GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 100,000 Max Cl/Cd: 53.72 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe701-il-100000-n5.txt Download as CSV file: xf-goe701-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3322 0.11412 0.10889 -0.0429 1.0000 0.0584
-10.500 -0.3406 0.11117 0.10600 -0.0424 1.0000 0.0585
-10.250 -0.3580 0.10755 0.10246 -0.0424 1.0000 0.0592
-10.000 -0.3643 0.10510 0.10008 -0.0417 0.9997 0.0602
-9.750 -0.3381 0.10365 0.09860 -0.0430 0.9964 0.0624
-9.500 -0.3275 0.09924 0.09417 -0.0473 0.9917 0.0631
-9.250 -0.3183 0.09474 0.08965 -0.0519 0.9863 0.0640
-9.000 -0.3110 0.09007 0.08496 -0.0569 0.9805 0.0657
-8.750 -0.3082 0.08456 0.07945 -0.0628 0.9731 0.0667
-8.500 -0.3115 0.07893 0.07381 -0.0685 0.9633 0.0671
-8.250 -0.3199 0.07173 0.06658 -0.0761 0.9512 0.0678
-8.000 -0.3364 0.05999 0.05464 -0.0874 0.9377 0.0692
-7.500 -0.2989 0.05431 0.04876 -0.0924 0.9259 0.0714
-7.250 -0.2980 0.04861 0.04279 -0.0945 0.9151 0.0726
-7.000 -0.2937 0.04246 0.03617 -0.0965 0.9068 0.0751
-6.750 -0.2920 0.03557 0.02837 -0.0972 0.8984 0.0781
-6.500 -0.2650 0.03290 0.02530 -0.0987 0.8953 0.0798
-6.250 -0.2506 0.03213 0.02445 -0.0967 0.8859 0.0809
-6.000 -0.2202 0.03109 0.02326 -0.0977 0.8822 0.0831
-5.750 -0.1933 0.02966 0.02152 -0.0981 0.8776 0.0861
-5.500 -0.1754 0.02811 0.01954 -0.0968 0.8699 0.0889
-5.250 -0.1443 0.02678 0.01795 -0.0977 0.8662 0.0912
-5.000 -0.1151 0.02615 0.01729 -0.0981 0.8617 0.0936
-4.750 -0.0932 0.02564 0.01666 -0.0970 0.8543 0.0968
-4.500 -0.0612 0.02466 0.01537 -0.0978 0.8505 0.1014
-4.250 -0.0290 0.02376 0.01433 -0.0986 0.8468 0.1050
-4.000 -0.0090 0.02342 0.01398 -0.0972 0.8387 0.1081
-3.750 0.0237 0.02284 0.01326 -0.0980 0.8346 0.1139
-3.500 0.0591 0.02212 0.01238 -0.0992 0.8316 0.1200
-3.250 0.0771 0.02193 0.01222 -0.0974 0.8226 0.1242
-3.000 0.1099 0.02144 0.01161 -0.0981 0.8183 0.1311
-2.750 0.1425 0.02100 0.01113 -0.0989 0.8141 0.1378
-2.500 0.1634 0.02087 0.01099 -0.0975 0.8058 0.1437
-2.250 0.1965 0.02047 0.01048 -0.0982 0.8014 0.1511
-2.000 0.2248 0.02024 0.01029 -0.0982 0.7956 0.1579
-1.750 0.2495 0.02011 0.01007 -0.0974 0.7883 0.1659
-1.500 0.2826 0.01979 0.00980 -0.0983 0.7838 0.1741
-1.250 0.3066 0.01968 0.00963 -0.0974 0.7764 0.1819
-1.000 0.3340 0.01944 0.00944 -0.0971 0.7699 0.1887
-0.750 0.3691 0.01910 0.00904 -0.0982 0.7655 0.1980
-0.500 0.3878 0.01904 0.00908 -0.0964 0.7566 0.2058
-0.250 0.4188 0.01878 0.00881 -0.0967 0.7509 0.2165
0.000 0.4446 0.01863 0.00870 -0.0962 0.7439 0.2278
0.250 0.4706 0.01848 0.00861 -0.0956 0.7364 0.2411
0.500 0.5061 0.01817 0.00834 -0.0968 0.7314 0.2627
0.750 0.5255 0.01818 0.00848 -0.0952 0.7218 0.2865
1.250 0.5769 0.01756 0.00839 -0.0941 0.7054 0.4319
1.750 0.7095 0.01617 0.00798 -0.1085 0.6789 1.0000
2.000 0.7307 0.01623 0.00794 -0.1069 0.6668 1.0000
2.250 0.7501 0.01638 0.00803 -0.1051 0.6559 1.0000
2.500 0.7743 0.01645 0.00800 -0.1041 0.6466 1.0000
2.750 0.7940 0.01660 0.00810 -0.1023 0.6354 1.0000
3.000 0.8142 0.01675 0.00820 -0.1006 0.6245 1.0000
