GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 500,000 Max Cl/Cd: 77.57 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe564-il-500000-n5.txt Download as CSV file: xf-goe564-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 564 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6937 0.06821 0.06593 -0.0462 1.0000 0.0094
-11.000 -0.8854 0.03237 0.02923 -0.0599 1.0000 0.0078
-10.750 -0.8749 0.02880 0.02530 -0.0603 0.9988 0.0081
-10.500 -0.8535 0.02603 0.02217 -0.0617 0.9965 0.0084
-10.250 -0.8293 0.02393 0.01977 -0.0629 0.9946 0.0086
-10.000 -0.8064 0.02210 0.01770 -0.0634 0.9921 0.0092
-9.750 -0.7803 0.02087 0.01629 -0.0641 0.9899 0.0097
-9.500 -0.7526 0.01988 0.01515 -0.0649 0.9880 0.0103
-9.250 -0.7240 0.01896 0.01406 -0.0657 0.9865 0.0111
-9.000 -0.6967 0.01804 0.01294 -0.0662 0.9847 0.0118
-8.750 -0.6715 0.01713 0.01192 -0.0662 0.9817 0.0127
-8.500 -0.6428 0.01663 0.01136 -0.0668 0.9796 0.0138
-8.250 -0.6128 0.01610 0.01075 -0.0675 0.9778 0.0149
-8.000 -0.5814 0.01559 0.01009 -0.0685 0.9763 0.0162
-7.750 -0.5529 0.01512 0.00958 -0.0689 0.9734 0.0176
-7.500 -0.5239 0.01491 0.00935 -0.0693 0.9699 0.0190
-7.250 -0.4932 0.01455 0.00891 -0.0701 0.9676 0.0206
-7.000 -0.4616 0.01417 0.00843 -0.0710 0.9658 0.0219
-6.750 -0.4291 0.01384 0.00799 -0.0721 0.9645 0.0231
-6.500 -0.4041 0.01320 0.00729 -0.0717 0.9602 0.0247
-6.250 -0.3754 0.01284 0.00690 -0.0720 0.9569 0.0261
-6.000 -0.3442 0.01251 0.00651 -0.0728 0.9544 0.0277
-5.500 -0.2802 0.01182 0.00566 -0.0747 0.9500 0.0302
-5.250 -0.2547 0.01156 0.00535 -0.0741 0.9445 0.0308
-5.000 -0.2256 0.01103 0.00475 -0.0745 0.9407 0.0320
-4.750 -0.1940 0.01055 0.00423 -0.0753 0.9377 0.0336
-4.500 -0.1660 0.01022 0.00385 -0.0753 0.9324 0.0346
-4.250 -0.1371 0.00992 0.00351 -0.0755 0.9271 0.0357
-4.000 -0.1056 0.00964 0.00319 -0.0762 0.9231 0.0371
-3.750 -0.0770 0.00941 0.00293 -0.0763 0.9177 0.0389
-3.500 -0.0482 0.00921 0.00268 -0.0765 0.9120 0.0406
-3.250 -0.0175 0.00898 0.00243 -0.0770 0.9075 0.0443
-3.000 0.0097 0.00877 0.00225 -0.0768 0.9011 0.0515
-2.750 0.0384 0.00854 0.00211 -0.0770 0.8951 0.0710
-2.500 0.0670 0.00840 0.00200 -0.0771 0.8890 0.0853
-2.250 0.0951 0.00830 0.00189 -0.0770 0.8821 0.0938
-2.000 0.1234 0.00820 0.00179 -0.0770 0.8738 0.1022
-1.750 0.1517 0.00812 0.00167 -0.0769 0.8621 0.1094
-1.500 0.1789 0.00805 0.00157 -0.0766 0.8471 0.1175
-1.250 0.2056 0.00799 0.00148 -0.0762 0.8322 0.1255
-1.000 0.2320 0.00795 0.00140 -0.0757 0.8172 0.1354
-0.750 0.2580 0.00788 0.00135 -0.0752 0.8024 0.1515
-0.250 0.3071 0.00764 0.00124 -0.0737 0.7577 0.2325
0.000 0.3290 0.00748 0.00119 -0.0724 0.7170 0.3204
0.250 0.3479 0.00734 0.00117 -0.0705 0.6654 0.4401
0.500 0.3670 0.00713 0.00122 -0.0687 0.6330 0.5779
0.750 0.3855 0.00685 0.00129 -0.0667 0.6123 0.7189
1.000 0.4048 0.00659 0.00140 -0.0645 0.5918 0.8582
1.250 0.4739 0.00679 0.00158 -0.0734 0.5491 0.9755
1.500 0.5211 0.00711 0.00167 -0.0778 0.4967 0.9975
1.750 0.5473 0.00743 0.00176 -0.0776 0.4459 1.0000
2.000 0.5668 0.00777 0.00187 -0.0759 0.3989 1.0000
2.250 0.5868 0.00811 0.00201 -0.0743 0.3539 1.0000
