GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.11 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe584-il-1000000-n5.txt Download as CSV file: xf-goe584-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 584 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0074 0.03641 0.03360 -0.1038 1.0000 0.0117
-15.000 -1.0435 0.03231 0.02928 -0.1006 1.0000 0.0116
-14.750 -1.0366 0.02888 0.02563 -0.1025 0.9910 0.0119
-14.500 -1.0194 0.02656 0.02314 -0.1040 0.9825 0.0123
-14.250 -0.9948 0.02473 0.02115 -0.1060 0.9746 0.0126
-14.000 -0.9647 0.02322 0.01949 -0.1084 0.9663 0.0130
-13.750 -0.9326 0.02160 0.01772 -0.1113 0.9549 0.0136
-13.500 -0.9008 0.02023 0.01619 -0.1137 0.9375 0.0142
-13.250 -0.8763 0.01928 0.01507 -0.1140 0.9124 0.0149
-13.000 -0.8565 0.01858 0.01419 -0.1131 0.8890 0.0156
-12.750 -0.8374 0.01789 0.01335 -0.1120 0.8704 0.0162
-12.500 -0.8186 0.01716 0.01248 -0.1108 0.8551 0.0171
-12.250 -0.7980 0.01654 0.01175 -0.1098 0.8427 0.0180
-12.000 -0.7763 0.01601 0.01110 -0.1089 0.8320 0.0189
-11.750 -0.7547 0.01544 0.01042 -0.1080 0.8224 0.0200
-11.500 -0.7320 0.01490 0.00981 -0.1073 0.8139 0.0214
-11.000 -0.6850 0.01402 0.00880 -0.1059 0.7986 0.0247
-10.750 -0.6606 0.01367 0.00838 -0.1053 0.7913 0.0266
-10.500 -0.6353 0.01340 0.00808 -0.1049 0.7848 0.0287
-10.250 -0.6097 0.01315 0.00778 -0.1044 0.7776 0.0304
-10.000 -0.5843 0.01290 0.00745 -0.1039 0.7711 0.0317
-9.750 -0.5578 0.01272 0.00726 -0.1036 0.7650 0.0330
-9.500 -0.5311 0.01261 0.00712 -0.1032 0.7579 0.0344
-9.250 -0.5046 0.01247 0.00693 -0.1029 0.7517 0.0356
-9.000 -0.4779 0.01231 0.00671 -0.1026 0.7451 0.0366
-8.750 -0.4516 0.01214 0.00646 -0.1021 0.7385 0.0373
-8.500 -0.4251 0.01194 0.00621 -0.1018 0.7321 0.0380
-8.250 -0.3985 0.01178 0.00602 -0.1015 0.7249 0.0390
-8.000 -0.3715 0.01169 0.00590 -0.1012 0.7187 0.0398
-7.750 -0.3443 0.01158 0.00577 -0.1009 0.7122 0.0406
-7.500 -0.3172 0.01152 0.00565 -0.1006 0.7053 0.0414
-7.250 -0.2901 0.01139 0.00548 -0.1003 0.6987 0.0422
-7.000 -0.2632 0.01127 0.00530 -0.1000 0.6916 0.0429
-6.750 -0.2362 0.01115 0.00513 -0.0997 0.6853 0.0436
-6.500 -0.2087 0.01106 0.00499 -0.0995 0.6790 0.0441
-6.250 -0.1818 0.01095 0.00482 -0.0992 0.6722 0.0444
-6.000 -0.1549 0.01077 0.00458 -0.0989 0.6661 0.0448
-5.750 -0.1293 0.01040 0.00416 -0.0984 0.6593 0.0456
-5.500 -0.1030 0.01018 0.00389 -0.0980 0.6535 0.0462
-5.250 -0.0759 0.01000 0.00368 -0.0977 0.6481 0.0468
-5.000 -0.0490 0.00985 0.00350 -0.0974 0.6418 0.0473
