GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 404 AIRFOIL (goe404-il) Reynolds number: 500,000 Max Cl/Cd: 94.19 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe404-il-500000-n5.txt Download as CSV file: xf-goe404-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 404 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7035 0.03331 0.02950 -0.0939 0.9745 0.0270
-11.250 -0.6874 0.02979 0.02564 -0.0963 0.9666 0.0271
-11.000 -0.6688 0.02760 0.02319 -0.0970 0.9578 0.0272
-10.750 -0.6478 0.02590 0.02127 -0.0974 0.9499 0.0273
-10.500 -0.6282 0.02432 0.01950 -0.0972 0.9407 0.0275
-10.250 -0.6072 0.02305 0.01810 -0.0968 0.9322 0.0277
-10.000 -0.5852 0.02202 0.01695 -0.0963 0.9232 0.0279
-9.750 -0.5624 0.02112 0.01594 -0.0958 0.9149 0.0280
-9.500 -0.5393 0.02031 0.01503 -0.0952 0.9046 0.0282
-9.250 -0.5159 0.01957 0.01417 -0.0945 0.8927 0.0284
-9.000 -0.4923 0.01888 0.01335 -0.0938 0.8784 0.0286
-8.750 -0.4683 0.01823 0.01257 -0.0931 0.8620 0.0288
-8.500 -0.4440 0.01762 0.01182 -0.0924 0.8429 0.0291
-8.250 -0.4195 0.01707 0.01110 -0.0917 0.8177 0.0293
-8.000 -0.3950 0.01659 0.01043 -0.0910 0.7894 0.0296
-7.750 -0.3699 0.01615 0.00981 -0.0903 0.7647 0.0299
-7.500 -0.3443 0.01574 0.00923 -0.0897 0.7448 0.0303
-7.250 -0.3183 0.01537 0.00869 -0.0893 0.7285 0.0306
-7.000 -0.2920 0.01500 0.00819 -0.0888 0.7141 0.0309
-6.750 -0.2653 0.01464 0.00771 -0.0884 0.7020 0.0311
-6.500 -0.2392 0.01421 0.00720 -0.0880 0.6908 0.0315
-6.250 -0.2122 0.01385 0.00678 -0.0877 0.6803 0.0318
-6.000 -0.1853 0.01355 0.00640 -0.0873 0.6711 0.0322
-5.750 -0.1578 0.01325 0.00605 -0.0871 0.6618 0.0327
-5.250 -0.1029 0.01275 0.00541 -0.0865 0.6433 0.0336
-5.000 -0.0754 0.01253 0.00512 -0.0862 0.6343 0.0342
-4.750 -0.0476 0.01231 0.00484 -0.0859 0.6264 0.0348
-4.500 -0.0199 0.01209 0.00457 -0.0856 0.6174 0.0354
-4.250 0.0077 0.01188 0.00433 -0.0854 0.6085 0.0363
-4.000 0.0355 0.01170 0.00410 -0.0851 0.5981 0.0374
-3.750 0.0633 0.01155 0.00389 -0.0848 0.5883 0.0387
-3.500 0.0910 0.01139 0.00369 -0.0845 0.5778 0.0404
-3.250 0.1187 0.01123 0.00351 -0.0843 0.5676 0.0429
-3.000 0.1463 0.01111 0.00336 -0.0840 0.5560 0.0465
-2.750 0.1741 0.01101 0.00326 -0.0837 0.5431 0.0525
-2.500 0.2018 0.01097 0.00320 -0.0835 0.5288 0.0595
-2.250 0.2295 0.01099 0.00316 -0.0832 0.5127 0.0649
-2.000 0.2571 0.01103 0.00313 -0.0829 0.4963 0.0690
-1.750 0.2846 0.01108 0.00309 -0.0826 0.4811 0.0727
-1.500 0.3123 0.01112 0.00309 -0.0823 0.4672 0.0757
-1.250 0.3400 0.01117 0.00309 -0.0821 0.4554 0.0787
-1.000 0.3675 0.01124 0.00306 -0.0818 0.4448 0.0811
-0.750 0.3952 0.01123 0.00305 -0.0816 0.4355 0.0836
-0.500 0.4227 0.01130 0.00308 -0.0813 0.4269 0.0863
-0.250 0.4506 0.01133 0.00308 -0.0811 0.4192 0.0891
0.000 0.4780 0.01139 0.00309 -0.0809 0.4109 0.0916
0.250 0.5055 0.01139 0.00309 -0.0807 0.4034 0.0945
0.500 0.5331 0.01143 0.00311 -0.0804 0.3960 0.0970
0.750 0.5604 0.01149 0.00313 -0.0802 0.3896 0.0992
1.000 0.5883 0.01151 0.00313 -0.0800 0.3837 0.1010
1.250 0.6157 0.01152 0.00314 -0.0797 0.3772 0.1036
1.500 0.6428 0.01158 0.00318 -0.0795 0.3717 0.1062
1.750 0.6707 0.01160 0.00321 -0.0793 0.3674 0.1090
2.000 0.6983 0.01165 0.00325 -0.0791 0.3622 0.1120
2.250 0.7256 0.01171 0.00330 -0.0789 0.3570 0.1162
