GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 500,000 Max Cl/Cd: 87.92 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe585-il-500000-n5.txt Download as CSV file: xf-goe585-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7012 0.02632 0.02290 -0.0659 0.9952 0.0135
-9.250 -0.6799 0.02256 0.01859 -0.0675 0.9918 0.0144
-9.000 -0.6485 0.02264 0.01870 -0.0684 0.9896 0.0150
-8.750 -0.6162 0.02289 0.01900 -0.0693 0.9877 0.0155
-8.500 -0.5845 0.02261 0.01865 -0.0705 0.9860 0.0162
-8.250 -0.5582 0.02133 0.01713 -0.0710 0.9825 0.0172
-8.000 -0.5318 0.01960 0.01506 -0.0716 0.9790 0.0183
-7.750 -0.5022 0.01852 0.01375 -0.0726 0.9767 0.0191
-7.500 -0.4712 0.01818 0.01339 -0.0735 0.9745 0.0197
-7.250 -0.4436 0.01798 0.01315 -0.0736 0.9701 0.0204
-7.000 -0.4135 0.01751 0.01260 -0.0743 0.9671 0.0212
-6.750 -0.3822 0.01689 0.01184 -0.0753 0.9648 0.0223
-6.500 -0.3525 0.01629 0.01110 -0.0758 0.9614 0.0233
-6.250 -0.3241 0.01573 0.01041 -0.0760 0.9567 0.0241
-6.000 -0.2927 0.01526 0.00980 -0.0768 0.9533 0.0246
-5.750 -0.2619 0.01398 0.00832 -0.0778 0.9504 0.0258
-5.500 -0.2348 0.01329 0.00756 -0.0777 0.9444 0.0266
-5.250 -0.2040 0.01275 0.00695 -0.0784 0.9399 0.0274
-5.000 -0.1714 0.01230 0.00642 -0.0794 0.9361 0.0283
-4.750 -0.1429 0.01183 0.00589 -0.0795 0.9295 0.0290
-4.500 -0.1124 0.01136 0.00534 -0.0800 0.9239 0.0295
-4.250 -0.0824 0.01092 0.00482 -0.0803 0.9177 0.0301
-4.000 -0.0532 0.01053 0.00435 -0.0804 0.9083 0.0307
-3.750 -0.0246 0.01021 0.00395 -0.0804 0.8954 0.0313
-3.500 0.0032 0.00995 0.00360 -0.0802 0.8804 0.0320
-3.250 0.0302 0.00970 0.00328 -0.0798 0.8661 0.0325
-3.000 0.0568 0.00949 0.00299 -0.0793 0.8513 0.0329
-2.750 0.0830 0.00926 0.00267 -0.0787 0.8342 0.0334
-2.500 0.1089 0.00905 0.00235 -0.0781 0.8138 0.0343
-2.250 0.1347 0.00890 0.00211 -0.0774 0.7927 0.0354
-2.000 0.1606 0.00880 0.00191 -0.0767 0.7734 0.0365
-1.750 0.1864 0.00874 0.00175 -0.0761 0.7545 0.0378
-1.500 0.2122 0.00869 0.00162 -0.0755 0.7365 0.0394
-1.250 0.2380 0.00866 0.00151 -0.0749 0.7191 0.0420
-1.000 0.2637 0.00859 0.00143 -0.0742 0.7021 0.0523
-0.750 0.2891 0.00849 0.00139 -0.0736 0.6854 0.0856
-0.500 0.3147 0.00846 0.00135 -0.0730 0.6676 0.1070
-0.250 0.3402 0.00844 0.00133 -0.0724 0.6483 0.1294
0.000 0.3656 0.00845 0.00131 -0.0718 0.6262 0.1486
0.250 0.3906 0.00844 0.00130 -0.0711 0.6019 0.1778
0.500 0.4147 0.00837 0.00133 -0.0703 0.5744 0.2483
0.750 0.4382 0.00833 0.00139 -0.0695 0.5391 0.3279
1.000 0.4606 0.00840 0.00145 -0.0684 0.4913 0.3982
1.250 0.4696 0.00734 0.00160 -0.0645 0.4553 0.8465
1.750 0.5742 0.00780 0.00186 -0.0753 0.3862 1.0000
2.000 0.5976 0.00801 0.00195 -0.0743 0.3665 1.0000
2.250 0.6212 0.00821 0.00205 -0.0733 0.3489 1.0000
2.500 0.6451 0.00838 0.00215 -0.0724 0.3350 1.0000
2.750 0.6692 0.00855 0.00225 -0.0716 0.3227 1.0000
