GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 500,000 Max Cl/Cd: 98.79 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe187-il-500000-n5.txt Download as CSV file: xf-goe187-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3421 0.11764 0.11541 -0.0134 1.0000 0.0052
-9.500 -0.3355 0.11451 0.11230 -0.0150 1.0000 0.0052
-9.250 -0.3292 0.11141 0.10921 -0.0166 1.0000 0.0052
-9.000 -0.2158 0.09222 0.09025 -0.0279 1.0000 0.0055
-8.750 -0.2122 0.08898 0.08703 -0.0281 0.9997 0.0056
-8.500 -0.2037 0.08512 0.08317 -0.0303 0.9883 0.0058
-8.250 -0.1950 0.08118 0.07923 -0.0327 0.9712 0.0059
-8.000 -0.1852 0.07710 0.07513 -0.0353 0.9456 0.0060
-7.750 -0.1796 0.07357 0.07153 -0.0366 0.9121 0.0061
-7.500 -0.1776 0.07055 0.06841 -0.0369 0.8795 0.0061
-7.250 -0.1753 0.06751 0.06526 -0.0374 0.8507 0.0062
-7.000 -0.1726 0.06444 0.06211 -0.0382 0.8247 0.0063
-6.750 -0.1700 0.06132 0.05890 -0.0394 0.8010 0.0064
-6.500 -0.1645 0.05791 0.05541 -0.0416 0.7817 0.0065
-6.250 -0.1551 0.05420 0.05163 -0.0447 0.7639 0.0066
-6.000 -0.1433 0.05034 0.04769 -0.0483 0.7495 0.0068
-5.750 -0.1290 0.04641 0.04368 -0.0520 0.7362 0.0069
-5.500 -0.1122 0.04240 0.03958 -0.0559 0.7245 0.0071
-5.250 -0.0921 0.03837 0.03546 -0.0599 0.7154 0.0075
-5.000 -0.0676 0.03450 0.03148 -0.0642 0.7074 0.0078
-4.750 -0.0404 0.03075 0.02758 -0.0682 0.6995 0.0080
-4.500 -0.0156 0.02726 0.02396 -0.0708 0.6916 0.0081
-4.250 0.0093 0.02396 0.02049 -0.0728 0.6838 0.0081
-4.000 0.0343 0.02083 0.01720 -0.0744 0.6769 0.0082
-3.750 0.0600 0.01789 0.01407 -0.0757 0.6700 0.0082
-3.500 0.0860 0.01522 0.01121 -0.0766 0.6635 0.0082
-3.000 0.1346 0.00965 0.00521 -0.0786 0.6494 0.0090
-2.000 0.2544 0.01873 0.01293 -0.0828 0.6312 0.0076
-1.750 0.2837 0.01691 0.01081 -0.0827 0.6234 0.0073
-1.500 0.3132 0.01525 0.00885 -0.0824 0.6148 0.0072
-1.250 0.3426 0.01372 0.00703 -0.0821 0.6058 0.0073
-1.000 0.3714 0.01239 0.00542 -0.0817 0.5955 0.0078
-0.750 0.3994 0.01176 0.00465 -0.0816 0.5837 0.0093
-0.500 0.4273 0.01115 0.00391 -0.0815 0.5712 0.0100
-0.250 0.4552 0.01064 0.00329 -0.0813 0.5578 0.0110
0.000 0.4828 0.01034 0.00287 -0.0812 0.5402 0.0126
0.250 0.5102 0.01002 0.00239 -0.0811 0.5148 0.0155
0.500 0.5374 0.00998 0.00217 -0.0810 0.4837 0.0191
0.750 0.5645 0.01006 0.00207 -0.0809 0.4567 0.0240
1.000 0.5916 0.01011 0.00196 -0.0809 0.4348 0.0301
1.250 0.6190 0.01019 0.00192 -0.0809 0.4180 0.0368
1.500 0.6456 0.00817 0.00206 -0.0814 0.4050 1.0000
1.750 0.6730 0.00832 0.00208 -0.0813 0.3943 1.0000
2.000 0.7004 0.00848 0.00213 -0.0813 0.3836 1.0000
2.250 0.7276 0.00866 0.00220 -0.0813 0.3725 1.0000
2.750 0.7821 0.00898 0.00236 -0.0812 0.3544 1.0000
3.000 0.8093 0.00915 0.00246 -0.0812 0.3473 1.0000
3.250 0.8367 0.00928 0.00258 -0.0812 0.3411 1.0000
3.500 0.8637 0.00946 0.00270 -0.0812 0.3342 1.0000