3.250 0.8372 0.01685 0.00822 -0.0994 0.6140 1.0000
3.500 0.8567 0.01701 0.00834 -0.0977 0.6020 1.0000
3.750 0.8759 0.01718 0.00849 -0.0958 0.5896 1.0000
4.000 0.8962 0.01735 0.00859 -0.0942 0.5773 1.0000
4.250 0.9168 0.01751 0.00869 -0.0926 0.5645 1.0000
4.500 0.9363 0.01770 0.00884 -0.0908 0.5512 1.0000
4.750 0.9541 0.01793 0.00904 -0.0888 0.5370 1.0000
5.000 0.9718 0.01817 0.00923 -0.0867 0.5221 1.0000
5.250 0.9891 0.01843 0.00945 -0.0846 0.5064 1.0000
5.500 1.0056 0.01872 0.00968 -0.0824 0.4900 1.0000
5.750 1.0215 0.01904 0.00993 -0.0800 0.4732 1.0000
6.000 1.0366 0.01939 0.01022 -0.0776 0.4560 1.0000
6.250 1.0501 0.01977 0.01054 -0.0750 0.4384 1.0000
6.500 1.0622 0.02019 0.01087 -0.0721 0.4206 1.0000
6.750 1.0737 0.02065 0.01125 -0.0691 0.4029 1.0000
7.000 1.0852 0.02116 0.01169 -0.0663 0.3860 1.0000
7.250 1.0970 0.02171 0.01217 -0.0637 0.3699 1.0000
7.500 1.1090 0.02230 0.01270 -0.0611 0.3549 1.0000
7.750 1.1211 0.02293 0.01327 -0.0587 0.3408 1.0000
8.000 1.1340 0.02357 0.01387 -0.0564 0.3283 1.0000
8.250 1.1472 0.02424 0.01451 -0.0543 0.3174 1.0000
8.500 1.1603 0.02494 0.01515 -0.0522 0.3073 1.0000
8.750 1.1740 0.02563 0.01586 -0.0503 0.2975 1.0000
9.000 1.1874 0.02638 0.01654 -0.0484 0.2892 1.0000
9.250 1.2013 0.02710 0.01734 -0.0467 0.2807 1.0000
9.500 1.2149 0.02789 0.01806 -0.0449 0.2735 1.0000
9.750 1.2289 0.02865 0.01891 -0.0433 0.2660 1.0000
10.000 1.2429 0.02945 0.01970 -0.0417 0.2597 1.0000
10.250 1.2572 0.03026 0.02057 -0.0401 0.2534 1.0000
10.500 1.2698 0.03112 0.02151 -0.0385 0.2468 1.0000
10.750 1.2829 0.03201 0.02236 -0.0369 0.2408 1.0000
11.000 1.2931 0.03298 0.02347 -0.0352 0.2338 1.0000
11.250 1.3037 0.03397 0.02447 -0.0335 0.2276 1.0000
11.500 1.3134 0.03503 0.02563 -0.0319 0.2212 1.0000
11.750 1.3233 0.03611 0.02682 -0.0303 0.2154 1.0000
12.000 1.3333 0.03720 0.02790 -0.0288 0.2101 1.0000
12.250 1.3402 0.03848 0.02935 -0.0272 0.2039 1.0000
12.500 1.3463 0.03981 0.03078 -0.0256 0.1979 1.0000
12.750 1.3531 0.04115 0.03217 -0.0242 0.1926 1.0000
13.000 1.3581 0.04268 0.03390 -0.0228 0.1865 1.0000
13.250 1.3624 0.04425 0.03555 -0.0214 0.1812 1.0000
13.500 1.3663 0.04595 0.03737 -0.0202 0.1756 1.0000
13.750 1.3691 0.04780 0.03940 -0.0191 0.1696 1.0000
14.000 1.3690 0.04987 0.04150 -0.0180 0.1638 1.0000
14.250 1.3704 0.05204 0.04390 -0.0172 0.1570 1.0000
14.500 1.3698 0.05441 0.04637 -0.0165 0.1514 1.0000
14.750 1.3700 0.05687 0.04901 -0.0159 0.1453 1.0000
15.000 1.3669 0.05974 0.05198 -0.0155 0.1387 1.0000
15.250 1.3631 0.06286 0.05525 -0.0154 0.1314 1.0000
15.500 1.3546 0.06663 0.05907 -0.0156 0.1235 1.0000
15.750 1.3480 0.07039 0.06298 -0.0159 0.1153 1.0000
16.000 1.3368 0.07489 0.06756 -0.0166 0.1066 1.0000
16.250 1.3231 0.07993 0.07266 -0.0177 0.0992 1.0000
16.500 1.3089 0.08529 0.07813 -0.0190 0.0906 1.0000
16.750 1.2927 0.09114 0.08408 -0.0208 0.0838 1.0000
17.000 1.2737 0.09766 0.09069 -0.0230 0.0775 1.0000
17.250 1.2556 0.10427 0.09742 -0.0255 0.0703 1.0000
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