3.000 0.6933 0.00872 0.00237 -0.0708 0.3115 1.0000
3.250 0.7173 0.00891 0.00250 -0.0699 0.3009 1.0000
3.500 0.7417 0.00907 0.00263 -0.0691 0.2903 1.0000
3.750 0.7659 0.00925 0.00276 -0.0683 0.2798 1.0000
4.000 0.7900 0.00945 0.00292 -0.0675 0.2697 1.0000
4.250 0.8144 0.00963 0.00308 -0.0668 0.2607 1.0000
4.500 0.8388 0.00982 0.00324 -0.0660 0.2523 1.0000
4.750 0.8627 0.01005 0.00343 -0.0652 0.2412 1.0000
5.000 0.8868 0.01027 0.00361 -0.0645 0.2298 1.0000
5.250 0.9109 0.01049 0.00381 -0.0637 0.2198 1.0000
5.500 0.9348 0.01074 0.00403 -0.0630 0.2099 1.0000
5.750 0.9587 0.01098 0.00425 -0.0622 0.2001 1.0000
6.000 0.9828 0.01121 0.00448 -0.0615 0.1918 1.0000
6.500 1.0304 0.01172 0.00499 -0.0600 0.1749 1.0000
6.750 1.0538 0.01202 0.00526 -0.0592 0.1637 1.0000
7.000 1.0768 0.01234 0.00554 -0.0583 0.1518 1.0000
7.250 1.0991 0.01273 0.00586 -0.0574 0.1336 1.0000
7.500 1.1202 0.01323 0.00626 -0.0563 0.1097 1.0000
7.750 1.1397 0.01389 0.00676 -0.0551 0.0832 1.0000
8.250 1.1797 0.01508 0.00781 -0.0526 0.0549 1.0000
8.500 1.2007 0.01556 0.00830 -0.0515 0.0471 1.0000
8.750 1.2206 0.01613 0.00886 -0.0503 0.0380 1.0000
9.000 1.2386 0.01686 0.00951 -0.0489 0.0253 1.0000
9.250 1.2564 0.01757 0.01019 -0.0474 0.0181 1.0000
9.500 1.2744 0.01825 0.01088 -0.0459 0.0152 1.0000
9.750 1.2930 0.01882 0.01153 -0.0444 0.0138 1.0000
10.000 1.3105 0.01946 0.01225 -0.0429 0.0126 1.0000
10.250 1.3262 0.02020 0.01305 -0.0411 0.0114 1.0000
10.500 1.3408 0.02096 0.01389 -0.0392 0.0105 1.0000
10.750 1.3547 0.02161 0.01463 -0.0371 0.0101 1.0000
11.000 1.3667 0.02234 0.01544 -0.0347 0.0096 1.0000
11.250 1.3777 0.02312 0.01630 -0.0323 0.0091 1.0000
11.500 1.3876 0.02397 0.01723 -0.0298 0.0087 1.0000
11.750 1.3957 0.02495 0.01832 -0.0273 0.0084 1.0000
12.000 1.3998 0.02622 0.01968 -0.0245 0.0080 1.0000
12.250 1.4031 0.02757 0.02114 -0.0218 0.0078 1.0000
12.500 1.4099 0.02875 0.02242 -0.0198 0.0076 1.0000
12.750 1.4149 0.03010 0.02389 -0.0178 0.0074 1.0000
13.000 1.4183 0.03165 0.02555 -0.0159 0.0071 1.0000
13.250 1.4212 0.03334 0.02735 -0.0142 0.0069 1.0000
13.500 1.4237 0.03517 0.02928 -0.0129 0.0066 1.0000
13.750 1.4247 0.03725 0.03148 -0.0118 0.0064 1.0000
14.000 1.4218 0.03988 0.03423 -0.0109 0.0064 1.0000
14.250 1.4193 0.04268 0.03715 -0.0105 0.0063 1.0000
14.500 1.4153 0.04584 0.04043 -0.0106 0.0061 1.0000
14.750 1.4089 0.04953 0.04426 -0.0111 0.0060 1.0000
15.000 1.4008 0.05367 0.04854 -0.0120 0.0060 1.0000
15.250 1.3879 0.05880 0.05381 -0.0137 0.0058 1.0000
15.500 1.3769 0.06401 0.05916 -0.0157 0.0059 1.0000
15.750 1.3618 0.07019 0.06548 -0.0185 0.0057 1.0000
16.000 1.3465 0.07668 0.07211 -0.0215 0.0057 1.0000
16.250 1.3321 0.08314 0.07870 -0.0245 0.0057 1.0000
16.500 1.3148 0.09017 0.08587 -0.0279 0.0057 1.0000
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