GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 500,000 Max Cl/Cd: 101.84 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe408-il-500000.txt Download as CSV file: xf-goe408-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3196 0.09191 0.08983 -0.0229 1.0000 0.0220
-8.500 -0.3254 0.08873 0.08668 -0.0240 1.0000 0.0221
-8.250 -0.3284 0.08534 0.08331 -0.0243 1.0000 0.0221
-8.000 -0.3292 0.08048 0.07849 -0.0230 1.0000 0.0224
-7.750 -0.3281 0.07753 0.07555 -0.0220 1.0000 0.0226
-7.500 -0.3309 0.07474 0.07279 -0.0211 1.0000 0.0228
-7.250 -0.3364 0.07225 0.07033 -0.0198 1.0000 0.0230
-7.000 -0.4282 0.08094 0.07890 -0.0195 1.0000 0.0225
-6.750 -0.4262 0.07805 0.07602 -0.0191 1.0000 0.0226
-6.500 -0.4245 0.07535 0.07333 -0.0183 1.0000 0.0228
-6.250 -0.4000 0.07184 0.06980 -0.0224 0.9974 0.0235
-6.000 -0.3700 0.06730 0.06520 -0.0291 0.9940 0.0241
-5.750 -0.3266 0.06097 0.05869 -0.0402 0.9883 0.0276
-5.250 -0.2617 0.04988 0.04725 -0.0505 0.9786 0.0279
-4.750 -0.2167 0.03958 0.03665 -0.0550 0.9673 0.0290
-4.500 -0.1873 0.03675 0.03369 -0.0569 0.9634 0.0297
-4.250 -0.1742 0.02865 0.02502 -0.0545 0.9526 0.0290
-4.000 -0.1440 0.03055 0.02710 -0.0557 0.9452 0.0319
-3.750 -0.1215 0.02544 0.02152 -0.0543 0.9377 0.0333
-3.500 -0.0964 0.02601 0.02217 -0.0545 0.9264 0.0388
-3.250 -0.0716 0.02371 0.01961 -0.0534 0.9161 0.0421
-3.000 -0.0439 0.02073 0.01624 -0.0531 0.9084 0.0468
-2.750 -0.0066 0.02000 0.01549 -0.0556 0.8993 0.0502
-2.500 0.0323 0.01788 0.01288 -0.0574 0.8891 0.0579
-2.250 0.0803 0.01664 0.01159 -0.0623 0.8776 0.0609
-2.000 0.1302 0.01558 0.01018 -0.0671 0.8612 0.0712
-1.750 0.1778 0.01290 0.00691 -0.0703 0.8418 0.0574
-1.500 0.2233 0.01203 0.00580 -0.0742 0.8195 0.0573
-1.250 0.2565 0.01146 0.00503 -0.0753 0.7961 0.0572
-1.000 0.2863 0.01098 0.00439 -0.0756 0.7763 0.0574
-0.750 0.3130 0.01056 0.00385 -0.0752 0.7586 0.0577
-0.500 0.3385 0.01021 0.00342 -0.0746 0.7423 0.0586
-0.250 0.3631 0.00999 0.00314 -0.0738 0.7275 0.0603
0.000 0.3873 0.00980 0.00289 -0.0729 0.7139 0.0614
0.500 0.4341 0.00953 0.00251 -0.0706 0.6882 0.0639
0.750 0.4570 0.00942 0.00237 -0.0694 0.6758 0.0651
1.000 0.4797 0.00935 0.00226 -0.0681 0.6629 0.0662
1.250 0.5017 0.00931 0.00216 -0.0667 0.6480 0.0676
1.500 0.5234 0.00930 0.00209 -0.0652 0.6321 0.0688
1.750 0.5452 0.00921 0.00199 -0.0637 0.6170 0.0738
2.000 0.5668 0.00923 0.00196 -0.0622 0.5999 0.0776
2.250 0.5884 0.00926 0.00194 -0.0607 0.5822 0.0840
2.500 0.6100 0.00927 0.00197 -0.0593 0.5639 0.1103
2.750 0.8326 0.00839 0.00289 -0.1056 0.5161 1.0000
3.000 0.8555 0.00856 0.00299 -0.1045 0.4992 1.0000
3.250 0.8782 0.00873 0.00309 -0.1033 0.4817 1.0000
3.500 0.9001 0.00895 0.00321 -0.1020 0.4619 1.0000
3.750 0.9230 0.00914 0.00334 -0.1009 0.4463 1.0000
4.000 0.9457 0.00933 0.00349 -0.0998 0.4307 1.0000
