GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.27 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe548-il-1000000-n5.txt Download as CSV file: xf-goe548-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 548 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6893 0.10884 0.10695 -0.0435 1.0000 0.0033
-15.250 -0.7441 0.09413 0.09210 -0.0500 1.0000 0.0031
-15.000 -0.7945 0.08096 0.07883 -0.0562 1.0000 0.0030
-14.750 -0.8704 0.06305 0.06073 -0.0660 1.0000 0.0028
-14.500 -0.8961 0.05452 0.05206 -0.0713 1.0000 0.0029
-14.250 -0.9227 0.04654 0.04391 -0.0767 1.0000 0.0028
-14.000 -0.9503 0.03997 0.03715 -0.0803 1.0000 0.0028
-13.750 -0.9562 0.03664 0.03369 -0.0817 0.9997 0.0029
-13.500 -0.9534 0.03294 0.02979 -0.0853 0.9978 0.0029
-13.250 -0.9472 0.03033 0.02701 -0.0871 0.9944 0.0029
-13.000 -0.9399 0.02833 0.02485 -0.0873 0.9901 0.0030
-12.500 -0.9181 0.02546 0.02170 -0.0862 0.9785 0.0030
-12.250 -0.9143 0.02334 0.01937 -0.0845 0.9694 0.0032
-11.750 -0.8750 0.02077 0.01650 -0.0848 0.9603 0.0033
-11.500 -0.8503 0.01976 0.01539 -0.0855 0.9565 0.0035
-11.250 -0.8217 0.01895 0.01450 -0.0868 0.9540 0.0037
-11.000 -0.7924 0.01802 0.01344 -0.0883 0.9514 0.0038
-10.750 -0.7644 0.01718 0.01250 -0.0894 0.9472 0.0039
-10.500 -0.7350 0.01644 0.01163 -0.0906 0.9432 0.0041
-10.250 -0.7055 0.01566 0.01073 -0.0919 0.9391 0.0043
-10.000 -0.6790 0.01508 0.01005 -0.0923 0.9347 0.0045
-9.750 -0.6537 0.01454 0.00941 -0.0924 0.9306 0.0046
-9.500 -0.6282 0.01403 0.00881 -0.0925 0.9269 0.0047
-9.250 -0.6051 0.01339 0.00807 -0.0921 0.9233 0.0051
-9.000 -0.5830 0.01292 0.00756 -0.0914 0.9199 0.0056
-8.750 -0.5595 0.01255 0.00713 -0.0908 0.9167 0.0059
-8.500 -0.5357 0.01214 0.00663 -0.0904 0.9133 0.0062
-8.250 -0.5107 0.01183 0.00625 -0.0901 0.9103 0.0067
-8.000 -0.4872 0.01153 0.00589 -0.0894 0.9074 0.0070
-7.750 -0.4654 0.01110 0.00541 -0.0884 0.9041 0.0078
-7.500 -0.4420 0.01077 0.00504 -0.0878 0.9010 0.0086
-7.250 -0.4174 0.01049 0.00471 -0.0873 0.8981 0.0095
-7.000 -0.3919 0.01025 0.00441 -0.0870 0.8955 0.0103
-6.750 -0.3688 0.00995 0.00410 -0.0863 0.8928 0.0130
-6.500 -0.3453 0.00968 0.00384 -0.0855 0.8894 0.0161
-6.250 -0.3209 0.00944 0.00361 -0.0850 0.8861 0.0231
-6.000 -0.2954 0.00924 0.00343 -0.0847 0.8831 0.0281
-5.750 -0.2695 0.00910 0.00327 -0.0844 0.8802 0.0318
-5.500 -0.2442 0.00898 0.00313 -0.0840 0.8769 0.0331
-5.250 -0.2194 0.00878 0.00293 -0.0834 0.8732 0.0361