-4.750 -0.0220 0.00974 0.00335 -0.0971 0.6360 0.0479
-4.500 0.0053 0.00960 0.00319 -0.0969 0.6303 0.0485
-4.250 0.0324 0.00948 0.00302 -0.0966 0.6247 0.0490
-4.000 0.0594 0.00937 0.00287 -0.0963 0.6194 0.0495
-3.750 0.0868 0.00924 0.00272 -0.0961 0.6141 0.0501
-3.500 0.1140 0.00915 0.00259 -0.0958 0.6083 0.0507
-3.250 0.1411 0.00906 0.00246 -0.0955 0.6032 0.0512
-3.000 0.1687 0.00897 0.00235 -0.0953 0.5981 0.0517
-2.750 0.1960 0.00889 0.00224 -0.0951 0.5926 0.0521
-2.250 0.2508 0.00878 0.00208 -0.0947 0.5820 0.0529
-2.000 0.2781 0.00873 0.00200 -0.0944 0.5756 0.0533
-1.750 0.3049 0.00864 0.00187 -0.0941 0.5692 0.0542
-1.500 0.3322 0.00856 0.00178 -0.0939 0.5626 0.0553
-1.250 0.3592 0.00852 0.00171 -0.0936 0.5563 0.0565
-1.000 0.3865 0.00847 0.00166 -0.0934 0.5513 0.0577
-0.750 0.4140 0.00843 0.00162 -0.0932 0.5457 0.0589
-0.500 0.4411 0.00842 0.00159 -0.0929 0.5400 0.0601
-0.250 0.4684 0.00840 0.00156 -0.0927 0.5348 0.0616
0.000 0.4959 0.00839 0.00155 -0.0925 0.5294 0.0629
0.250 0.5229 0.00840 0.00154 -0.0923 0.5232 0.0647
0.500 0.5500 0.00838 0.00153 -0.0920 0.5181 0.0704
0.750 0.5772 0.00836 0.00154 -0.0918 0.5122 0.0782
1.000 0.6033 0.00831 0.00156 -0.0915 0.5058 0.1079
1.250 0.6298 0.00822 0.00159 -0.0912 0.5006 0.1533
1.500 0.6564 0.00819 0.00163 -0.0909 0.4939 0.1852
1.750 0.6824 0.00818 0.00168 -0.0905 0.4875 0.2183
2.000 0.7087 0.00810 0.00174 -0.0902 0.4812 0.2692
2.250 0.7336 0.00796 0.00182 -0.0897 0.4744 0.3645
2.500 0.7574 0.00773 0.00190 -0.0890 0.4675 0.4923
2.750 0.7760 0.00725 0.00202 -0.0872 0.4601 0.7277
3.000 0.8405 0.00691 0.00224 -0.0952 0.4508 0.9770
3.250 0.8806 0.00709 0.00235 -0.0979 0.4389 0.9946
3.500 0.9168 0.00727 0.00246 -0.0999 0.4247 1.0000
3.750 0.9388 0.00748 0.00258 -0.0987 0.4080 1.0000
4.000 0.9606 0.00771 0.00272 -0.0975 0.3900 1.0000
4.250 0.9822 0.00794 0.00287 -0.0963 0.3730 1.0000
4.500 1.0035 0.00820 0.00304 -0.0950 0.3555 1.0000
4.750 1.0252 0.00844 0.00320 -0.0939 0.3419 1.0000
5.000 1.0475 0.00865 0.00337 -0.0928 0.3303 1.0000
5.250 1.0694 0.00887 0.00354 -0.0917 0.3188 1.0000
5.500 1.0909 0.00912 0.00373 -0.0905 0.3076 1.0000
5.750 1.1125 0.00935 0.00392 -0.0893 0.2972 1.0000
6.000 1.1345 0.00956 0.00410 -0.0882 0.2885 1.0000
6.500 1.1771 0.01004 0.00451 -0.0859 0.2696 1.0000
6.750 1.1975 0.01031 0.00474 -0.0846 0.2597 1.0000
7.000 1.2170 0.01062 0.00500 -0.0831 0.2482 1.0000
7.250 1.2370 0.01089 0.00524 -0.0817 0.2381 1.0000
7.500 1.2545 0.01126 0.00554 -0.0800 0.2237 1.0000