4.250 0.9684 0.00953 0.00364 -0.0987 0.4144 1.0000
4.500 0.9907 0.00974 0.00380 -0.0975 0.3961 1.0000
4.750 1.0133 0.00995 0.00398 -0.0964 0.3811 1.0000
5.000 1.0353 0.01018 0.00417 -0.0952 0.3620 1.0000
5.250 1.0569 0.01044 0.00437 -0.0939 0.3425 1.0000
5.500 1.0781 0.01072 0.00459 -0.0926 0.3177 1.0000
5.750 1.0975 0.01113 0.00484 -0.0909 0.2833 1.0000
6.000 1.1147 0.01169 0.00519 -0.0889 0.2372 1.0000
6.250 1.1324 0.01224 0.00556 -0.0870 0.2022 1.0000
6.500 1.1507 0.01273 0.00594 -0.0852 0.1779 1.0000
6.750 1.1696 0.01317 0.00632 -0.0835 0.1604 1.0000
7.000 1.1888 0.01358 0.00670 -0.0819 0.1461 1.0000
7.250 1.2067 0.01408 0.00712 -0.0800 0.1263 1.0000
7.500 1.2237 0.01463 0.00756 -0.0780 0.1023 1.0000
7.750 1.2334 0.01567 0.00829 -0.0747 0.0567 1.0000
8.000 1.2460 0.01650 0.00910 -0.0719 0.0421 1.0000
8.250 1.2597 0.01723 0.00982 -0.0692 0.0319 1.0000
8.500 1.2726 0.01800 0.01058 -0.0664 0.0250 1.0000
8.750 1.2866 0.01864 0.01130 -0.0638 0.0226 1.0000
9.000 1.2991 0.01927 0.01197 -0.0609 0.0204 1.0000
9.250 1.3063 0.02006 0.01283 -0.0571 0.0191 1.0000
9.500 1.3100 0.02102 0.01389 -0.0526 0.0177 1.0000
9.750 1.3194 0.02169 0.01465 -0.0493 0.0169 1.0000
10.000 1.3280 0.02244 0.01550 -0.0460 0.0160 1.0000
10.250 1.3357 0.02325 0.01638 -0.0427 0.0153 1.0000
10.500 1.3396 0.02433 0.01752 -0.0389 0.0144 1.0000
10.750 1.3401 0.02565 0.01894 -0.0348 0.0140 1.0000
11.000 1.3313 0.02772 0.02115 -0.0297 0.0135 1.0000
11.250 1.3339 0.02913 0.02267 -0.0264 0.0133 1.0000
11.500 1.3393 0.03041 0.02406 -0.0238 0.0129 1.0000
11.750 1.3406 0.03212 0.02590 -0.0209 0.0128 1.0000
12.000 1.3450 0.03363 0.02752 -0.0187 0.0124 1.0000
12.250 1.3476 0.03538 0.02940 -0.0166 0.0121 1.0000
12.500 1.3498 0.03726 0.03139 -0.0147 0.0115 1.0000
12.750 1.3499 0.03953 0.03378 -0.0128 0.0114 1.0000
13.000 1.3538 0.04128 0.03562 -0.0119 0.0110 1.0000
13.250 1.3543 0.04359 0.03803 -0.0108 0.0107 1.0000
13.500 1.3512 0.04647 0.04102 -0.0096 0.0105 1.0000
13.750 1.3507 0.04904 0.04367 -0.0090 0.0102 1.0000
14.000 1.3459 0.05233 0.04709 -0.0080 0.0101 1.0000
14.250 1.3365 0.05636 0.05128 -0.0070 0.0098 1.0000
14.500 1.3373 0.05899 0.05404 -0.0071 0.0100 1.0000
14.750 1.3175 0.06475 0.06004 -0.0063 0.0097 1.0000
15.000 1.3076 0.06905 0.06452 -0.0070 0.0096 1.0000
15.250 1.2967 0.07369 0.06933 -0.0080 0.0096 1.0000
15.750 1.2732 0.08380 0.07979 -0.0113 0.0095 1.0000
16.000 1.2612 0.08924 0.08539 -0.0135 0.0095 1.0000
16.250 1.2411 0.09615 0.09247 -0.0157 0.0096 1.0000
16.500 1.2273 0.10233 0.09880 -0.0185 0.0096 1.0000
17.000 1.1922 0.11701 0.11380 -0.0260 0.0096 1.0000
17.250 1.1782 0.12448 0.12144 -0.0306 0.0094 1.0000
17.500 1.1524 0.13392 0.13101 -0.0351 0.0097 1.0000
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