-5.000 -0.1938 0.00863 0.00275 -0.0831 0.8688 0.0389
-4.750 -0.1689 0.00849 0.00260 -0.0826 0.8628 0.0411
-4.500 -0.1435 0.00840 0.00246 -0.0821 0.8551 0.0430
-4.250 -0.1188 0.00827 0.00230 -0.0815 0.8459 0.0442
-4.000 -0.0943 0.00812 0.00210 -0.0808 0.8344 0.0470
-3.750 -0.0703 0.00799 0.00193 -0.0800 0.8181 0.0502
-3.500 -0.0475 0.00792 0.00177 -0.0789 0.7912 0.0534
-3.250 -0.0258 0.00792 0.00163 -0.0775 0.7643 0.0564
-3.000 -0.0033 0.00786 0.00152 -0.0764 0.7477 0.0686
-2.750 0.0181 0.00760 0.00139 -0.0753 0.7366 0.1195
-2.500 0.0404 0.00738 0.00129 -0.0743 0.7279 0.1699
-2.250 0.0646 0.00723 0.00122 -0.0736 0.7213 0.2023
-2.000 0.0882 0.00715 0.00117 -0.0728 0.7124 0.2294
-1.750 0.1121 0.00701 0.00112 -0.0721 0.7034 0.2638
-1.500 0.1356 0.00687 0.00108 -0.0713 0.6962 0.3058
-1.250 0.1592 0.00670 0.00105 -0.0706 0.6882 0.3574
-1.000 0.1832 0.00659 0.00102 -0.0699 0.6818 0.3950
-0.750 0.2077 0.00648 0.00101 -0.0693 0.6737 0.4318
-0.500 0.2315 0.00637 0.00100 -0.0685 0.6661 0.4707
-0.250 0.2555 0.00625 0.00100 -0.0678 0.6584 0.5131
0.000 0.2786 0.00617 0.00101 -0.0668 0.6460 0.5547
0.250 0.3009 0.00610 0.00102 -0.0657 0.6307 0.5975
0.500 0.3239 0.00610 0.00103 -0.0647 0.6129 0.6198
0.750 0.3458 0.00616 0.00105 -0.0634 0.5866 0.6385
1.000 0.3666 0.00625 0.00109 -0.0620 0.5589 0.6605
1.250 0.3870 0.00632 0.00116 -0.0605 0.5346 0.6920
1.500 0.4059 0.00638 0.00125 -0.0586 0.5085 0.7342
1.750 0.4261 0.00640 0.00134 -0.0570 0.4892 0.7758
2.000 0.4464 0.00644 0.00143 -0.0554 0.4705 0.8145
2.250 0.4673 0.00653 0.00153 -0.0539 0.4503 0.8455
2.500 0.4897 0.00661 0.00164 -0.0528 0.4302 0.8717
2.750 0.5135 0.00677 0.00177 -0.0520 0.4045 0.8969
3.000 0.5415 0.00710 0.00197 -0.0524 0.3565 0.9222
3.250 0.5712 0.00832 0.00253 -0.0538 0.2016 0.9455
3.500 0.6116 0.00883 0.00284 -0.0571 0.1549 0.9570
3.750 0.6476 0.00937 0.00313 -0.0595 0.1032 0.9658
4.250 0.7115 0.00996 0.00361 -0.0619 0.0764 0.9818
4.500 0.7426 0.01025 0.00385 -0.0629 0.0662 0.9891
4.750 0.7697 0.01092 0.00430 -0.0633 0.0171 0.9955
5.000 0.8023 0.01122 0.00459 -0.0646 0.0131 0.9987
5.250 0.8312 0.01149 0.00490 -0.0652 0.0111 1.0000
5.500 0.8486 0.01169 0.00512 -0.0631 0.0103 1.0000
5.750 0.8658 0.01192 0.00536 -0.0611 0.0095 1.0000
6.000 0.8823 0.01219 0.00564 -0.0589 0.0086 1.0000
6.250 0.8973 0.01254 0.00601 -0.0564 0.0075 1.0000
6.500 0.9125 0.01284 0.00635 -0.0539 0.0072 1.0000
