GOE 571 AIRFOIL (goe571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 571 AIRFOIL (goe571-il) Reynolds number: 1,000,000 Max Cl/Cd: 62.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe571-il-1000000.txt Download as CSV file: xf-goe571-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 571 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
------ -------- --------- --------- -------- -------- --------
-12.000 0.5147 0.09527 0.09094 -0.1702 0.5414 0.0230
-11.750 0.5228 0.09322 0.08889 -0.1708 0.5380 0.0231
-11.500 0.5313 0.09133 0.08698 -0.1715 0.5341 0.0233
-11.250 0.5393 0.08944 0.08507 -0.1720 0.5297 0.0236
-11.000 0.5465 0.08741 0.08303 -0.1727 0.5261 0.0238
-10.750 0.5527 0.08523 0.08087 -0.1733 0.5230 0.0240
-10.500 0.5589 0.08314 0.07877 -0.1739 0.5191 0.0246
-10.250 0.5639 0.08093 0.07656 -0.1745 0.5152 0.0248
-10.000 0.5414 0.07487 0.07052 -0.1777 0.5135 0.0261
-9.750 0.5435 0.07237 0.06799 -0.1783 0.5085 0.0261
-9.500 0.5432 0.06960 0.06526 -0.1783 0.5061 0.0263
-9.250 0.5474 0.06765 0.06331 -0.1783 0.5013 0.0264
-9.000 0.5529 0.06604 0.06170 -0.1782 0.4975 0.0265
-8.750 0.5547 0.06410 0.05974 -0.1781 0.4920 0.0266
-8.500 0.5546 0.06196 0.05761 -0.1781 0.4883 0.0266
-8.250 0.5557 0.06010 0.05577 -0.1780 0.4849 0.0267
-8.000 0.5495 0.05758 0.05328 -0.1779 0.4814 0.0268
-7.750 0.5438 0.05551 0.05121 -0.1775 0.4772 0.0270
-7.500 0.5205 0.05211 0.04784 -0.1783 0.4741 0.0271
-7.250 0.4879 0.04929 0.04503 -0.1751 0.4715 0.0271
-7.000 0.4497 0.04746 0.04322 -0.1678 0.4700 0.0271
-6.750 0.4253 0.04571 0.04147 -0.1618 0.4676 0.0272
-6.500 0.4039 0.04371 0.03944 -0.1562 0.4648 0.0273
-6.250 0.3861 0.04197 0.03765 -0.1504 0.4620 0.0274
-6.000 0.3702 0.04032 0.03593 -0.1445 0.4588 0.0276
-5.750 0.3580 0.03875 0.03428 -0.1390 0.4549 0.0278
-5.500 0.2926 0.03238 0.02730 -0.1240 0.4547 0.0299
-5.250 0.2628 0.02876 0.02342 -0.1151 0.4534 0.0302
-5.000 0.2719 0.02772 0.02240 -0.1122 0.4508 0.0303
-4.750 0.2766 0.02681 0.02143 -0.1084 0.4480 0.0304
-4.500 0.2866 0.02637 0.02099 -0.1055 0.4448 0.0306
-4.250 0.2905 0.02556 0.02008 -0.1014 0.4415 0.0307
-4.000 0.2987 0.02529 0.01977 -0.0980 0.4378 0.0309
-3.750 0.3056 0.02456 0.01897 -0.0944 0.4358 0.0311
-3.500 0.3161 0.02406 0.01842 -0.0914 0.4338 0.0316
-3.250 0.3236 0.02327 0.01751 -0.0876 0.4312 0.0318
-3.000 0.3138 0.02159 0.01531 -0.0799 0.4296 0.0345
-2.750 0.3254 0.02112 0.01481 -0.0771 0.4270 0.0347
-2.500 0.3378 0.02083 0.01452 -0.0745 0.4246 0.0351
-2.250 0.3470 0.02050 0.01411 -0.0711 0.4217 0.0353
-2.000 0.3585 0.02036 0.01393 -0.0682 0.4192 0.0359
-1.750 0.3720 0.01994 0.01342 -0.0655 0.4181 0.0367
-1.500 0.3812 0.01942 0.01268 -0.0618 0.4166 0.0391
-1.250 0.3964 0.01907 0.01233 -0.0596 0.4150 0.0395
-1.000 0.4111 0.01885 0.01208 -0.0573 0.4132 0.0399
-0.750 0.4253 0.01869 0.01188 -0.0549 0.4112 0.0410
-0.500 0.4357 0.01857 0.01159 -0.0517 0.4093 0.0438
-0.250 0.4486 0.01842 0.01142 -0.0492 0.4067 0.0442
0.000 0.4620 0.01837 0.01134 -0.0469 0.4044 0.0453
0.250 0.4905 0.01716 0.00967 -0.0456 0.4022 0.0299
0.500 0.5112 0.01689 0.00938 -0.0446 0.4013 0.0301
0.750 0.5310 0.01683 0.00932 -0.0434 0.4002 0.0300
1.000 0.5516 0.01671 0.00921 -0.0424 0.3987 0.0301
1.250 0.5735 0.01646 0.00900 -0.0418 0.3974 0.0308
1.500 0.5925 0.01651 0.00906 -0.0406 0.3958 0.0311
1.750 0.6112 0.01663 0.00918 -0.0395 0.3941 0.0316
