GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe385-il-1000000-n5.txt Download as CSV file: xf-goe385-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4099 0.10882 0.10724 -0.0133 1.0000 0.0053
-10.000 -0.4077 0.10450 0.10294 -0.0153 1.0000 0.0055
-8.750 -0.4161 0.08024 0.07853 -0.0284 0.8833 0.0068
-7.750 -0.4011 0.04713 0.04473 -0.0623 0.8081 0.0090
-7.500 -0.4088 0.02485 0.02125 -0.0694 0.8024 0.0115
-7.000 -0.3717 0.01436 0.00949 -0.0692 0.7870 0.0151
-6.750 -0.3429 0.01472 0.00986 -0.0693 0.7778 0.0155
-6.500 -0.3140 0.01519 0.01036 -0.0694 0.7678 0.0157
-6.250 -0.2855 0.01555 0.01073 -0.0694 0.7564 0.0159
-6.000 -0.2574 0.01568 0.01081 -0.0695 0.7431 0.0163
-5.750 -0.2298 0.01546 0.01049 -0.0695 0.7256 0.0167
-5.500 -0.2027 0.01487 0.00968 -0.0695 0.7027 0.0177
-5.250 -0.1759 0.01393 0.00846 -0.0694 0.6794 0.0190
-5.000 -0.1482 0.01357 0.00792 -0.0694 0.6613 0.0194
-4.750 -0.1204 0.01323 0.00744 -0.0694 0.6481 0.0198
-4.500 -0.0930 0.01263 0.00672 -0.0695 0.6373 0.0204
-4.250 -0.0650 0.01244 0.00644 -0.0696 0.6264 0.0208
-4.000 -0.0368 0.01233 0.00626 -0.0697 0.6152 0.0212
-3.750 -0.0086 0.01213 0.00598 -0.0698 0.6054 0.0216
-3.500 0.0195 0.01179 0.00555 -0.0699 0.5964 0.0221
-3.250 0.0477 0.01143 0.00511 -0.0700 0.5893 0.0226
-2.750 0.1044 0.01086 0.00442 -0.0702 0.5782 0.0238
-2.500 0.1328 0.01055 0.00405 -0.0703 0.5720 0.0243
-2.250 0.1611 0.01029 0.00374 -0.0704 0.5664 0.0247
-2.000 0.1896 0.01003 0.00344 -0.0705 0.5601 0.0249
-1.750 0.2179 0.00982 0.00317 -0.0706 0.5536 0.0252
-1.500 0.2464 0.00960 0.00292 -0.0707 0.5475 0.0254
-1.250 0.2749 0.00942 0.00270 -0.0708 0.5404 0.0255
-1.000 0.3034 0.00925 0.00250 -0.0710 0.5334 0.0257
-0.750 0.3319 0.00915 0.00236 -0.0711 0.5248 0.0258
-0.500 0.3603 0.00894 0.00210 -0.0713 0.5134 0.0263
-0.250 0.3887 0.00876 0.00184 -0.0714 0.4994 0.0269
0.000 0.4172 0.00865 0.00167 -0.0716 0.4872 0.0277
0.250 0.4456 0.00861 0.00157 -0.0717 0.4729 0.0287
0.500 0.4738 0.00864 0.00152 -0.0718 0.4546 0.0295
0.750 0.5018 0.00872 0.00150 -0.0720 0.4319 0.0303
1.000 0.5297 0.00882 0.00151 -0.0721 0.4085 0.0310
1.250 0.5576 0.00893 0.00153 -0.0722 0.3874 0.0317
1.500 0.5855 0.00903 0.00156 -0.0723 0.3698 0.0324
1.750 0.6135 0.00913 0.00160 -0.0724 0.3548 0.0332
2.000 0.6415 0.00924 0.00165 -0.0725 0.3419 0.0343
2.250 0.6694 0.00934 0.00171 -0.0726 0.3305 0.0367
2.500 0.6975 0.00940 0.00178 -0.0727 0.3207 0.0561
3.000 0.7476 0.00764 0.00213 -0.0724 0.2992 1.0000
3.250 0.7751 0.00784 0.00224 -0.0724 0.2858 1.0000
3.500 0.8027 0.00801 0.00235 -0.0725 0.2752 1.0000
3.750 0.8305 0.00816 0.00246 -0.0726 0.2683 1.0000
4.000 0.8582 0.00831 0.00258 -0.0727 0.2613 1.0000
4.250 0.8858 0.00846 0.00270 -0.0728 0.2551 1.0000
4.500 0.9134 0.00862 0.00284 -0.0729 0.2483 1.0000
4.750 0.9406 0.00881 0.00298 -0.0729 0.2402 1.0000