6.750 0.9269 0.01310 0.00664 -0.0513 0.0069 1.0000
7.000 0.9414 0.01339 0.00695 -0.0487 0.0065 1.0000
7.250 0.9562 0.01370 0.00730 -0.0462 0.0062 1.0000
7.500 0.9718 0.01402 0.00763 -0.0440 0.0058 1.0000
7.750 0.9881 0.01434 0.00795 -0.0420 0.0054 1.0000
8.000 1.0021 0.01483 0.00847 -0.0395 0.0051 1.0000
8.250 1.0169 0.01530 0.00898 -0.0373 0.0048 1.0000
8.500 1.0326 0.01574 0.00948 -0.0353 0.0046 1.0000
8.750 1.0482 0.01620 0.00999 -0.0333 0.0044 1.0000
9.000 1.0626 0.01675 0.01059 -0.0312 0.0042 1.0000
9.250 1.0762 0.01736 0.01126 -0.0290 0.0041 1.0000
9.500 1.0886 0.01807 0.01204 -0.0266 0.0041 1.0000
9.750 1.1037 0.01862 0.01263 -0.0249 0.0039 1.0000
10.000 1.1179 0.01925 0.01330 -0.0230 0.0038 1.0000
10.250 1.1339 0.01977 0.01384 -0.0215 0.0035 1.0000
10.500 1.1491 0.02034 0.01443 -0.0200 0.0034 1.0000
10.750 1.1554 0.02154 0.01573 -0.0172 0.0033 1.0000
11.000 1.1606 0.02282 0.01712 -0.0144 0.0031 1.0000
11.250 1.1711 0.02379 0.01817 -0.0125 0.0031 1.0000
11.500 1.1818 0.02476 0.01922 -0.0106 0.0030 1.0000
11.750 1.1934 0.02568 0.02021 -0.0090 0.0029 1.0000
12.000 1.2042 0.02667 0.02127 -0.0074 0.0028 1.0000
12.250 1.2090 0.02816 0.02287 -0.0053 0.0028 1.0000
12.500 1.2173 0.02942 0.02421 -0.0036 0.0027 1.0000
12.750 1.2243 0.03080 0.02569 -0.0020 0.0026 1.0000
13.000 1.2298 0.03236 0.02735 -0.0004 0.0025 1.0000
13.250 1.2327 0.03422 0.02932 0.0012 0.0025 1.0000
13.500 1.2296 0.03672 0.03197 0.0031 0.0025 1.0000
13.750 1.2348 0.03846 0.03382 0.0041 0.0025 1.0000
14.000 1.2389 0.04041 0.03586 0.0050 0.0024 1.0000
14.250 1.2475 0.04194 0.03744 0.0054 0.0023 1.0000
14.500 1.2456 0.04462 0.04025 0.0063 0.0023 1.0000
14.750 1.2409 0.04771 0.04349 0.0070 0.0023 1.0000
15.000 1.2422 0.05024 0.04611 0.0072 0.0022 1.0000
15.250 1.2383 0.05348 0.04948 0.0073 0.0022 1.0000
15.500 1.2413 0.05601 0.05208 0.0070 0.0022 1.0000
15.750 1.2336 0.05998 0.05618 0.0066 0.0022 1.0000
16.000 1.2191 0.06506 0.06145 0.0058 0.0022 1.0000
16.250 1.2232 0.06784 0.06427 0.0048 0.0021 1.0000
16.500 1.2134 0.07263 0.06920 0.0034 0.0021 1.0000
16.750 1.2069 0.07717 0.07384 0.0018 0.0021 1.0000
17.000 1.1781 0.08532 0.08224 -0.0010 0.0021 1.0000
17.250 1.1604 0.09205 0.08912 -0.0038 0.0021 1.0000
17.500 1.1601 0.09613 0.09324 -0.0058 0.0021 1.0000
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Polar data table (+)
Polar graphs
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