GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 735 AIRFOIL (goe735-il) Reynolds number: 100,000 Max Cl/Cd: 23.43 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe735-il-100000.txt Download as CSV file: xf-goe735-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 735 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1323 0.10301 0.09791 -0.0512 0.8205 0.2044
-10.500 -0.3929 0.06647 0.06121 -0.0793 0.8342 0.1447
-10.250 -0.4212 0.06235 0.05693 -0.0769 0.8243 0.1442
-10.000 -0.4544 0.05886 0.05327 -0.0732 0.8126 0.1439
-9.750 -0.4883 0.05542 0.04951 -0.0684 0.8043 0.1439
-9.500 -0.5181 0.05211 0.04580 -0.0639 0.7931 0.1446
-9.250 -0.4652 0.05257 0.04664 -0.0652 0.7823 0.1495
-9.000 -0.4696 0.05050 0.04438 -0.0624 0.7714 0.1517
-8.750 -0.4790 0.04812 0.04167 -0.0585 0.7638 0.1537
-8.500 -0.4859 0.04577 0.03898 -0.0551 0.7531 0.1561
-8.250 -0.4929 0.04364 0.03632 -0.0506 0.7461 0.1585
-8.000 -0.4845 0.04174 0.03423 -0.0486 0.7355 0.1613
-7.750 -0.4596 0.04102 0.03361 -0.0478 0.7271 0.1652
-7.500 -0.4457 0.03990 0.03232 -0.0460 0.7175 0.1685
-7.250 -0.4354 0.03856 0.03064 -0.0434 0.7092 0.1721
-7.000 -0.4263 0.03744 0.02900 -0.0401 0.7031 0.1751
-6.750 -0.4058 0.03599 0.02760 -0.0396 0.6924 0.1784
-6.500 -0.3832 0.03510 0.02664 -0.0383 0.6858 0.1822
-6.250 -0.3637 0.03436 0.02576 -0.0371 0.6767 0.1860
-6.000 -0.3451 0.03348 0.02459 -0.0354 0.6690 0.1898
-5.750 -0.3245 0.03239 0.02318 -0.0337 0.6638 0.1934
-5.500 -0.3011 0.03174 0.02263 -0.0335 0.6537 0.1973
-5.250 -0.2769 0.03100 0.02176 -0.0324 0.6471 0.2017
-5.000 -0.2532 0.03034 0.02087 -0.0312 0.6417 0.2066
-4.750 -0.2313 0.02993 0.02036 -0.0306 0.6324 0.2110
-4.500 -0.2036 0.02909 0.01954 -0.0302 0.6265 0.2162
-4.250 -0.1780 0.02860 0.01894 -0.0294 0.6209 0.2224
-4.000 -0.1558 0.02849 0.01870 -0.0287 0.6121 0.2284
-3.750 -0.1266 0.02764 0.01794 -0.0286 0.6066 0.2355
-3.500 -0.0997 0.02720 0.01740 -0.0279 0.6019 0.2440
-3.250 -0.0769 0.02714 0.01747 -0.0276 0.5934 0.2524
-3.000 -0.0505 0.02672 0.01703 -0.0270 0.5879 0.2638
-2.750 -0.0218 0.02607 0.01638 -0.0265 0.5839 0.2771
-2.500 -0.0021 0.02626 0.01676 -0.0258 0.5756 0.2921
-2.250 0.0220 0.02592 0.01654 -0.0250 0.5698 0.3134
-2.000 0.0474 0.02535 0.01610 -0.0241 0.5659 0.3465
-1.750 0.0663 0.02508 0.01621 -0.0227 0.5606 0.3975
-1.500 0.0783 0.02478 0.01667 -0.0204 0.5538 0.4978
-1.250 0.1587 0.02408 0.01713 -0.0267 0.5480 0.7950
-1.000 0.2214 0.02469 0.01751 -0.0303 0.5436 0.8575
-0.750 0.2718 0.02638 0.01923 -0.0340 0.5350 0.8865
-0.500 0.3215 0.02706 0.01972 -0.0366 0.5298 0.9130
-0.250 0.3921 0.02732 0.01966 -0.0426 0.5254 0.9327
0.000 0.4508 0.02848 0.02083 -0.0490 0.5173 0.9520
0.250 0.5185 0.02867 0.02087 -0.0562 0.5113 0.9713
0.500 0.6075 0.02804 0.01994 -0.0669 0.5066 0.9952
0.750 0.6363 0.02864 0.02055 -0.0687 0.5016 1.0000
1.000 0.6473 0.02957 0.02155 -0.0676 0.4960 1.0000
1.250 0.6635 0.02985 0.02176 -0.0664 0.4919 1.0000
1.500 0.6822 0.02992 0.02171 -0.0651 0.4886 1.0000
1.750 0.7028 0.02999 0.02162 -0.0640 0.4860 1.0000
2.000 0.7004 0.03231 0.02418 -0.0621 0.4800 1.0000
2.250 0.7040 0.03387 0.02582 -0.0600 0.4750 1.0000
2.500 0.7191 0.03432 0.02622 -0.0585 0.4717 1.0000
2.750 0.7409 0.03425 0.02603 -0.0573 0.4691 1.0000
3.000 0.7653 0.03413 0.02575 -0.0563 0.4668 1.0000
3.250 0.5223 0.05190 0.04430 -0.0373 0.4500 1.0000
3.500 0.6065 0.04804 0.04029 -0.0398 0.4502 1.0000
3.750 0.6578 0.04614 0.03824 -0.0404 0.4494 1.0000
4.000 0.7144 0.04398 0.03593 -0.0415 0.4486 1.0000
4.250 0.7572 0.04287 0.03467 -0.0419 0.4474 1.0000
4.500 0.3115 0.07886 0.07130 -0.0220 0.4451 1.0000
4.750 0.3333 0.08078 0.07316 -0.0215 0.4465 1.0000
5.000 0.2256 0.09011 0.08268 -0.0205 0.4759 1.0000
5.250 0.2425 0.09157 0.08408 -0.0198 0.4715 1.0000
5.500 0.2692 0.09340 0.08584 -0.0196 0.4687 1.0000
5.750 0.3066 0.09596 0.08833 -0.0199 0.4670 1.0000
6.000 0.2598 0.09689 0.08927 -0.0170 0.4560 1.0000
6.250 0.2798 0.09845 0.09076 -0.0164 0.4516 1.0000
6.500 0.3082 0.10053 0.09278 -0.0163 0.4492 1.0000
6.750 0.3449 0.10346 0.09566 -0.0167 0.4478 1.0000
7.000 0.2953 0.10415 0.09637 -0.0142 0.4364 1.0000
7.250 0.3173 0.10582 0.09799 -0.0139 0.4323 1.0000
7.500 0.3488 0.10818 0.10030 -0.0139 0.4300 1.0000
7.750 0.3860 0.11152 0.10360 -0.0144 0.4288 1.0000
8.000 0.3309 0.11188 0.10398 -0.0123 0.4172 1.0000
8.250 0.3532 0.11370 0.10577 -0.0120 0.4134 1.0000
8.500 0.3849 0.11626 0.10828 -0.0120 0.4113 1.0000
8.750 0.4263 0.12012 0.11211 -0.0127 0.4101 1.0000
9.000 0.3666 0.11998 0.11200 -0.0110 0.3984 1.0000
9.250 0.3869 0.12197 0.11397 -0.0108 0.3952 1.0000
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Polar data table (+)
Polar graphs
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