GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.23 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe479-il-1000000-n5.txt Download as CSV file: xf-goe479-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.1209 0.03429 0.03127 -0.1025 1.0000 0.0155
-15.750 -1.1435 0.03139 0.02822 -0.1007 1.0000 0.0156
-15.500 -1.1600 0.02984 0.02658 -0.0961 1.0000 0.0157
-15.250 -1.1623 0.02851 0.02517 -0.0930 1.0000 0.0159
-15.000 -1.1577 0.02735 0.02393 -0.0907 0.9998 0.0162
-14.750 -1.1345 0.02615 0.02265 -0.0916 0.9983 0.0165
-14.500 -1.1103 0.02510 0.02151 -0.0925 0.9965 0.0170
-14.250 -1.0846 0.02410 0.02043 -0.0935 0.9945 0.0174
-14.000 -1.0596 0.02318 0.01940 -0.0941 0.9921 0.0178
-13.750 -1.0338 0.02226 0.01837 -0.0948 0.9892 0.0182
-13.500 -1.0064 0.02140 0.01740 -0.0957 0.9867 0.0185
-13.250 -0.9780 0.02054 0.01648 -0.0968 0.9847 0.0189
-13.000 -0.9505 0.01988 0.01577 -0.0974 0.9821 0.0193
-12.750 -0.9245 0.01927 0.01511 -0.0976 0.9783 0.0196
-12.500 -0.8956 0.01872 0.01449 -0.0983 0.9756 0.0200
-12.250 -0.8654 0.01819 0.01390 -0.0993 0.9739 0.0205
-12.000 -0.8350 0.01761 0.01324 -0.1003 0.9725 0.0209
-11.750 -0.8094 0.01711 0.01267 -0.1002 0.9686 0.0213
-11.500 -0.7816 0.01661 0.01208 -0.1005 0.9651 0.0216
-11.250 -0.7519 0.01610 0.01148 -0.1013 0.9621 0.0219
-11.000 -0.7223 0.01544 0.01077 -0.1021 0.9593 0.0224
-10.750 -0.6967 0.01505 0.01034 -0.1019 0.9542 0.0228
-10.500 -0.6688 0.01467 0.00992 -0.1021 0.9496 0.0232
-10.250 -0.6397 0.01429 0.00948 -0.1025 0.9456 0.0236
-10.000 -0.6134 0.01395 0.00910 -0.1023 0.9401 0.0240
-9.750 -0.5868 0.01361 0.00869 -0.1021 0.9338 0.0245
-9.500 -0.5594 0.01325 0.00825 -0.1021 0.9281 0.0249
-9.250 -0.5345 0.01290 0.00783 -0.1015 0.9212 0.0252
-9.000 -0.5079 0.01262 0.00748 -0.1012 0.9146 0.0255
-8.750 -0.4820 0.01231 0.00711 -0.1008 0.9081 0.0258
-8.500 -0.4576 0.01186 0.00659 -0.1002 0.9001 0.0262
-8.250 -0.4322 0.01153 0.00620 -0.0997 0.8923 0.0267
-8.000 -0.4066 0.01125 0.00588 -0.0992 0.8830 0.0271
-7.750 -0.3807 0.01101 0.00559 -0.0987 0.8739 0.0275
-7.500 -0.3548 0.01081 0.00532 -0.0982 0.8633 0.0280
-7.250 -0.3294 0.01058 0.00502 -0.0976 0.8501 0.0284
-7.000 -0.3042 0.01039 0.00473 -0.0969 0.8338 0.0288
-6.750 -0.2794 0.01022 0.00445 -0.0961 0.8140 0.0292
-6.500 -0.2547 0.01007 0.00420 -0.0953 0.7919 0.0296
-6.250 -0.2302 0.00996 0.00396 -0.0945 0.7688 0.0299
-6.000 -0.2060 0.00982 0.00370 -0.0936 0.7465 0.0303
-5.750 -0.1812 0.00965 0.00345 -0.0928 0.7290 0.0311
-5.500 -0.1556 0.00953 0.00327 -0.0923 0.7151 0.0318
