GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.81 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe257-il-1000000-n5.txt Download as CSV file: xf-goe257-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4471 0.09583 0.09431 -0.0119 1.0000 0.0055
-8.750 -0.4508 0.08933 0.08783 -0.0163 0.9641 0.0058
-8.500 -0.4497 0.08615 0.08459 -0.0178 0.9307 0.0059
-8.250 -0.4459 0.08294 0.08128 -0.0201 0.9014 0.0060
-8.000 -0.4368 0.07959 0.07780 -0.0235 0.8655 0.0062
-7.750 -0.4264 0.07598 0.07393 -0.0274 0.7930 0.0064
-7.250 -0.4006 0.06079 0.05834 -0.0442 0.7310 0.0079
-6.750 -0.3574 0.05183 0.04909 -0.0529 0.7063 0.0085
-6.500 -0.3335 0.04830 0.04543 -0.0559 0.6971 0.0090
-6.250 -0.3076 0.03685 0.03352 -0.0626 0.6910 0.0110
-5.750 -0.2536 0.02321 0.01887 -0.0666 0.6777 0.0146
-5.500 -0.2260 0.02307 0.01866 -0.0670 0.6701 0.0149
-5.250 -0.1985 0.02293 0.01846 -0.0673 0.6631 0.0151
-5.000 -0.1708 0.02232 0.01773 -0.0677 0.6573 0.0154
-4.750 -0.1427 0.02129 0.01657 -0.0682 0.6525 0.0160
-4.500 -0.1141 0.01973 0.01478 -0.0686 0.6471 0.0171
-4.250 -0.0844 0.01708 0.01164 -0.0689 0.6423 0.0188
-4.000 -0.0555 0.01676 0.01118 -0.0692 0.6370 0.0192
-3.750 -0.0270 0.01496 0.00910 -0.0697 0.6317 0.0198
-3.500 0.0016 0.01430 0.00834 -0.0701 0.6270 0.0200
-3.250 0.0304 0.01375 0.00771 -0.0704 0.6223 0.0203
-3.000 0.0592 0.01326 0.00714 -0.0708 0.6171 0.0206
-2.750 0.0880 0.01294 0.00674 -0.0711 0.6123 0.0210
-2.500 0.1170 0.01248 0.00622 -0.0714 0.6073 0.0214
-2.250 0.1459 0.01202 0.00568 -0.0716 0.6015 0.0218
-2.000 0.1748 0.01164 0.00521 -0.0719 0.5949 0.0223
-1.750 0.2037 0.01129 0.00479 -0.0721 0.5858 0.0228
-1.500 0.2325 0.01100 0.00444 -0.0724 0.5754 0.0233
-1.250 0.2614 0.01074 0.00410 -0.0727 0.5641 0.0236
-1.000 0.2902 0.01050 0.00380 -0.0729 0.5531 0.0238
-0.750 0.3190 0.01027 0.00352 -0.0732 0.5420 0.0240
-0.500 0.3478 0.01008 0.00327 -0.0735 0.5274 0.0241
-0.250 0.3765 0.00997 0.00308 -0.0737 0.5082 0.0244
0.000 0.4051 0.00992 0.00295 -0.0740 0.4876 0.0247
0.250 0.4338 0.00982 0.00277 -0.0743 0.4721 0.0248
0.500 0.4626 0.00973 0.00262 -0.0746 0.4587 0.0248
0.750 0.4913 0.00967 0.00251 -0.0749 0.4460 0.0249
1.000 0.5201 0.00964 0.00242 -0.0752 0.4343 0.0250
1.250 0.5488 0.00962 0.00237 -0.0755 0.4251 0.0252
1.500 0.5776 0.00961 0.00234 -0.0758 0.4170 0.0254
1.750 0.6063 0.00959 0.00226 -0.0761 0.4052 0.0264
2.000 0.6350 0.00960 0.00223 -0.0764 0.3953 0.0279
2.250 0.6637 0.00962 0.00224 -0.0766 0.3875 0.0289
2.500 0.6922 0.00969 0.00228 -0.0769 0.3771 0.0298
2.750 0.7207 0.00976 0.00232 -0.0772 0.3653 0.0306
3.000 0.7491 0.00985 0.00238 -0.0774 0.3511 0.0313
3.250 0.7773 0.01001 0.00246 -0.0777 0.3297 0.0328
3.500 0.8045 0.01036 0.00262 -0.0779 0.2832 0.0336
3.750 0.8312 0.01085 0.00289 -0.0780 0.2347 0.0362
4.250 0.8817 0.00950 0.00340 -0.0780 0.1979 1.0000
