GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 459 AIRFOIL (goe459-il) Reynolds number: 100,000 Max Cl/Cd: 37.28 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe459-il-100000-n5.txt Download as CSV file: xf-goe459-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 459 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7841 0.10419 0.09859 -0.0284 1.0000 0.0417
-14.750 -0.8619 0.08446 0.07860 -0.0407 1.0000 0.0390
-14.500 -0.8965 0.07528 0.06920 -0.0461 1.0000 0.0389
-14.250 -0.9215 0.06849 0.06219 -0.0495 1.0000 0.0390
-14.000 -0.9392 0.06343 0.05694 -0.0516 1.0000 0.0400
-13.750 -0.9556 0.05885 0.05213 -0.0528 1.0000 0.0408
-13.500 -0.9710 0.05474 0.04776 -0.0532 1.0000 0.0420
-13.250 -0.9865 0.05100 0.04367 -0.0528 1.0000 0.0435
-13.000 -0.9912 0.04854 0.04111 -0.0518 1.0000 0.0450
-12.750 -0.9918 0.04672 0.03926 -0.0506 1.0000 0.0466
-12.500 -0.9943 0.04488 0.03730 -0.0489 1.0000 0.0486
-12.250 -0.9978 0.04303 0.03523 -0.0467 1.0000 0.0509
-12.000 -1.0022 0.04128 0.03317 -0.0440 1.0000 0.0532
-11.750 -1.0015 0.03964 0.03137 -0.0414 1.0000 0.0554
-11.500 -0.9970 0.03845 0.03018 -0.0389 1.0000 0.0577
-11.250 -0.9943 0.03740 0.02906 -0.0359 1.0000 0.0603
-11.000 -0.9921 0.03637 0.02783 -0.0326 1.0000 0.0630
-10.750 -0.9875 0.03527 0.02645 -0.0294 1.0000 0.0654
-10.500 -0.9787 0.03407 0.02521 -0.0271 1.0000 0.0685
-10.250 -0.9702 0.03329 0.02444 -0.0246 1.0000 0.0721
-10.000 -0.9604 0.03242 0.02342 -0.0221 1.0000 0.0757
-9.750 -0.9484 0.03148 0.02222 -0.0198 1.0000 0.0784
-9.500 -0.9322 0.03027 0.02101 -0.0183 1.0000 0.0807
-9.250 -0.9169 0.02930 0.02000 -0.0165 1.0000 0.0829
-9.000 -0.9012 0.02838 0.01902 -0.0146 1.0000 0.0848
-8.750 -0.8852 0.02748 0.01803 -0.0128 1.0000 0.0866
-8.500 -0.8693 0.02664 0.01710 -0.0108 1.0000 0.0884
-8.250 -0.8537 0.02585 0.01620 -0.0088 1.0000 0.0903
-8.000 -0.8396 0.02506 0.01539 -0.0066 1.0000 0.0926
-7.750 -0.8266 0.02432 0.01465 -0.0042 1.0000 0.0953
-7.500 -0.8128 0.02367 0.01397 -0.0018 1.0000 0.0986
-7.250 -0.7986 0.02304 0.01328 0.0005 1.0000 0.1021
-7.000 -0.7852 0.02241 0.01263 0.0030 1.0000 0.1059
-6.750 -0.7722 0.02178 0.01204 0.0055 1.0000 0.1107
-6.500 -0.7582 0.02123 0.01144 0.0080 1.0000 0.1174
-6.250 -0.7453 0.02064 0.01091 0.0105 1.0000 0.1266
-6.000 -0.7319 0.02009 0.01040 0.0130 1.0000 0.1401
-5.750 -0.7185 0.01956 0.00993 0.0155 1.0000 0.1581
-5.500 -0.7051 0.01906 0.00952 0.0179 1.0000 0.1795
-5.250 -0.6918 0.01859 0.00916 0.0203 1.0000 0.2037
-5.000 -0.6777 0.01819 0.00886 0.0226 1.0000 0.2292
-4.750 -0.6631 0.01785 0.00858 0.0249 1.0000 0.2550
-4.500 -0.6480 0.01752 0.00833 0.0270 0.9999 0.2802
-4.250 -0.6116 0.01716 0.00806 0.0247 0.9931 0.3154
-4.000 -0.5789 0.01667 0.00785 0.0232 0.9857 0.3640
-3.750 -0.5486 0.01623 0.00773 0.0223 0.9778 0.4253
-3.500 -0.5171 0.01591 0.00762 0.0214 0.9706 0.4828
-3.250 -0.4864 0.01564 0.00753 0.0208 0.9627 0.5325
-3.000 -0.4565 0.01542 0.00748 0.0204 0.9546 0.5751
-2.750 -0.4222 0.01527 0.00742 0.0193 0.9478 0.6119
-2.500 -0.3922 0.01513 0.00736 0.0190 0.9391 0.6438
-2.250 -0.3553 0.01502 0.00729 0.0174 0.9330 0.6711
-2.000 -0.3240 0.01493 0.00723 0.0169 0.9243 0.6960
-1.750 -0.2862 0.01484 0.00721 0.0153 0.9182 0.7240
-1.500 -0.2507 0.01480 0.00724 0.0142 0.9108 0.7512
-1.250 -0.2117 0.01478 0.00726 0.0124 0.9039 0.7757