2.500 0.6071 0.00845 0.00216 -0.0728 0.3107 1.0000
2.750 0.6279 0.00879 0.00232 -0.0714 0.2738 1.0000
3.000 0.6496 0.00906 0.00247 -0.0702 0.2487 1.0000
3.250 0.6717 0.00933 0.00264 -0.0690 0.2290 1.0000
3.500 0.6941 0.00957 0.00281 -0.0679 0.2129 1.0000
4.000 0.7397 0.01001 0.00315 -0.0658 0.1882 1.0000
4.250 0.7631 0.01020 0.00332 -0.0649 0.1809 1.0000
4.500 0.7864 0.01040 0.00351 -0.0640 0.1735 1.0000
4.750 0.8098 0.01060 0.00370 -0.0631 0.1660 1.0000
5.000 0.8331 0.01082 0.00391 -0.0622 0.1578 1.0000
5.250 0.8564 0.01104 0.00413 -0.0612 0.1472 1.0000
5.500 0.8789 0.01133 0.00435 -0.0602 0.1297 1.0000
5.750 0.8995 0.01179 0.00464 -0.0590 0.0998 1.0000
6.000 0.9210 0.01218 0.00496 -0.0578 0.0875 1.0000
6.250 0.9430 0.01253 0.00531 -0.0567 0.0804 1.0000
6.500 0.9656 0.01283 0.00563 -0.0558 0.0745 1.0000
6.750 0.9874 0.01320 0.00598 -0.0547 0.0635 1.0000
7.000 1.0069 0.01378 0.00640 -0.0533 0.0389 1.0000
7.250 1.0274 0.01429 0.00688 -0.0520 0.0308 1.0000
7.500 1.0479 0.01479 0.00740 -0.0507 0.0261 1.0000
7.750 1.0693 0.01519 0.00786 -0.0496 0.0229 1.0000
8.000 1.0898 0.01567 0.00836 -0.0484 0.0193 1.0000
8.250 1.1100 0.01619 0.00891 -0.0471 0.0168 1.0000
8.500 1.1303 0.01666 0.00943 -0.0458 0.0151 1.0000
8.750 1.1496 0.01722 0.01001 -0.0444 0.0135 1.0000
9.000 1.1673 0.01792 0.01077 -0.0428 0.0122 1.0000
9.250 1.1865 0.01843 0.01136 -0.0414 0.0113 1.0000
9.500 1.2046 0.01901 0.01201 -0.0399 0.0106 1.0000
9.750 1.2218 0.01964 0.01270 -0.0382 0.0098 1.0000
10.000 1.2371 0.02034 0.01345 -0.0363 0.0093 1.0000
10.250 1.2480 0.02125 0.01445 -0.0336 0.0087 1.0000
10.500 1.2605 0.02200 0.01529 -0.0312 0.0084 1.0000
10.750 1.2726 0.02278 0.01619 -0.0288 0.0081 1.0000
11.000 1.2842 0.02359 0.01710 -0.0265 0.0078 1.0000
11.250 1.2958 0.02440 0.01800 -0.0242 0.0074 1.0000
11.500 1.3060 0.02531 0.01900 -0.0219 0.0071 1.0000
11.750 1.3176 0.02613 0.01989 -0.0199 0.0068 1.0000
12.000 1.3247 0.02727 0.02112 -0.0175 0.0065 1.0000
12.250 1.3287 0.02866 0.02260 -0.0149 0.0063 1.0000
12.500 1.3303 0.03026 0.02432 -0.0122 0.0061 1.0000
12.750 1.3346 0.03172 0.02592 -0.0101 0.0060 1.0000
13.000 1.3372 0.03338 0.02770 -0.0081 0.0059 1.0000
13.250 1.3390 0.03519 0.02966 -0.0062 0.0058 1.0000
13.500 1.3399 0.03718 0.03180 -0.0046 0.0056 1.0000
13.750 1.3385 0.03947 0.03424 -0.0032 0.0056 1.0000
14.000 1.3352 0.04211 0.03703 -0.0022 0.0055 1.0000
14.250 1.3323 0.04488 0.03994 -0.0015 0.0054 1.0000
14.500 1.3269 0.04813 0.04334 -0.0013 0.0053 1.0000
14.750 1.3203 0.05177 0.04713 -0.0017 0.0052 1.0000
15.000 1.3143 0.05563 0.05113 -0.0026 0.0051 1.0000
15.250 1.3018 0.06065 0.05632 -0.0041 0.0051 1.0000
15.500 1.2908 0.06579 0.06161 -0.0061 0.0051 1.0000
15.750 1.2775 0.07166 0.06765 -0.0088 0.0050 1.0000
16.000 1.2656 0.07769 0.07382 -0.0119 0.0049 1.0000
16.250 1.2465 0.08532 0.08162 -0.0158 0.0050 1.0000
16.500 1.2298 0.09288 0.08933 -0.0199 0.0049 1.0000
16.750 1.2114 0.10098 0.09757 -0.0243 0.0049 1.0000
17.000 1.1897 0.10988 0.10663 -0.0291 0.0050 1.0000
17.250 1.1709 0.11840 0.11527 -0.0338 0.0050 1.0000
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