GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.78 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe408-il-1000000.txt Download as CSV file: xf-goe408-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3344 0.08990 0.08843 -0.0200 1.0000 0.0136
-8.750 -0.3337 0.08679 0.08533 -0.0199 1.0000 0.0137
-8.500 -0.3271 0.08531 0.08386 -0.0192 1.0000 0.0142
-8.250 -0.3275 0.08235 0.08092 -0.0191 1.0000 0.0144
-8.000 -0.3300 0.07916 0.07774 -0.0190 1.0000 0.0145
-7.250 -0.5450 0.01793 0.01417 -0.0457 0.9796 0.0124
-7.000 -0.5206 0.01593 0.01185 -0.0455 0.9775 0.0130
-6.750 -0.4912 0.01475 0.01044 -0.0460 0.9760 0.0133
-6.500 -0.4614 0.01349 0.00896 -0.0466 0.9749 0.0149
-6.250 -0.4346 0.01296 0.00837 -0.0463 0.9717 0.0164
-6.000 -0.4076 0.01228 0.00755 -0.0461 0.9678 0.0172
-5.750 -0.3739 0.01187 0.00714 -0.0473 0.9653 0.0196
-5.500 -0.3359 0.01171 0.00697 -0.0494 0.9635 0.0219
-5.250 -0.3120 0.01151 0.00680 -0.0482 0.9562 0.0237
-5.000 -0.2758 0.01218 0.00762 -0.0498 0.9522 0.0252
-4.750 -0.2524 0.01221 0.00766 -0.0485 0.9432 0.0265
-4.500 -0.2256 0.01218 0.00760 -0.0481 0.9339 0.0277
-4.250 -0.1972 0.01189 0.00727 -0.0480 0.9250 0.0292
-4.000 -0.1616 0.01221 0.00766 -0.0496 0.9160 0.0301
-3.750 -0.1149 0.01227 0.00773 -0.0536 0.9079 0.0313
-3.500 -0.0627 0.01207 0.00746 -0.0590 0.8983 0.0335
-3.250 0.0000 0.01249 0.00781 -0.0668 0.8839 0.0351
-3.000 0.0519 0.01094 0.00599 -0.0727 0.8620 0.0376
-2.750 0.0941 0.01088 0.00578 -0.0760 0.8289 0.0389
-2.500 0.1223 0.01073 0.00544 -0.0761 0.7967 0.0401
-2.250 0.1460 0.01038 0.00492 -0.0750 0.7716 0.0410
-2.000 0.1694 0.01012 0.00450 -0.0739 0.7511 0.0420
-1.750 0.1934 0.01005 0.00433 -0.0729 0.7349 0.0431
-1.500 0.2174 0.00988 0.00405 -0.0719 0.7201 0.0437
-1.250 0.2418 0.00978 0.00387 -0.0710 0.7073 0.0441
-1.000 0.2659 0.00979 0.00381 -0.0700 0.6943 0.0445
-0.750 0.2904 0.00915 0.00308 -0.0693 0.6837 0.0450
-0.500 0.3138 0.00866 0.00253 -0.0682 0.6729 0.0457
-0.250 0.3364 0.00833 0.00217 -0.0670 0.6622 0.0468
0.000 0.3590 0.00820 0.00201 -0.0657 0.6496 0.0482
0.250 0.3821 0.00811 0.00189 -0.0645 0.6382 0.0496
0.500 0.4047 0.00805 0.00177 -0.0633 0.6252 0.0507
0.750 0.4270 0.00800 0.00167 -0.0619 0.6086 0.0518
1.000 0.4500 0.00796 0.00158 -0.0608 0.5952 0.0527
1.250 0.4731 0.00794 0.00151 -0.0596 0.5796 0.0537
1.500 0.4961 0.00795 0.00146 -0.0585 0.5618 0.0543
1.750 0.5190 0.00798 0.00142 -0.0573 0.5410 0.0552
2.000 0.5421 0.00805 0.00141 -0.0562 0.5210 0.0558
2.250 0.5657 0.00805 0.00135 -0.0552 0.5033 0.0591
2.500 0.5897 0.00810 0.00135 -0.0543 0.4873 0.0632
2.750 0.6137 0.00817 0.00139 -0.0534 0.4721 0.0662
3.000 0.6377 0.00825 0.00144 -0.0526 0.4581 0.0732
3.250 0.6616 0.00824 0.00155 -0.0517 0.4444 0.1434
3.500 0.9212 0.00778 0.00269 -0.1073 0.3821 1.0000
3.750 0.9450 0.00794 0.00280 -0.1064 0.3688 1.0000
4.000 0.9685 0.00810 0.00292 -0.1055 0.3541 1.0000
