GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 500,000 Max Cl/Cd: 96.72 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe436-il-500000.txt Download as CSV file: xf-goe436-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3183 0.08145 0.07932 -0.0409 1.0000 0.0409
-9.250 -0.3261 0.07781 0.07572 -0.0386 1.0000 0.0414
-9.000 -0.3202 0.07599 0.07393 -0.0374 0.9994 0.0417
-8.750 -0.3000 0.07325 0.07117 -0.0393 0.9976 0.0425
-8.500 -0.2836 0.06968 0.06760 -0.0425 0.9951 0.0437
-8.250 -0.2763 0.06454 0.06246 -0.0473 0.9916 0.0456
-8.000 -0.4074 0.05047 0.04794 -0.0727 0.9831 0.0416
-7.750 -0.4303 0.02866 0.02469 -0.0814 0.9710 0.0412
-7.500 -0.4028 0.02753 0.02355 -0.0824 0.9665 0.0420
-7.250 -0.3239 0.04338 0.04059 -0.0820 0.9710 0.0465
-7.000 -0.3303 0.02790 0.02404 -0.0861 0.9601 0.0438
-6.750 -0.3013 0.02446 0.02018 -0.0880 0.9568 0.0454
-6.500 -0.2812 0.02156 0.01682 -0.0874 0.9487 0.0467
-6.250 -0.2518 0.02006 0.01497 -0.0880 0.9434 0.0477
-6.000 -0.2278 0.01787 0.01251 -0.0879 0.9365 0.0491
-5.750 -0.2002 0.01711 0.01169 -0.0880 0.9289 0.0500
-5.500 -0.1719 0.01644 0.01094 -0.0881 0.9214 0.0509
-5.250 -0.1448 0.01580 0.01020 -0.0878 0.9127 0.0519
-5.000 -0.1183 0.01514 0.00942 -0.0874 0.9031 0.0531
-4.750 -0.0900 0.01458 0.00872 -0.0873 0.8943 0.0545
-4.500 -0.0643 0.01408 0.00809 -0.0866 0.8837 0.0556
-4.250 -0.0369 0.01374 0.00762 -0.0863 0.8743 0.0563
-4.000 -0.0116 0.01253 0.00629 -0.0857 0.8645 0.0578
-3.750 0.0143 0.01205 0.00579 -0.0852 0.8545 0.0592
-3.500 0.0412 0.01177 0.00545 -0.0849 0.8450 0.0607
-3.250 0.0672 0.01152 0.00515 -0.0843 0.8339 0.0624
-3.000 0.0934 0.01123 0.00480 -0.0837 0.8231 0.0639
-2.750 0.1197 0.01098 0.00448 -0.0831 0.8122 0.0653
-2.500 0.1458 0.01082 0.00426 -0.0825 0.8005 0.0664
-2.250 0.1700 0.01022 0.00363 -0.0816 0.7887 0.0690
-2.000 0.1954 0.01000 0.00339 -0.0810 0.7758 0.0713
-1.750 0.2209 0.00984 0.00319 -0.0803 0.7612 0.0737
-1.500 0.2461 0.00969 0.00299 -0.0795 0.7447 0.0759
-1.250 0.2714 0.00959 0.00281 -0.0787 0.7259 0.0779
-1.000 0.2955 0.00936 0.00252 -0.0778 0.7053 0.0814
-0.750 0.3199 0.00927 0.00235 -0.0769 0.6836 0.0855
-0.500 0.3444 0.00925 0.00224 -0.0760 0.6609 0.0896
-0.250 0.3685 0.00925 0.00212 -0.0750 0.6393 0.0942
0.000 0.3927 0.00922 0.00205 -0.0741 0.6181 0.1030
0.250 0.4170 0.00919 0.00200 -0.0733 0.5966 0.1194
0.500 0.4389 0.00888 0.00198 -0.0722 0.5745 0.2375
0.750 0.4502 0.00772 0.00205 -0.0692 0.5521 0.6646
1.000 0.5111 0.00737 0.00230 -0.0757 0.5126 0.9682
1.250 0.5710 0.00773 0.00239 -0.0826 0.4759 0.9955
1.500 0.6077 0.00795 0.00245 -0.0846 0.4541 1.0000
1.750 0.6289 0.00814 0.00253 -0.0832 0.4405 1.0000
2.000 0.6503 0.00834 0.00262 -0.0819 0.4295 1.0000
2.250 0.6729 0.00849 0.00271 -0.0807 0.4203 1.0000
2.500 0.6950 0.00868 0.00282 -0.0795 0.4124 1.0000
2.750 0.7180 0.00882 0.00293 -0.0785 0.4048 1.0000
3.000 0.7401 0.00903 0.00305 -0.0773 0.3966 1.0000
3.250 0.7636 0.00916 0.00315 -0.0763 0.3887 1.0000
3.500 0.7858 0.00938 0.00329 -0.0751 0.3818 1.0000
