.500 1.0627 0.01823 0.00990 -0.0892 0.5207 1.0000
5.750 1.0805 0.01854 0.01028 -0.0869 0.4999 1.0000
6.000 1.0997 0.01885 0.01054 -0.0848 0.4783 1.0000
6.250 1.1161 0.01921 0.01096 -0.0822 0.4544 1.0000
6.500 1.1325 0.01959 0.01130 -0.0797 0.4295 1.0000
6.750 1.1478 0.02002 0.01168 -0.0769 0.4033 1.0000
7.000 1.1614 0.02048 0.01217 -0.0739 0.3763 1.0000
7.250 1.1755 0.02101 0.01272 -0.0711 0.3504 1.0000
7.500 1.1892 0.02157 0.01327 -0.0683 0.3258 1.0000
7.750 1.1996 0.02207 0.01373 -0.0649 0.2989 1.0000
8.000 1.2085 0.02261 0.01425 -0.0613 0.2700 1.0000
8.250 1.2168 0.02328 0.01490 -0.0578 0.2397 1.0000
8.500 1.2226 0.02417 0.01574 -0.0539 0.2038 1.0000
8.750 1.2216 0.02562 0.01695 -0.0491 0.1587 1.0000
9.000 1.2145 0.02755 0.01855 -0.0434 0.1155 1.0000
9.250 1.2127 0.02917 0.02002 -0.0384 0.0912 1.0000
9.500 1.2122 0.03079 0.02155 -0.0339 0.0789 1.0000
9.750 1.2135 0.03254 0.02328 -0.0298 0.0713 1.0000
10.000 1.2149 0.03458 0.02518 -0.0263 0.0653 1.0000
10.250 1.2253 0.03635 0.02711 -0.0238 0.0608 1.0000
10.500 1.2395 0.03859 0.02933 -0.0220 0.0564 1.0000
10.750 1.2716 0.04227 0.03305 -0.0231 0.0527 1.0000
11.000 1.2790 0.04425 0.03539 -0.0203 0.0500 1.0000
11.250 1.2910 0.04679 0.03820 -0.0184 0.0482 1.0000
11.500 1.3003 0.04967 0.04134 -0.0164 0.0467 1.0000
11.750 1.3048 0.05270 0.04467 -0.0139 0.0462 1.0000
12.000 1.3030 0.05578 0.04805 -0.0110 0.0459 1.0000
12.250 1.2946 0.05895 0.05156 -0.0077 0.0459 1.0000
12.500 1.2823 0.06244 0.05535 -0.0047 0.0457 1.0000
12.750 1.2649 0.06607 0.05930 -0.0022 0.0459 1.0000
13.000 1.2429 0.07024 0.06380 -0.0006 0.0466 1.0000
13.250 1.2192 0.07501 0.06887 -0.0002 0.0471 1.0000
13.500 1.1935 0.08053 0.07464 -0.0009 0.0472 1.0000
13.750 1.1670 0.08664 0.08100 -0.0028 0.0479 1.0000
14.000 1.1377 0.09389 0.08846 -0.0060 0.0485 1.0000
14.250 1.1074 0.10209 0.09685 -0.0105 0.0493 1.0000
14.500 1.0763 0.11145 0.10635 -0.0161 0.0502 1.0000
14.750 1.0435 0.12244 0.11741 -0.0229 0.0513 1.0000
15.000 1.0175 0.13316 0.12815 -0.0290 0.0525 1.0000
15.250 1.0023 0.14199 0.13696 -0.0327 0.0534 1.0000
15.500 0.7184 0.15828 0.15338 -0.0347 0.0828 1.0000
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Polar data table (+)
Polar graphs
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