4.250 0.9918 0.00828 0.00304 -0.1045 0.3376 1.0000
4.500 1.0141 0.00853 0.00319 -0.1034 0.3139 1.0000
4.750 1.0354 0.00885 0.00338 -0.1021 0.2820 1.0000
5.000 1.0562 0.00921 0.00359 -0.1007 0.2493 1.0000
5.250 1.0740 0.00977 0.00389 -0.0987 0.2010 1.0000
5.500 1.0936 0.01019 0.00417 -0.0971 0.1727 1.0000
5.750 1.1144 0.01052 0.00442 -0.0957 0.1557 1.0000
6.000 1.1355 0.01083 0.00468 -0.0944 0.1422 1.0000
6.250 1.1562 0.01115 0.00495 -0.0930 0.1275 1.0000
6.500 1.1771 0.01146 0.00521 -0.0916 0.1162 1.0000
6.750 1.1973 0.01181 0.00550 -0.0901 0.1008 1.0000
7.250 1.2292 0.01307 0.00647 -0.0856 0.0467 1.0000
7.500 1.2487 0.01344 0.00685 -0.0840 0.0395 1.0000
7.750 1.2659 0.01395 0.00731 -0.0819 0.0284 1.0000
8.000 1.2815 0.01458 0.00785 -0.0796 0.0190 1.0000
8.250 1.2999 0.01499 0.00832 -0.0778 0.0170 1.0000
8.500 1.3160 0.01555 0.00888 -0.0755 0.0146 1.0000
8.750 1.3314 0.01614 0.00953 -0.0731 0.0132 1.0000
9.000 1.3484 0.01658 0.01003 -0.0711 0.0124 1.0000
9.250 1.3644 0.01706 0.01057 -0.0689 0.0119 1.0000
9.500 1.3788 0.01761 0.01117 -0.0664 0.0110 1.0000
9.750 1.3878 0.01830 0.01192 -0.0629 0.0104 1.0000
10.000 1.3899 0.01920 0.01293 -0.0580 0.0098 1.0000
10.250 1.3992 0.01977 0.01358 -0.0546 0.0095 1.0000
10.500 1.4094 0.02033 0.01420 -0.0515 0.0092 1.0000
10.750 1.4184 0.02098 0.01494 -0.0482 0.0089 1.0000
11.000 1.4270 0.02167 0.01570 -0.0450 0.0085 1.0000
11.250 1.4375 0.02230 0.01639 -0.0422 0.0082 1.0000
11.500 1.4454 0.02308 0.01723 -0.0392 0.0079 1.0000
11.750 1.4497 0.02409 0.01833 -0.0356 0.0078 1.0000
12.000 1.4557 0.02504 0.01934 -0.0326 0.0074 1.0000
12.250 1.4524 0.02661 0.02101 -0.0285 0.0071 1.0000
12.500 1.4332 0.02944 0.02403 -0.0231 0.0068 1.0000
12.750 1.4343 0.03106 0.02576 -0.0206 0.0068 1.0000
13.000 1.4412 0.03231 0.02708 -0.0189 0.0067 1.0000
13.250 1.4430 0.03410 0.02897 -0.0171 0.0066 1.0000
13.500 1.4417 0.03632 0.03132 -0.0153 0.0065 1.0000
13.750 1.4472 0.03801 0.03308 -0.0144 0.0064 1.0000
14.000 1.4415 0.04098 0.03620 -0.0132 0.0063 1.0000
14.250 1.4424 0.04338 0.03870 -0.0126 0.0061 1.0000
14.500 1.4326 0.04710 0.04256 -0.0119 0.0063 1.0000
14.750 1.4342 0.04967 0.04522 -0.0119 0.0060 1.0000
15.000 1.4293 0.05306 0.04873 -0.0120 0.0059 1.0000
15.250 1.4213 0.05699 0.05279 -0.0122 0.0058 1.0000
15.500 1.4091 0.06156 0.05750 -0.0126 0.0059 1.0000
15.750 1.4083 0.06486 0.06088 -0.0135 0.0056 1.0000
16.000 1.4013 0.06906 0.06519 -0.0145 0.0056 1.0000
16.250 1.3847 0.07471 0.07099 -0.0158 0.0057 1.0000
16.500 1.3826 0.07852 0.07487 -0.0172 0.0055 1.0000
16.750 1.3615 0.08514 0.08167 -0.0190 0.0057 1.0000
17.000 1.3567 0.08965 0.08626 -0.0209 0.0055 1.0000
17.250 1.3522 0.09423 0.09089 -0.0229 0.0052 1.0000
17.500 1.3323 0.10112 0.09794 -0.0253 0.0053 1.0000
17.750 1.3170 0.10752 0.10448 -0.0278 0.0054 1.0000
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