-5.250 -0.1296 0.00940 0.00309 -0.0918 0.7030 0.0324
-5.000 -0.1034 0.00929 0.00292 -0.0913 0.6923 0.0331
-4.750 -0.0771 0.00918 0.00276 -0.0908 0.6828 0.0338
-4.500 -0.0505 0.00907 0.00260 -0.0904 0.6744 0.0344
-4.250 -0.0240 0.00898 0.00246 -0.0900 0.6652 0.0350
-4.000 0.0025 0.00884 0.00230 -0.0896 0.6574 0.0363
-3.750 0.0291 0.00875 0.00218 -0.0892 0.6492 0.0375
-3.500 0.0560 0.00866 0.00207 -0.0888 0.6428 0.0390
-3.250 0.0830 0.00859 0.00197 -0.0885 0.6360 0.0404
-3.000 0.1095 0.00851 0.00187 -0.0881 0.6289 0.0426
-2.750 0.1367 0.00842 0.00178 -0.0878 0.6222 0.0449
-2.500 0.1636 0.00837 0.00171 -0.0875 0.6151 0.0471
-2.250 0.1905 0.00829 0.00163 -0.0871 0.6093 0.0504
-2.000 0.2177 0.00823 0.00156 -0.0868 0.6030 0.0539
-1.750 0.2445 0.00818 0.00150 -0.0865 0.5963 0.0584
-1.000 0.3248 0.00796 0.00137 -0.0854 0.5750 0.0929
-0.750 0.3514 0.00788 0.00134 -0.0851 0.5670 0.1152
-0.500 0.3778 0.00783 0.00133 -0.0847 0.5580 0.1363
-0.250 0.4038 0.00781 0.00133 -0.0842 0.5453 0.1565
0.000 0.4295 0.00781 0.00133 -0.0837 0.5286 0.1810
0.250 0.4547 0.00780 0.00134 -0.0831 0.5084 0.2128
0.500 0.4798 0.00782 0.00137 -0.0825 0.4881 0.2467
0.750 0.5050 0.00782 0.00142 -0.0819 0.4723 0.2840
1.000 0.5296 0.00772 0.00146 -0.0813 0.4608 0.3550
1.250 0.5531 0.00753 0.00153 -0.0805 0.4491 0.4671
1.500 0.5755 0.00727 0.00161 -0.0794 0.4390 0.6027
1.750 0.5971 0.00709 0.00170 -0.0780 0.4300 0.7120
2.000 0.6191 0.00694 0.00178 -0.0767 0.4228 0.7960
2.250 0.6592 0.00679 0.00196 -0.0791 0.4107 0.9471
2.500 0.7151 0.00700 0.00209 -0.0854 0.3948 0.9767
2.750 0.7527 0.00719 0.00220 -0.0875 0.3813 0.9901
3.000 0.7921 0.00734 0.00230 -0.0901 0.3702 0.9988
3.250 0.8213 0.00750 0.00240 -0.0904 0.3582 1.0000
3.500 0.8439 0.00767 0.00250 -0.0893 0.3444 1.0000
3.750 0.8664 0.00786 0.00262 -0.0881 0.3301 1.0000
4.000 0.8880 0.00809 0.00275 -0.0869 0.3094 1.0000
4.250 0.9080 0.00843 0.00294 -0.0853 0.2808 1.0000
4.500 0.9276 0.00879 0.00315 -0.0837 0.2544 1.0000
4.750 0.9484 0.00909 0.00335 -0.0823 0.2348 1.0000
5.000 0.9692 0.00940 0.00356 -0.0809 0.2166 1.0000
5.250 0.9902 0.00968 0.00377 -0.0796 0.2017 1.0000
5.500 1.0113 0.00997 0.00399 -0.0783 0.1879 1.0000
5.750 1.0315 0.01030 0.00422 -0.0769 0.1709 1.0000
6.000 1.0503 0.01070 0.00450 -0.0752 0.1502 1.0000
6.250 1.0679 0.01118 0.00484 -0.0733 0.1248 1.0000
6.500 1.0766 0.01214 0.00548 -0.0700 0.0691 1.0000
6.750 1.0914 0.01275 0.00596 -0.0677 0.0469 1.0000
7.000 1.1105 0.01310 0.00628 -0.0661 0.0416 1.0000
7.250 1.1304 0.01339 0.00657 -0.0647 0.0392 1.0000