5.000 0.9679 0.00898 0.00313 -0.0730 0.2320 1.0000
5.250 0.9951 0.00917 0.00330 -0.0730 0.2251 1.0000
5.500 1.0216 0.00944 0.00350 -0.0730 0.2116 1.0000
5.750 1.0473 0.00980 0.00374 -0.0728 0.1887 1.0000
6.000 1.0682 0.01073 0.00431 -0.0721 0.1258 1.0000
6.250 1.0934 0.01112 0.00463 -0.0719 0.1125 1.0000
6.500 1.1188 0.01146 0.00494 -0.0717 0.1040 1.0000
6.750 1.1446 0.01174 0.00520 -0.0716 0.0960 1.0000
7.000 1.1668 0.01243 0.00570 -0.0710 0.0639 1.0000
7.250 1.1905 0.01291 0.00613 -0.0706 0.0506 1.0000
7.500 1.2145 0.01334 0.00653 -0.0702 0.0416 1.0000
7.750 1.2348 0.01416 0.00720 -0.0693 0.0169 1.0000
8.000 1.2581 0.01461 0.00767 -0.0688 0.0131 1.0000
8.250 1.2816 0.01503 0.00811 -0.0683 0.0110 1.0000
8.500 1.3050 0.01543 0.00854 -0.0679 0.0100 1.0000
8.750 1.3274 0.01589 0.00903 -0.0673 0.0089 1.0000
9.000 1.3490 0.01642 0.00959 -0.0665 0.0079 1.0000
9.250 1.3712 0.01686 0.01008 -0.0659 0.0075 1.0000
9.500 1.3925 0.01735 0.01061 -0.0652 0.0070 1.0000
9.750 1.4129 0.01787 0.01117 -0.0643 0.0065 1.0000
10.000 1.4323 0.01846 0.01178 -0.0633 0.0060 1.0000
10.250 1.4495 0.01916 0.01254 -0.0620 0.0055 1.0000
10.500 1.4678 0.01973 0.01317 -0.0609 0.0053 1.0000
10.750 1.4842 0.02036 0.01385 -0.0594 0.0051 1.0000
11.000 1.4972 0.02103 0.01458 -0.0574 0.0048 1.0000
11.250 1.5090 0.02178 0.01539 -0.0554 0.0046 1.0000
11.500 1.5202 0.02262 0.01629 -0.0534 0.0044 1.0000
11.750 1.5305 0.02357 0.01730 -0.0516 0.0043 1.0000
12.000 1.5395 0.02467 0.01846 -0.0497 0.0041 1.0000
12.250 1.5463 0.02601 0.01989 -0.0479 0.0039 1.0000
12.500 1.5500 0.02770 0.02168 -0.0461 0.0038 1.0000
12.750 1.5573 0.02921 0.02328 -0.0449 0.0037 1.0000
13.000 1.5634 0.03093 0.02509 -0.0438 0.0036 1.0000
13.250 1.5682 0.03287 0.02711 -0.0429 0.0036 1.0000
13.500 1.5720 0.03498 0.02932 -0.0422 0.0035 1.0000
13.750 1.5750 0.03727 0.03171 -0.0416 0.0034 1.0000
14.000 1.5768 0.03978 0.03432 -0.0412 0.0033 1.0000
14.250 1.5772 0.04256 0.03719 -0.0411 0.0032 1.0000
14.500 1.5770 0.04552 0.04024 -0.0411 0.0031 1.0000
14.750 1.5749 0.04878 0.04361 -0.0413 0.0031 1.0000
15.000 1.5722 0.05217 0.04710 -0.0416 0.0030 1.0000
15.250 1.5671 0.05590 0.05094 -0.0420 0.0029 1.0000
15.500 1.5610 0.05985 0.05500 -0.0425 0.0029 1.0000
15.750 1.5536 0.06405 0.05930 -0.0432 0.0028 1.0000
16.000 1.5442 0.06870 0.06406 -0.0442 0.0028 1.0000
16.250 1.5346 0.07349 0.06895 -0.0453 0.0028 1.0000
16.500 1.5229 0.07868 0.07425 -0.0467 0.0027 1.0000
16.750 1.5114 0.08400 0.07969 -0.0482 0.0027 1.0000
17.000 1.4984 0.08968 0.08548 -0.0499 0.0027 1.0000
17.250 1.4849 0.09550 0.09141 -0.0517 0.0027 1.0000
17.500 1.4716 0.10139 0.09741 -0.0537 0.0026 1.0000
17.750 1.4576 0.10750 0.10363 -0.0559 0.0026 1.0000
18.000 1.4440 0.11358 0.10981 -0.0581 0.0026 1.0000
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