GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 500,000 Max Cl/Cd: 76.56 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe548-il-500000-n5.txt Download as CSV file: xf-goe548-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7301 0.06655 0.06390 -0.0626 1.0000 0.0046
-13.000 -0.7621 0.05657 0.05375 -0.0690 1.0000 0.0047
-12.750 -0.7853 0.04951 0.04655 -0.0735 1.0000 0.0046
-12.500 -0.8012 0.04487 0.04179 -0.0756 1.0000 0.0046
-12.250 -0.8200 0.04046 0.03718 -0.0771 0.9994 0.0046
-12.000 -0.8214 0.03599 0.03244 -0.0814 0.9951 0.0046
-11.750 -0.8192 0.03303 0.02923 -0.0826 0.9896 0.0047
-11.500 -0.8201 0.03016 0.02608 -0.0821 0.9826 0.0048
-11.250 -0.8096 0.02811 0.02384 -0.0819 0.9773 0.0050
-11.000 -0.7971 0.02644 0.02199 -0.0811 0.9716 0.0051
-10.750 -0.7799 0.02499 0.02037 -0.0809 0.9678 0.0052
-10.500 -0.7587 0.02376 0.01897 -0.0812 0.9656 0.0054
-10.250 -0.7420 0.02256 0.01762 -0.0803 0.9612 0.0056
-10.000 -0.7212 0.02150 0.01641 -0.0800 0.9577 0.0059
-9.750 -0.6971 0.02053 0.01529 -0.0803 0.9553 0.0062
-9.500 -0.6706 0.01961 0.01422 -0.0810 0.9536 0.0066
-9.250 -0.6434 0.01872 0.01317 -0.0817 0.9520 0.0069
-9.000 -0.6252 0.01759 0.01191 -0.0806 0.9477 0.0074
-8.750 -0.6011 0.01672 0.01093 -0.0806 0.9447 0.0078
-8.500 -0.5735 0.01598 0.01009 -0.0812 0.9423 0.0083
-8.250 -0.5449 0.01529 0.00926 -0.0819 0.9403 0.0089
-8.000 -0.5159 0.01466 0.00853 -0.0827 0.9387 0.0096
-7.750 -0.4933 0.01417 0.00794 -0.0820 0.9351 0.0102
-7.500 -0.4693 0.01355 0.00724 -0.0816 0.9314 0.0118
-7.250 -0.4415 0.01304 0.00669 -0.0820 0.9284 0.0136
-7.000 -0.4120 0.01259 0.00615 -0.0827 0.9257 0.0155
-6.750 -0.3846 0.01218 0.00574 -0.0829 0.9229 0.0201
-6.500 -0.3610 0.01191 0.00546 -0.0822 0.9192 0.0254
-6.250 -0.3346 0.01171 0.00525 -0.0821 0.9159 0.0310
-6.000 -0.3062 0.01150 0.00497 -0.0824 0.9131 0.0342
-5.750 -0.2773 0.01123 0.00470 -0.0829 0.9105 0.0381
-5.500 -0.2518 0.01106 0.00448 -0.0826 0.9069 0.0411
-5.250 -0.2267 0.01095 0.00432 -0.0821 0.9027 0.0432
-5.000 -0.2011 0.01064 0.00396 -0.0818 0.8988 0.0472
-4.750 -0.1730 0.01039 0.00367 -0.0821 0.8958 0.0510
-4.500 -0.1496 0.01021 0.00345 -0.0812 0.8912 0.0532
-4.250 -0.1246 0.01004 0.00323 -0.0807 0.8862 0.0553
-4.000 -0.0961 0.00987 0.00299 -0.0809 0.8814 0.0583
-3.750 -0.0744 0.00967 0.00280 -0.0796 0.8734 0.0662
-3.500 -0.0507 0.00928 0.00256 -0.0789 0.8657 0.1093
-3.250 -0.0303 0.00884 0.00235 -0.0776 0.8565 0.1738
-3.000 -0.0071 0.00860 0.00221 -0.0767 0.8482 0.2106
-2.750 0.0173 0.00837 0.00206 -0.0761 0.8397 0.2436
-2.500 0.0400 0.00814 0.00193 -0.0751 0.8285 0.2811
-2.250 0.0632 0.00791 0.00181 -0.0742 0.8156 0.3250
-2.000 0.0869 0.00769 0.00170 -0.0734 0.8004 0.3700
-1.750 0.1107 0.00751 0.00158 -0.0726 0.7844 0.4140
-1.500 0.1336 0.00733 0.00149 -0.0717 0.7696 0.4658
-1.000 0.1797 0.00710 0.00142 -0.0697 0.7467 0.5564
-0.750 0.2030 0.00704 0.00141 -0.0688 0.7360 0.5948
-0.500 0.2258 0.00700 0.00142 -0.0677 0.7244 0.6296
-0.250 0.2490 0.00695 0.00144 -0.0667 0.7152 0.6639
0.000 0.2725 0.00695 0.00146 -0.0658 0.7042 0.6885
0.250 0.2960 0.00693 0.00149 -0.0648 0.6950 0.7167
0.500 0.3190 0.00692 0.00153 -0.0637 0.6845 0.7469
0.750 0.3419 0.00686 0.00159 -0.0626 0.6750 0.7849
1.000 0.3650 0.00683 0.00166 -0.0614 0.6644 0.8244
1.250 0.3900 0.00683 0.00173 -0.0607 0.6534 0.8579