7.500 1.1498 0.01370 0.00687 -0.0631 0.0373 1.0000
7.750 1.1674 0.01401 0.00718 -0.0613 0.0360 1.0000
8.000 1.1838 0.01433 0.00751 -0.0592 0.0345 1.0000
8.250 1.2011 0.01463 0.00783 -0.0573 0.0340 1.0000
8.500 1.2185 0.01495 0.00817 -0.0555 0.0335 1.0000
8.750 1.2355 0.01528 0.00853 -0.0537 0.0330 1.0000
9.000 1.2525 0.01565 0.00891 -0.0519 0.0324 1.0000
9.250 1.2689 0.01604 0.00933 -0.0501 0.0318 1.0000
9.500 1.2852 0.01646 0.00976 -0.0483 0.0311 1.0000
9.750 1.3008 0.01693 0.01025 -0.0465 0.0305 1.0000
10.000 1.3157 0.01744 0.01078 -0.0446 0.0299 1.0000
10.250 1.3298 0.01802 0.01139 -0.0427 0.0294 1.0000
10.500 1.3436 0.01862 0.01204 -0.0409 0.0290 1.0000
10.750 1.3589 0.01916 0.01261 -0.0393 0.0287 1.0000
11.000 1.3736 0.01974 0.01324 -0.0377 0.0285 1.0000
11.250 1.3880 0.02037 0.01391 -0.0361 0.0281 1.0000
11.500 1.4016 0.02106 0.01464 -0.0346 0.0278 1.0000
11.750 1.4152 0.02177 0.01540 -0.0331 0.0274 1.0000
12.000 1.4281 0.02256 0.01623 -0.0316 0.0269 1.0000
12.250 1.4404 0.02341 0.01712 -0.0302 0.0266 1.0000
12.500 1.4523 0.02433 0.01808 -0.0288 0.0261 1.0000
12.750 1.4631 0.02535 0.01913 -0.0275 0.0255 1.0000
13.000 1.4724 0.02653 0.02036 -0.0261 0.0251 1.0000
13.250 1.4803 0.02788 0.02176 -0.0248 0.0248 1.0000
13.500 1.4864 0.02942 0.02337 -0.0235 0.0243 1.0000
13.750 1.4966 0.03068 0.02469 -0.0226 0.0242 1.0000
14.000 1.5059 0.03206 0.02614 -0.0217 0.0239 1.0000
14.250 1.5150 0.03350 0.02764 -0.0210 0.0236 1.0000
14.500 1.5231 0.03507 0.02927 -0.0203 0.0233 1.0000
14.750 1.5302 0.03676 0.03103 -0.0197 0.0229 1.0000
15.000 1.5373 0.03851 0.03285 -0.0191 0.0225 1.0000
15.250 1.5448 0.04027 0.03465 -0.0187 0.0220 1.0000
15.500 1.5499 0.04230 0.03673 -0.0183 0.0216 1.0000
15.750 1.5531 0.04456 0.03907 -0.0180 0.0214 1.0000
16.000 1.5559 0.04693 0.04149 -0.0178 0.0210 1.0000
16.250 1.5559 0.04966 0.04429 -0.0176 0.0207 1.0000
16.500 1.5550 0.05253 0.04724 -0.0176 0.0204 1.0000
16.750 1.5571 0.05511 0.04990 -0.0176 0.0201 1.0000
17.000 1.5574 0.05795 0.05282 -0.0178 0.0199 1.0000
17.250 1.5564 0.06101 0.05597 -0.0180 0.0196 1.0000
17.500 1.5569 0.06391 0.05894 -0.0183 0.0191 1.0000
17.750 1.5553 0.06712 0.06223 -0.0188 0.0187 1.0000
18.000 1.5510 0.07075 0.06595 -0.0194 0.0185 1.0000
18.250 1.5483 0.07422 0.06949 -0.0200 0.0181 1.0000
18.500 1.5436 0.07799 0.07334 -0.0208 0.0177 1.0000
18.750 1.5387 0.08182 0.07723 -0.0217 0.0174 1.0000
19.000 1.5312 0.08609 0.08158 -0.0227 0.0171 1.0000
19.250 1.5234 0.09047 0.08605 -0.0239 0.0169 1.0000
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