3.750 0.8098 0.00948 0.00341 -0.0743 0.3752 1.0000
4.000 0.8327 0.00966 0.00353 -0.0732 0.3684 1.0000
4.250 0.8561 0.00982 0.00367 -0.0723 0.3622 1.0000
4.500 0.8797 0.00995 0.00379 -0.0714 0.3554 1.0000
4.750 0.9023 0.01016 0.00395 -0.0703 0.3487 1.0000
5.000 0.9264 0.01027 0.00408 -0.0695 0.3427 1.0000
5.250 0.9496 0.01044 0.00424 -0.0685 0.3374 1.0000
5.500 0.9726 0.01064 0.00442 -0.0676 0.3324 1.0000
5.750 0.9967 0.01076 0.00458 -0.0668 0.3271 1.0000
6.000 1.0198 0.01095 0.00475 -0.0658 0.3215 1.0000
6.250 1.0429 0.01114 0.00495 -0.0649 0.3161 1.0000
6.500 1.0668 0.01128 0.00513 -0.0641 0.3104 1.0000
6.750 1.0892 0.01149 0.00531 -0.0631 0.3038 1.0000
7.000 1.1129 0.01164 0.00551 -0.0623 0.2967 1.0000
7.250 1.1354 0.01185 0.00571 -0.0613 0.2895 1.0000
7.500 1.1585 0.01203 0.00592 -0.0604 0.2827 1.0000
7.750 1.1807 0.01224 0.00614 -0.0594 0.2743 1.0000
8.000 1.2032 0.01244 0.00637 -0.0584 0.2647 1.0000
8.250 1.2245 0.01270 0.00661 -0.0573 0.2519 1.0000
8.500 1.2446 0.01302 0.00688 -0.0560 0.2340 1.0000
8.750 1.2622 0.01349 0.00723 -0.0543 0.2092 1.0000
9.000 1.2751 0.01424 0.00777 -0.0519 0.1731 1.0000
9.250 1.2858 0.01510 0.00843 -0.0492 0.1420 1.0000
9.500 1.2950 0.01592 0.00911 -0.0462 0.1179 1.0000
9.750 1.3045 0.01670 0.00978 -0.0433 0.0950 1.0000
10.000 1.3116 0.01762 0.01055 -0.0401 0.0739 1.0000
10.250 1.3224 0.01835 0.01125 -0.0376 0.0672 1.0000
10.500 1.3329 0.01911 0.01201 -0.0351 0.0632 1.0000
10.750 1.3430 0.01990 0.01283 -0.0327 0.0600 1.0000
11.000 1.3559 0.02054 0.01355 -0.0307 0.0582 1.0000
11.250 1.3663 0.02134 0.01443 -0.0285 0.0559 1.0000
11.500 1.3737 0.02234 0.01548 -0.0261 0.0536 1.0000
11.750 1.3759 0.02370 0.01688 -0.0233 0.0508 1.0000
12.000 1.3900 0.02439 0.01766 -0.0220 0.0491 1.0000
12.250 1.4007 0.02531 0.01866 -0.0204 0.0464 1.0000
12.500 1.4054 0.02668 0.02007 -0.0185 0.0436 1.0000
12.750 1.4138 0.02787 0.02134 -0.0170 0.0407 1.0000
13.000 1.4241 0.02897 0.02247 -0.0158 0.0369 1.0000
13.250 1.4311 0.03037 0.02391 -0.0145 0.0328 1.0000
13.500 1.4344 0.03215 0.02569 -0.0132 0.0296 1.0000
13.750 1.4391 0.03389 0.02749 -0.0121 0.0266 1.0000
14.000 1.4398 0.03609 0.02973 -0.0111 0.0250 1.0000
14.250 1.4378 0.03868 0.03241 -0.0104 0.0236 1.0000
14.500 1.4374 0.04126 0.03508 -0.0099 0.0225 1.0000
14.750 1.4342 0.04429 0.03820 -0.0097 0.0217 1.0000
15.000 1.4270 0.04793 0.04192 -0.0099 0.0208 1.0000
15.250 1.4165 0.05217 0.04626 -0.0104 0.0203 1.0000
15.500 1.4080 0.05631 0.05052 -0.0111 0.0199 1.0000
15.750 1.4006 0.06046 0.05479 -0.0120 0.0195 1.0000
16.000 1.3934 0.06471 0.05915 -0.0130 0.0191 1.0000
16.250 1.3844 0.06928 0.06384 -0.0143 0.0189 1.0000
16.500 1.3749 0.07402 0.06868 -0.0156 0.0185 1.0000
16.750 1.3658 0.07878 0.07354 -0.0171 0.0181 1.0000
17.000 1.3565 0.08359 0.07845 -0.0186 0.0178 1.0000
17.250 1.3470 0.08848 0.08342 -0.0202 0.0175 1.0000
17.500 1.3352 0.09377 0.08878 -0.0221 0.0172 1.0000
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Polar data table (+)
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