2.500 0.7528 0.01178 0.00338 -0.0786 0.3526 0.1224
2.750 0.7804 0.01181 0.00345 -0.0785 0.3486 0.1310
3.000 0.8078 0.01184 0.00354 -0.0783 0.3443 0.1487
3.250 0.8347 0.01187 0.00366 -0.0780 0.3397 0.1917
3.500 0.8591 0.01130 0.00384 -0.0778 0.3348 0.5156
4.000 0.9237 0.01055 0.00418 -0.0793 0.3258 1.0000
4.250 0.9497 0.01072 0.00430 -0.0789 0.3218 1.0000
4.500 0.9753 0.01091 0.00445 -0.0784 0.3178 1.0000
4.750 1.0019 0.01104 0.00457 -0.0780 0.3141 1.0000
5.000 1.0279 0.01121 0.00471 -0.0776 0.3076 1.0000
5.250 1.0529 0.01145 0.00487 -0.0771 0.3001 1.0000
5.500 1.0790 0.01160 0.00502 -0.0767 0.2939 1.0000
5.750 1.1043 0.01182 0.00519 -0.0762 0.2868 1.0000
6.000 1.1296 0.01203 0.00538 -0.0757 0.2800 1.0000
6.250 1.1546 0.01226 0.00557 -0.0752 0.2716 1.0000
6.500 1.1793 0.01252 0.00578 -0.0747 0.2624 1.0000
6.750 1.2031 0.01282 0.00602 -0.0740 0.2504 1.0000
7.000 1.2260 0.01319 0.00630 -0.0733 0.2335 1.0000
7.250 1.2458 0.01377 0.00671 -0.0721 0.2055 1.0000
7.500 1.2642 0.01445 0.00722 -0.0708 0.1819 1.0000
7.750 1.2850 0.01494 0.00764 -0.0698 0.1719 1.0000
8.000 1.3057 0.01541 0.00807 -0.0687 0.1652 1.0000
8.250 1.3272 0.01580 0.00846 -0.0678 0.1608 1.0000
8.500 1.3477 0.01623 0.00888 -0.0667 0.1568 1.0000
8.750 1.3673 0.01670 0.00933 -0.0656 0.1531 1.0000
9.000 1.3870 0.01708 0.00974 -0.0644 0.1506 1.0000
9.250 1.4059 0.01747 0.01015 -0.0631 0.1482 1.0000
9.500 1.4239 0.01792 0.01062 -0.0617 0.1455 1.0000
9.750 1.4409 0.01843 0.01114 -0.0602 0.1428 1.0000
10.000 1.4565 0.01903 0.01175 -0.0586 0.1398 1.0000
10.250 1.4730 0.01959 0.01233 -0.0572 0.1372 1.0000
10.500 1.4905 0.02011 0.01289 -0.0560 0.1350 1.0000
10.750 1.5069 0.02070 0.01352 -0.0548 0.1326 1.0000
11.000 1.5223 0.02138 0.01423 -0.0535 0.1302 1.0000
11.250 1.5364 0.02215 0.01503 -0.0521 0.1279 1.0000
11.500 1.5493 0.02303 0.01594 -0.0507 0.1256 1.0000
11.750 1.5642 0.02381 0.01677 -0.0496 0.1238 1.0000
12.000 1.5786 0.02464 0.01765 -0.0485 0.1216 1.0000
12.250 1.5915 0.02561 0.01867 -0.0474 0.1185 1.0000
12.500 1.6025 0.02676 0.01984 -0.0463 0.1154 1.0000
12.750 1.6123 0.02805 0.02117 -0.0453 0.1127 1.0000
13.000 1.6239 0.02925 0.02242 -0.0444 0.1096 1.0000
13.250 1.6331 0.03069 0.02391 -0.0435 0.1057 1.0000
13.500 1.6396 0.03244 0.02568 -0.0427 0.1019 1.0000
13.750 1.6472 0.03414 0.02744 -0.0421 0.0973 1.0000
14.000 1.6503 0.03635 0.02967 -0.0414 0.0917 1.0000
14.250 1.6516 0.03878 0.03212 -0.0409 0.0846 1.0000
14.500 1.6485 0.04173 0.03508 -0.0404 0.0770 1.0000
14.750 1.6433 0.04498 0.03835 -0.0400 0.0718 1.0000
15.000 1.6370 0.04843 0.04185 -0.0398 0.0681 1.0000
15.250 1.6316 0.05188 0.04536 -0.0398 0.0659 1.0000
15.500 1.6260 0.05545 0.04900 -0.0399 0.0642 1.0000
15.750 1.6186 0.05930 0.05292 -0.0401 0.0626 1.0000
16.000 1.6099 0.06342 0.05712 -0.0405 0.0613 1.0000
16.250 1.6011 0.06765 0.06144 -0.0410 0.0601 1.0000
16.500 1.5947 0.07163 0.06552 -0.0416 0.0593 1.0000
16.750 1.5873 0.07580 0.06979 -0.0423 0.0585 1.0000
17.000 1.5795 0.08010 0.07417 -0.0430 0.0578 1.0000
17.250 1.5711 0.08448 0.07865 -0.0439 0.0572 1.0000
17.500 1.5622 0.08897 0.08322 -0.0449 0.0565 1.0000
17.750 1.5529 0.09358 0.08791 -0.0459 0.0558 1.0000
18.000 1.5435 0.09823 0.09265 -0.0471 0.0552 1.0000
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