GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 416A AIRFOIL (goe416a-il) Reynolds number: 500,000 Max Cl/Cd: 67.48 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe416a-il-500000-n5.txt Download as CSV file: xf-goe416a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 416A 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6045 0.09860 0.09642 -0.0048 1.0000 0.0065
-10.500 -0.6103 0.09151 0.08935 -0.0089 1.0000 0.0062
-10.250 -0.6237 0.08131 0.07911 -0.0162 1.0000 0.0060
-10.000 -0.6404 0.07305 0.07077 -0.0231 1.0000 0.0059
-9.750 -0.6820 0.05932 0.05668 -0.0331 1.0000 0.0046
-9.500 -0.6951 0.05475 0.05199 -0.0374 1.0000 0.0046
-9.250 -0.7041 0.05083 0.04790 -0.0392 1.0000 0.0045
-9.000 -0.7060 0.04688 0.04373 -0.0402 1.0000 0.0045
-8.750 -0.7030 0.04302 0.03963 -0.0405 1.0000 0.0045
-8.500 -0.6958 0.03927 0.03559 -0.0404 1.0000 0.0045
-8.250 -0.6852 0.03562 0.03164 -0.0399 1.0000 0.0045
-8.000 -0.6714 0.03226 0.02795 -0.0391 1.0000 0.0046
-7.750 -0.6561 0.02917 0.02452 -0.0382 1.0000 0.0047
-7.500 -0.6403 0.02644 0.02153 -0.0373 1.0000 0.0048
-7.250 -0.6222 0.02468 0.01959 -0.0364 1.0000 0.0049
-7.000 -0.5945 0.02331 0.01806 -0.0374 0.9967 0.0051
-6.750 -0.5634 0.02210 0.01672 -0.0388 0.9914 0.0055
-6.500 -0.5318 0.02065 0.01509 -0.0400 0.9861 0.0060
-6.250 -0.5017 0.01892 0.01319 -0.0407 0.9794 0.0061
-6.000 -0.4717 0.01734 0.01147 -0.0412 0.9720 0.0062
-5.750 -0.4418 0.01601 0.01004 -0.0418 0.9636 0.0064
-5.500 -0.4134 0.01494 0.00887 -0.0420 0.9538 0.0067
-5.250 -0.3860 0.01413 0.00795 -0.0421 0.9435 0.0070
-5.000 -0.3604 0.01308 0.00682 -0.0420 0.9321 0.0074
-4.750 -0.3344 0.01248 0.00619 -0.0418 0.9197 0.0079
-4.500 -0.3081 0.01212 0.00577 -0.0416 0.9064 0.0089
-4.250 -0.2820 0.01164 0.00520 -0.0413 0.8924 0.0096
-4.000 -0.2555 0.01115 0.00460 -0.0410 0.8780 0.0102
-3.750 -0.2285 0.01080 0.00414 -0.0409 0.8642 0.0108
-3.500 -0.2014 0.01024 0.00344 -0.0408 0.8506 0.0122
-3.250 -0.1739 0.00995 0.00304 -0.0407 0.8351 0.0145
-3.000 -0.1464 0.00977 0.00270 -0.0406 0.8150 0.0162
-2.750 -0.1190 0.00966 0.00243 -0.0404 0.7896 0.0182
-2.500 -0.0916 0.00954 0.00219 -0.0402 0.7615 0.0276
-2.000 -0.0391 0.00763 0.00157 -0.0411 0.7159 0.4518
-1.750 -0.0109 0.00774 0.00158 -0.0411 0.6956 0.4728
-1.500 0.0174 0.00785 0.00160 -0.0411 0.6752 0.4873
-1.250 0.0456 0.00796 0.00163 -0.0411 0.6548 0.4977
-1.000 0.0740 0.00805 0.00159 -0.0412 0.6371 0.5014
-0.750 0.1025 0.00811 0.00156 -0.0413 0.6220 0.5046
-0.500 0.1309 0.00814 0.00156 -0.0415 0.6083 0.5078
-0.250 0.1595 0.00820 0.00156 -0.0416 0.5939 0.5108
0.000 0.1881 0.00825 0.00155 -0.0418 0.5797 0.5130
0.250 0.2167 0.00831 0.00155 -0.0419 0.5658 0.5153
0.500 0.2452 0.00838 0.00155 -0.0421 0.5498 0.5174
0.750 0.2735 0.00844 0.00157 -0.0422 0.5294 0.5192
1.000 0.3018 0.00851 0.00159 -0.0423 0.5086 0.5211
1.250 0.3300 0.00861 0.00163 -0.0424 0.4883 0.5233
1.500 0.3580 0.00873 0.00168 -0.0426 0.4672 0.5257
1.750 0.3861 0.00887 0.00175 -0.0427 0.4490 0.5281
2.000 0.4142 0.00900 0.00183 -0.0428 0.4333 0.5303
2.250 0.4423 0.00913 0.00192 -0.0429 0.4190 0.5324