2.000 0.6304 0.01678 0.00932 -0.0384 0.3925 0.0319
2.250 0.6485 0.01699 0.00952 -0.0373 0.3903 0.0323
2.500 0.6666 0.01727 0.00978 -0.0363 0.3880 0.0325
2.750 0.6878 0.01749 0.00998 -0.0359 0.3858 0.0328
3.000 0.7118 0.01764 0.01015 -0.0359 0.3851 0.0332
3.250 0.7347 0.01786 0.01039 -0.0358 0.3841 0.0334
3.500 0.7585 0.01810 0.01064 -0.0359 0.3830 0.0337
3.750 0.7829 0.01834 0.01090 -0.0362 0.3818 0.0341
4.000 0.8121 0.01854 0.01112 -0.0376 0.3802 0.0358
4.250 0.8361 0.01887 0.01146 -0.0379 0.3787 0.0360
4.500 0.8606 0.01923 0.01183 -0.0385 0.3773 0.0372
4.750 0.8859 0.01961 0.01221 -0.0393 0.3758 0.0394
5.000 0.9116 0.02006 0.01266 -0.0403 0.3739 0.0418
5.250 0.9441 0.02048 0.01318 -0.0428 0.3717 0.0813
5.500 1.2532 0.01994 0.01480 -0.1015 0.3686 1.0000
5.750 1.2688 0.02047 0.01533 -0.1004 0.3676 1.0000
6.000 1.2851 0.02097 0.01584 -0.0995 0.3665 1.0000
6.250 1.3004 0.02155 0.01643 -0.0985 0.3653 1.0000
6.500 1.3153 0.02216 0.01704 -0.0975 0.3638 1.0000
6.750 1.3306 0.02277 0.01764 -0.0966 0.3625 1.0000
7.000 1.3443 0.02348 0.01836 -0.0955 0.3613 1.0000
7.250 1.3572 0.02426 0.01912 -0.0944 0.3594 1.0000
7.500 1.3685 0.02515 0.02000 -0.0932 0.3577 1.0000
7.750 1.3800 0.02602 0.02085 -0.0921 0.3554 1.0000
8.000 1.3953 0.02667 0.02148 -0.0913 0.3537 1.0000
8.250 1.4083 0.02755 0.02240 -0.0905 0.3529 1.0000
8.500 1.4224 0.02837 0.02324 -0.0899 0.3519 1.0000
8.750 1.4357 0.02925 0.02415 -0.0892 0.3507 1.0000
9.000 1.4487 0.03017 0.02509 -0.0885 0.3494 1.0000
9.250 1.4619 0.03109 0.02603 -0.0879 0.3478 1.0000
9.500 1.4729 0.03217 0.02713 -0.0871 0.3463 1.0000
9.750 1.4840 0.03325 0.02821 -0.0864 0.3447 1.0000
10.000 1.4934 0.03446 0.02943 -0.0856 0.3429 1.0000
10.250 1.5020 0.03570 0.03065 -0.0847 0.3407 1.0000
10.500 1.5151 0.03653 0.03147 -0.0841 0.3384 1.0000
10.750 1.5253 0.03779 0.03277 -0.0835 0.3375 1.0000
11.000 1.5351 0.03906 0.03409 -0.0830 0.3363 1.0000
11.250 1.5461 0.04024 0.03531 -0.0825 0.3348 1.0000
11.500 1.5541 0.04168 0.03679 -0.0819 0.3331 1.0000
11.750 1.5635 0.04301 0.03814 -0.0814 0.3314 1.0000
12.000 1.5705 0.04452 0.03966 -0.0807 0.3293 1.0000
12.250 1.5748 0.04623 0.04138 -0.0799 0.3271 1.0000
12.500 1.5838 0.04750 0.04263 -0.0793 0.3247 1.0000
12.750 1.5866 0.04947 0.04465 -0.0786 0.3220 1.0000
13.000 1.5968 0.05074 0.04596 -0.0783 0.3213 1.0000
13.250 1.6029 0.05243 0.04770 -0.0778 0.3190 1.0000
13.500 1.6042 0.05456 0.04987 -0.0771 0.3161 1.0000
13.750 1.6106 0.05617 0.05150 -0.0766 0.3144 1.0000
14.000 1.6138 0.05806 0.05338 -0.0760 0.3118 1.0000
14.250 1.6110 0.06054 0.05589 -0.0752 0.3079 1.0000
14.500 1.6167 0.06232 0.05772 -0.0748 0.3062 1.0000
14.750 1.6195 0.06436 0.05981 -0.0744 0.3037 1.0000
15.000 1.6178 0.06683 0.06231 -0.0737 0.3006 1.0000
15.250 1.6156 0.06930 0.06477 -0.0731 0.2972 1.0000
15.500 1.6150 0.07163 0.06712 -0.0725 0.2944 1.0000
15.750 1.6154 0.07398 0.06955 -0.0721 0.2920 1.0000
16.000 1.6113 0.07679 0.07240 -0.0716 0.2883 1.0000
16.250 1.6039 0.07991 0.07552 -0.0709 0.2844 1.0000
16.500 1.6003 0.08259 0.07820 -0.0704 0.2807 1.0000
16.750 1.5971 0.08536 0.08105 -0.0700 0.2786 1.0000
17.000 1.5950 0.08801 0.08374 -0.0697 0.2751 1.0000
17.250 1.5827 0.09173 0.08748 -0.0691 0.2711 1.0000
17.500 1.5758 0.09489 0.09064 -0.0687 0.2667 1.0000
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