-1.000 -0.1689 0.01476 0.00727 0.0097 0.8980 0.7940
-0.750 -0.1304 0.01476 0.00728 0.0079 0.8892 0.8105
-0.500 -0.0864 0.01475 0.00727 0.0050 0.8824 0.8260
-0.250 -0.0447 0.01477 0.00732 0.0027 0.8718 0.8425
0.000 0.0001 0.01479 0.00735 0.0000 0.8586 0.8587
0.250 0.0447 0.01477 0.00732 -0.0027 0.8425 0.8718
0.500 0.0865 0.01475 0.00727 -0.0050 0.8259 0.8824
0.750 0.1304 0.01476 0.00728 -0.0079 0.8105 0.8892
1.000 0.1689 0.01476 0.00726 -0.0097 0.7940 0.8980
1.250 0.2118 0.01477 0.00726 -0.0124 0.7756 0.9040
1.500 0.2507 0.01480 0.00724 -0.0142 0.7515 0.9107
1.750 0.2862 0.01484 0.00721 -0.0153 0.7241 0.9182
2.000 0.3239 0.01493 0.00723 -0.0169 0.6961 0.9243
2.250 0.3554 0.01502 0.00729 -0.0174 0.6715 0.9330
2.500 0.3922 0.01513 0.00736 -0.0190 0.6438 0.9391
2.750 0.4223 0.01527 0.00742 -0.0193 0.6113 0.9479
3.000 0.4564 0.01542 0.00747 -0.0204 0.5735 0.9547
3.250 0.4863 0.01564 0.00753 -0.0207 0.5311 0.9627
3.500 0.5171 0.01591 0.00762 -0.0214 0.4826 0.9706
3.750 0.5487 0.01622 0.00772 -0.0223 0.4257 0.9779
4.000 0.5788 0.01667 0.00785 -0.0232 0.3639 0.9857
4.250 0.6117 0.01715 0.00806 -0.0247 0.3159 0.9931
4.500 0.6481 0.01752 0.00833 -0.0270 0.2802 0.9999
4.750 0.6631 0.01784 0.00858 -0.0249 0.2553 1.0000
5.000 0.6777 0.01818 0.00885 -0.0226 0.2295 1.0000
5.250 0.6917 0.01859 0.00917 -0.0203 0.2038 1.0000
5.500 0.7052 0.01905 0.00952 -0.0179 0.1802 1.0000
5.750 0.7185 0.01956 0.00993 -0.0155 0.1585 1.0000
6.000 0.7319 0.02009 0.01040 -0.0130 0.1403 1.0000
6.250 0.7453 0.02064 0.01091 -0.0105 0.1268 1.0000
6.500 0.7582 0.02123 0.01143 -0.0080 0.1177 1.0000
6.750 0.7722 0.02178 0.01203 -0.0055 0.1107 1.0000
7.000 0.7851 0.02241 0.01263 -0.0030 0.1059 1.0000
7.250 0.7986 0.02304 0.01328 -0.0005 0.1023 1.0000
7.500 0.8128 0.02366 0.01396 0.0018 0.0988 1.0000
7.750 0.8267 0.02432 0.01465 0.0042 0.0954 1.0000
8.000 0.8397 0.02506 0.01539 0.0066 0.0927 1.0000
8.250 0.8538 0.02585 0.01620 0.0088 0.0904 1.0000
8.500 0.8694 0.02664 0.01709 0.0108 0.0885 1.0000
8.750 0.8853 0.02748 0.01803 0.0128 0.0867 1.0000
9.000 0.9013 0.02837 0.01901 0.0146 0.0848 1.0000
9.250 0.9170 0.02929 0.01999 0.0164 0.0829 1.0000
9.500 0.9323 0.03026 0.02100 0.0182 0.0807 1.0000
9.750 0.9483 0.03146 0.02220 0.0198 0.0783 1.0000
10.000 0.9603 0.03239 0.02340 0.0221 0.0756 1.0000
10.250 0.9702 0.03327 0.02442 0.0246 0.0721 1.0000
10.500 0.9789 0.03406 0.02521 0.0271 0.0685 1.0000
10.750 0.9883 0.03529 0.02646 0.0293 0.0655 1.0000
11.000 0.9924 0.03636 0.02783 0.0326 0.0630 1.0000
11.250 0.9950 0.03743 0.02909 0.0358 0.0603 1.0000
11.500 0.9979 0.03848 0.03023 0.0388 0.0578 1.0000
11.750 1.0021 0.03966 0.03139 0.0413 0.0554 1.0000
12.000 1.0027 0.04127 0.03316 0.0439 0.0532 1.0000
12.250 0.9983 0.04301 0.03521 0.0467 0.0508 1.0000
12.500 0.9948 0.04488 0.03730 0.0489 0.0486 1.0000
12.750 0.9926 0.04669 0.03922 0.0505 0.0465 1.0000
13.000 0.9921 0.04849 0.04105 0.0517 0.0449 1.0000
13.250 0.9876 0.05101 0.04368 0.0527 0.0435 1.0000
13.500 0.9711 0.05478 0.04781 0.0531 0.0418 1.0000
13.750 0.9566 0.05879 0.05208 0.0527 0.0407 1.0000
14.000 0.9408 0.06323 0.05675 0.0514 0.0395 1.0000
14.250 0.9225 0.06852 0.06224 0.0493 0.0390 1.0000
14.500 0.8993 0.07499 0.06889 0.0461 0.0386 1.0000
14.750 0.8606 0.08496 0.07911 0.0402 0.0391 1.0000
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