2.500 0.4704 0.00923 0.00202 -0.0430 0.4057 0.5345
2.750 0.4986 0.00933 0.00213 -0.0431 0.3949 0.5370
3.000 0.5267 0.00943 0.00225 -0.0432 0.3846 0.5399
3.250 0.5548 0.00954 0.00237 -0.0434 0.3728 0.5428
3.500 0.5829 0.00967 0.00251 -0.0435 0.3585 0.5455
3.750 0.6102 0.00989 0.00264 -0.0435 0.3224 0.5481
4.000 0.6356 0.01041 0.00287 -0.0434 0.2560 0.5509
4.250 0.6622 0.01075 0.00314 -0.0434 0.2310 0.5540
4.500 0.6896 0.01096 0.00336 -0.0434 0.2197 0.5575
4.750 0.7169 0.01117 0.00359 -0.0434 0.2097 0.5613
5.000 0.7441 0.01138 0.00385 -0.0434 0.2002 0.5652
5.250 0.7714 0.01156 0.00410 -0.0434 0.1899 0.5697
5.500 0.7983 0.01183 0.00436 -0.0434 0.1711 0.5742
5.750 0.8227 0.01245 0.00473 -0.0432 0.1165 0.5787
6.000 0.8476 0.01299 0.00518 -0.0430 0.0902 0.5841
6.250 0.8724 0.01352 0.00564 -0.0428 0.0638 0.5900
6.500 0.8975 0.01399 0.00610 -0.0425 0.0479 0.5966
6.750 0.9226 0.01445 0.00656 -0.0423 0.0366 0.6044
7.000 0.9469 0.01499 0.00709 -0.0420 0.0226 0.6134
7.250 0.9708 0.01559 0.00770 -0.0415 0.0127 0.6248
7.500 0.9946 0.01615 0.00835 -0.0411 0.0099 0.6394
7.750 1.0181 0.01674 0.00910 -0.0406 0.0081 0.6595
8.000 1.0417 0.01722 0.00982 -0.0401 0.0074 0.6907
8.250 1.0636 0.01762 0.01058 -0.0392 0.0068 0.7716
8.500 1.0822 0.01789 0.01129 -0.0375 0.0062 1.0000
8.750 1.1023 0.01888 0.01237 -0.0367 0.0056 1.0000
9.000 1.1236 0.01967 0.01325 -0.0359 0.0052 1.0000
9.250 1.1445 0.02044 0.01412 -0.0352 0.0048 1.0000
9.500 1.1639 0.02135 0.01513 -0.0342 0.0045 1.0000
9.750 1.1824 0.02231 0.01619 -0.0332 0.0043 1.0000
10.000 1.1997 0.02332 0.01730 -0.0321 0.0040 1.0000
10.250 1.2155 0.02442 0.01850 -0.0309 0.0039 1.0000
10.500 1.2279 0.02576 0.01997 -0.0293 0.0037 1.0000
10.750 1.2341 0.02756 0.02191 -0.0270 0.0035 1.0000
11.000 1.2409 0.02893 0.02341 -0.0247 0.0035 1.0000
11.250 1.2463 0.03041 0.02505 -0.0224 0.0034 1.0000
11.500 1.2498 0.03216 0.02695 -0.0205 0.0033 1.0000
11.750 1.2517 0.03418 0.02913 -0.0188 0.0032 1.0000
12.000 1.2522 0.03649 0.03161 -0.0176 0.0032 1.0000
12.250 1.2513 0.03913 0.03442 -0.0168 0.0031 1.0000
12.500 1.2491 0.04213 0.03759 -0.0166 0.0030 1.0000
12.750 1.2462 0.04545 0.04108 -0.0170 0.0030 1.0000
13.000 1.2414 0.04926 0.04507 -0.0179 0.0029 1.0000
13.250 1.2356 0.05345 0.04943 -0.0193 0.0029 1.0000
13.500 1.2281 0.05808 0.05423 -0.0211 0.0028 1.0000
13.750 1.2188 0.06316 0.05948 -0.0234 0.0028 1.0000
14.000 1.2075 0.06876 0.06524 -0.0260 0.0027 1.0000
14.250 1.1954 0.07473 0.07136 -0.0290 0.0027 1.0000
14.500 1.1793 0.08151 0.07830 -0.0323 0.0027 1.0000
14.750 1.1640 0.08843 0.08536 -0.0359 0.0027 1.0000
15.000 1.1449 0.09627 0.09336 -0.0399 0.0027 1.0000
15.250 1.1278 0.10411 0.10133 -0.0439 0.0027 1.0000
15.500 1.1081 0.11282 0.11018 -0.0484 0.0027 1.0000
15.750 1.0881 0.12186 0.11936 -0.0531 0.0028 1.0000
16.000 1.0678 0.13127 0.12889 -0.0580 0.0028 1.0000
16.250 1.0475 0.14109 0.13883 -0.0632 0.0029 1.0000
16.500 1.0255 0.15183 0.14969 -0.0688 0.0029 1.0000
16.750 1.0018 0.16389 0.16185 -0.0751 0.0030 1.0000
17.000 0.9741 0.17848 0.17654 -0.0825 0.0032 1.0000
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