7.750 1.2682 0.01177 0.00593 -0.0775 0.2035 1.0000
8.000 1.2798 0.01222 0.00630 -0.0747 0.1859 1.0000
8.250 1.2915 0.01267 0.00668 -0.0719 0.1717 1.0000
8.500 1.3034 0.01315 0.00710 -0.0692 0.1581 1.0000
8.750 1.3152 0.01368 0.00756 -0.0666 0.1441 1.0000
9.000 1.3283 0.01418 0.00802 -0.0644 0.1338 1.0000
9.250 1.3402 0.01477 0.00857 -0.0620 0.1237 1.0000
9.500 1.3538 0.01531 0.00909 -0.0601 0.1161 1.0000
9.750 1.3655 0.01599 0.00973 -0.0579 0.1075 1.0000
10.000 1.3794 0.01658 0.01032 -0.0562 0.1019 1.0000
10.250 1.3910 0.01734 0.01105 -0.0543 0.0953 1.0000
10.500 1.4055 0.01798 0.01171 -0.0529 0.0910 1.0000
10.750 1.4163 0.01887 0.01257 -0.0512 0.0845 1.0000
11.000 1.4260 0.01988 0.01355 -0.0494 0.0756 1.0000
11.250 1.4360 0.02093 0.01457 -0.0479 0.0676 1.0000
11.500 1.4307 0.02308 0.01657 -0.0451 0.0424 1.0000
11.750 1.4290 0.02513 0.01856 -0.0430 0.0288 1.0000
12.000 1.4370 0.02652 0.01997 -0.0417 0.0252 1.0000
12.250 1.4450 0.02794 0.02142 -0.0406 0.0226 1.0000
12.500 1.4548 0.02927 0.02278 -0.0396 0.0212 1.0000
12.750 1.4618 0.03082 0.02436 -0.0385 0.0195 1.0000
13.000 1.4699 0.03233 0.02592 -0.0376 0.0182 1.0000
13.250 1.4775 0.03392 0.02755 -0.0367 0.0171 1.0000
13.500 1.4837 0.03564 0.02931 -0.0359 0.0161 1.0000
13.750 1.4900 0.03740 0.03111 -0.0351 0.0153 1.0000
14.000 1.4969 0.03916 0.03292 -0.0344 0.0146 1.0000
14.250 1.5024 0.04108 0.03489 -0.0338 0.0139 1.0000
14.500 1.5066 0.04316 0.03702 -0.0332 0.0132 1.0000
14.750 1.5102 0.04534 0.03926 -0.0326 0.0127 1.0000
15.000 1.5155 0.04740 0.04137 -0.0322 0.0123 1.0000
15.250 1.5193 0.04964 0.04368 -0.0318 0.0119 1.0000
15.500 1.5223 0.05201 0.04610 -0.0315 0.0114 1.0000
15.750 1.5247 0.05445 0.04861 -0.0312 0.0111 1.0000
16.000 1.5251 0.05718 0.05138 -0.0310 0.0105 1.0000
16.500 1.5260 0.06273 0.05707 -0.0308 0.0101 1.0000
16.750 1.5269 0.06548 0.05990 -0.0308 0.0097 1.0000
17.000 1.5258 0.06854 0.06304 -0.0309 0.0096 1.0000
17.250 1.5248 0.07161 0.06618 -0.0310 0.0093 1.0000
17.500 1.5229 0.07485 0.06948 -0.0313 0.0090 1.0000
17.750 1.5196 0.07826 0.07296 -0.0316 0.0088 1.0000
18.000 1.5155 0.08185 0.07662 -0.0320 0.0087 1.0000
18.250 1.5094 0.08577 0.08062 -0.0326 0.0085 1.0000
18.500 1.5034 0.08971 0.08465 -0.0333 0.0082 1.0000
18.750 1.4982 0.09359 0.08861 -0.0340 0.0082 1.0000
19.000 1.4930 0.09752 0.09262 -0.0348 0.0080 1.0000
19.250 1.4863 0.10174 0.09694 -0.0359 0.0079 1.0000
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