4.500 0.9092 0.00980 0.00360 -0.0782 0.1798 1.0000
4.750 0.9364 0.01012 0.00381 -0.0783 0.1605 1.0000
5.000 0.9615 0.01088 0.00424 -0.0783 0.0983 1.0000
5.250 0.9869 0.01154 0.00471 -0.0783 0.0551 1.0000
5.500 1.0137 0.01187 0.00500 -0.0783 0.0450 1.0000
5.750 1.0403 0.01221 0.00529 -0.0784 0.0340 1.0000
6.000 1.0661 0.01270 0.00568 -0.0783 0.0151 1.0000
6.250 1.0928 0.01298 0.00598 -0.0783 0.0125 1.0000
6.500 1.1191 0.01331 0.00633 -0.0783 0.0109 1.0000
6.750 1.1450 0.01370 0.00676 -0.0782 0.0093 1.0000
7.000 1.1709 0.01405 0.00715 -0.0781 0.0085 1.0000
7.250 1.1967 0.01440 0.00752 -0.0780 0.0078 1.0000
7.500 1.2221 0.01477 0.00792 -0.0778 0.0071 1.0000
7.750 1.2470 0.01521 0.00838 -0.0776 0.0064 1.0000
8.000 1.2707 0.01579 0.00901 -0.0772 0.0059 1.0000
8.250 1.2951 0.01622 0.00949 -0.0769 0.0056 1.0000
8.500 1.3189 0.01671 0.01003 -0.0765 0.0053 1.0000
8.750 1.3421 0.01724 0.01060 -0.0760 0.0050 1.0000
9.000 1.3649 0.01777 0.01119 -0.0755 0.0047 1.0000
9.250 1.3873 0.01830 0.01176 -0.0750 0.0044 1.0000
9.500 1.4087 0.01891 0.01240 -0.0743 0.0041 1.0000
9.750 1.4267 0.01983 0.01339 -0.0730 0.0038 1.0000
10.000 1.4464 0.02049 0.01412 -0.0721 0.0037 1.0000
10.250 1.4648 0.02122 0.01494 -0.0709 0.0036 1.0000
10.500 1.4815 0.02201 0.01581 -0.0695 0.0035 1.0000
10.750 1.4963 0.02287 0.01676 -0.0678 0.0034 1.0000
11.000 1.5091 0.02379 0.01776 -0.0658 0.0033 1.0000
11.250 1.5200 0.02476 0.01881 -0.0636 0.0031 1.0000
11.500 1.5256 0.02581 0.01995 -0.0605 0.0031 1.0000
11.750 1.5298 0.02701 0.02124 -0.0575 0.0030 1.0000
12.000 1.5346 0.02836 0.02267 -0.0550 0.0029 1.0000
12.250 1.5387 0.02993 0.02435 -0.0529 0.0028 1.0000
12.500 1.5436 0.03159 0.02609 -0.0512 0.0028 1.0000
12.750 1.5471 0.03352 0.02812 -0.0497 0.0027 1.0000
13.000 1.5500 0.03569 0.03038 -0.0486 0.0027 1.0000
13.250 1.5515 0.03818 0.03298 -0.0479 0.0026 1.0000
13.500 1.5514 0.04105 0.03596 -0.0475 0.0026 1.0000
13.750 1.5494 0.04429 0.03931 -0.0473 0.0025 1.0000
14.000 1.5441 0.04797 0.04311 -0.0473 0.0025 1.0000
14.250 1.5359 0.05209 0.04737 -0.0474 0.0024 1.0000
14.500 1.5248 0.05662 0.05204 -0.0476 0.0024 1.0000
14.750 1.5144 0.06112 0.05667 -0.0479 0.0024 1.0000
15.000 1.5066 0.06543 0.06111 -0.0485 0.0023 1.0000
15.250 1.4991 0.06983 0.06563 -0.0493 0.0023 1.0000
15.500 1.4911 0.07444 0.07037 -0.0502 0.0023 1.0000
15.750 1.4830 0.07925 0.07530 -0.0514 0.0023 1.0000
16.000 1.4740 0.08432 0.08049 -0.0528 0.0023 1.0000
16.250 1.4644 0.08958 0.08588 -0.0544 0.0023 1.0000
16.500 1.4548 0.09496 0.09138 -0.0561 0.0022 1.0000
16.750 1.4449 0.10049 0.09702 -0.0580 0.0022 1.0000
17.000 1.4336 0.10632 0.10298 -0.0600 0.0022 1.0000
17.250 1.4219 0.11230 0.10908 -0.0623 0.0022 1.0000
17.500 1.4105 0.11837 0.11527 -0.0647 0.0022 1.0000
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