3.750 0.8909 0.00960 0.00282 -0.0812 0.3280 1.0000
4.000 0.9179 0.00977 0.00297 -0.0812 0.3213 1.0000
4.250 0.9448 0.00994 0.00313 -0.0812 0.3149 1.0000
4.500 0.9717 0.01011 0.00328 -0.0811 0.3078 1.0000
4.750 0.9984 0.01029 0.00347 -0.0811 0.3013 1.0000
5.000 1.0251 0.01048 0.00366 -0.0810 0.2927 1.0000
5.250 1.0515 0.01069 0.00385 -0.0810 0.2825 1.0000
5.500 1.0778 0.01091 0.00408 -0.0809 0.2726 1.0000
5.750 1.1036 0.01118 0.00432 -0.0807 0.2568 1.0000
6.000 1.1285 0.01155 0.00460 -0.0805 0.2315 1.0000
6.250 1.1509 0.01222 0.00504 -0.0800 0.1864 1.0000
6.500 1.1739 0.01281 0.00555 -0.0795 0.1625 1.0000
6.750 1.1952 0.01359 0.00615 -0.0788 0.1253 1.0000
7.000 1.2147 0.01455 0.00685 -0.0779 0.0884 1.0000
7.250 1.2380 0.01502 0.00733 -0.0774 0.0797 1.0000
7.500 1.2603 0.01559 0.00788 -0.0768 0.0676 1.0000
7.750 1.2734 0.01715 0.00913 -0.0749 0.0110 1.0000
8.000 1.2940 0.01784 0.00991 -0.0740 0.0070 1.0000
8.250 1.3135 0.01860 0.01078 -0.0728 0.0055 1.0000
8.500 1.3336 0.01926 0.01155 -0.0718 0.0047 1.0000
8.750 1.3518 0.02004 0.01242 -0.0706 0.0039 1.0000
9.000 1.3687 0.02090 0.01341 -0.0692 0.0035 1.0000
9.250 1.3843 0.02182 0.01444 -0.0676 0.0032 1.0000
9.500 1.3977 0.02284 0.01561 -0.0658 0.0029 1.0000
9.750 1.4084 0.02394 0.01682 -0.0635 0.0027 1.0000
10.000 1.4133 0.02517 0.01816 -0.0604 0.0025 1.0000
10.250 1.4125 0.02683 0.01995 -0.0569 0.0024 1.0000
10.500 1.4121 0.02863 0.02189 -0.0539 0.0024 1.0000
10.750 1.4148 0.03039 0.02379 -0.0518 0.0023 1.0000
11.000 1.4173 0.03231 0.02584 -0.0500 0.0021 1.0000
11.250 1.4192 0.03444 0.02811 -0.0487 0.0019 1.0000
11.500 1.4201 0.03684 0.03064 -0.0476 0.0018 1.0000
11.750 1.4205 0.03946 0.03339 -0.0469 0.0017 1.0000
12.000 1.4178 0.04255 0.03661 -0.0464 0.0017 1.0000
12.250 1.4149 0.04581 0.04000 -0.0462 0.0016 1.0000
12.500 1.4107 0.04932 0.04363 -0.0461 0.0016 1.0000
12.750 1.4051 0.05308 0.04752 -0.0462 0.0015 1.0000
13.000 1.3984 0.05707 0.05163 -0.0465 0.0015 1.0000
13.250 1.3903 0.06129 0.05598 -0.0469 0.0015 1.0000
13.500 1.3800 0.06587 0.06068 -0.0474 0.0014 1.0000
13.750 1.3697 0.07055 0.06548 -0.0479 0.0014 1.0000
14.000 1.3628 0.07499 0.07007 -0.0486 0.0014 1.0000
14.250 1.3558 0.07958 0.07481 -0.0496 0.0014 1.0000
14.500 1.3482 0.08432 0.07970 -0.0506 0.0013 1.0000
14.750 1.3401 0.08926 0.08479 -0.0517 0.0013 1.0000
15.000 1.3317 0.09437 0.09006 -0.0531 0.0013 1.0000
15.250 1.3228 0.09967 0.09552 -0.0546 0.0013 1.0000
15.500 1.3132 0.10517 0.10122 -0.0563 0.0012 1.0000
15.750 1.3031 0.11093 0.10714 -0.0583 0.0012 1.0000
16.000 1.2929 0.11689 0.11326 -0.0606 0.0012 1.0000
16.250 1.2826 0.12300 0.11952 -0.0631 0.0012 1.0000
16.500 1.2717 0.12939 0.12606 -0.0660 0.0012 1.0000
16.750 1.2606 0.13605 0.13287 -0.0692 0.0012 1.0000
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