1.500 0.4173 0.00686 0.00180 -0.0606 0.6385 0.8828
1.750 0.4475 0.00692 0.00187 -0.0611 0.6218 0.9031
2.000 0.4807 0.00706 0.00197 -0.0623 0.5975 0.9205
2.250 0.5158 0.00727 0.00208 -0.0641 0.5687 0.9347
2.500 0.5513 0.00753 0.00223 -0.0660 0.5392 0.9454
2.750 0.5859 0.00780 0.00240 -0.0677 0.5116 0.9544
3.000 0.6171 0.00806 0.00257 -0.0686 0.4875 0.9638
3.250 0.6461 0.00844 0.00279 -0.0692 0.4500 0.9725
3.500 0.6711 0.00909 0.00308 -0.0691 0.3730 0.9821
3.750 0.6954 0.01004 0.00350 -0.0691 0.2607 0.9910
4.000 0.7218 0.01099 0.00401 -0.0697 0.1735 0.9979
4.250 0.7476 0.01139 0.00429 -0.0697 0.1446 1.0000
4.750 0.7717 0.01229 0.00484 -0.0638 0.0798 1.0000
5.000 0.7872 0.01260 0.00511 -0.0615 0.0675 1.0000
5.250 0.7964 0.01323 0.00553 -0.0579 0.0225 1.0000
5.500 0.8125 0.01354 0.00587 -0.0557 0.0168 1.0000
5.750 0.8285 0.01385 0.00621 -0.0534 0.0148 1.0000
6.000 0.8424 0.01421 0.00661 -0.0506 0.0130 1.0000
6.250 0.8541 0.01464 0.00715 -0.0474 0.0113 1.0000
6.500 0.8684 0.01498 0.00753 -0.0449 0.0108 1.0000
6.750 0.8833 0.01532 0.00793 -0.0425 0.0101 1.0000
7.000 0.8977 0.01573 0.00839 -0.0400 0.0094 1.0000
7.250 0.9117 0.01620 0.00890 -0.0376 0.0089 1.0000
7.500 0.9251 0.01673 0.00948 -0.0351 0.0084 1.0000
7.750 0.9384 0.01730 0.01009 -0.0326 0.0081 1.0000
8.000 0.9482 0.01809 0.01094 -0.0297 0.0076 1.0000
8.250 0.9590 0.01887 0.01178 -0.0270 0.0072 1.0000
8.500 0.9732 0.01945 0.01242 -0.0249 0.0068 1.0000
8.750 0.9869 0.02009 0.01311 -0.0229 0.0063 1.0000
9.000 0.9980 0.02092 0.01403 -0.0204 0.0061 1.0000
9.250 1.0085 0.02182 0.01501 -0.0181 0.0059 1.0000
9.500 1.0181 0.02282 0.01609 -0.0156 0.0058 1.0000
9.750 1.0299 0.02369 0.01701 -0.0137 0.0056 1.0000
10.000 1.0408 0.02465 0.01803 -0.0116 0.0054 1.0000
10.250 1.0509 0.02569 0.01911 -0.0097 0.0052 1.0000
10.500 1.0593 0.02694 0.02045 -0.0075 0.0051 1.0000
10.750 1.0635 0.02872 0.02229 -0.0050 0.0049 1.0000
11.000 1.0731 0.03003 0.02371 -0.0031 0.0048 1.0000
11.250 1.0824 0.03140 0.02521 -0.0014 0.0047 1.0000
11.500 1.0906 0.03300 0.02695 0.0005 0.0045 1.0000
11.750 1.0976 0.03481 0.02895 0.0024 0.0044 1.0000
12.000 1.1052 0.03627 0.03053 0.0039 0.0042 1.0000
12.250 1.1097 0.03841 0.03284 0.0057 0.0042 1.0000
12.500 1.1137 0.04032 0.03489 0.0073 0.0040 1.0000
12.750 1.1182 0.04191 0.03659 0.0084 0.0038 1.0000
13.000 1.1200 0.04400 0.03882 0.0096 0.0036 1.0000
13.250 1.1186 0.04669 0.04167 0.0109 0.0036 1.0000
13.500 1.1090 0.05072 0.04598 0.0125 0.0037 1.0000
13.750 1.1103 0.05279 0.04813 0.0127 0.0036 1.0000
14.000 1.1061 0.05578 0.05127 0.0130 0.0036 1.0000
14.250 1.1047 0.05842 0.05399 0.0128 0.0034 1.0000
14.500 1.0936 0.06277 0.05854 0.0127 0.0034 1.0000
14.750 1.0818 0.06738 0.06333 0.0120 0.0034 1.0000
15.000 1.0742 0.07155 0.06763 0.0108 0.0034 1.0000
15.250 1.0584 0.07734 0.07362 0.0090 0.0034 1.0000
15.500 1.0523 0.08174 0.07812 0.0070 0.0033 1.0000
15.750 1.0327 0.08881 0.08538 0.0040 0.0034 1.0000
16.000 1.0062 0.09773 0.09454 -0.0001 0.0034 1.0000
16.250 1.0000 0.10303 0.09991 -0.0032 0.0033 1.0000
16.500 0.9765 0.11231 0.10939 -0.0082 0.0034 1.0000
16.750 0.9576 0.12122 0.11844 -0.0132 0.0034 1.0000
17.000 0.8908 0.14449 0.14207 -0.0258 0.0037 1.0000
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Polar data table (+)
Polar graphs
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