GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.5 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe584-il-1000000.txt Download as CSV file: xf-goe584-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0965 0.03224 0.02933 -0.1052 1.0000 0.0198
-15.500 -1.1128 0.03018 0.02715 -0.1017 1.0000 0.0201
-15.250 -1.1150 0.02851 0.02535 -0.0992 1.0000 0.0204
-15.000 -1.1126 0.02712 0.02386 -0.0968 1.0000 0.0207
-14.750 -1.1071 0.02593 0.02255 -0.0944 1.0000 0.0211
-14.500 -1.0995 0.02493 0.02144 -0.0920 1.0000 0.0215
-14.250 -1.0976 0.02365 0.02008 -0.0888 1.0000 0.0221
-14.000 -1.0699 0.02254 0.01892 -0.0902 0.9983 0.0229
-13.750 -1.0382 0.02165 0.01796 -0.0919 0.9957 0.0237
-13.500 -1.0070 0.02080 0.01701 -0.0934 0.9927 0.0245
-13.250 -0.9773 0.02000 0.01608 -0.0945 0.9886 0.0251
-13.000 -0.9464 0.01912 0.01518 -0.0960 0.9847 0.0262
-12.750 -0.9135 0.01866 0.01470 -0.0973 0.9810 0.0271
-12.500 -0.8822 0.01823 0.01422 -0.0983 0.9745 0.0281
-12.250 -0.8455 0.01777 0.01365 -0.1003 0.9706 0.0289
-12.000 -0.8123 0.01716 0.01302 -0.1019 0.9624 0.0301
-11.750 -0.7733 0.01699 0.01286 -0.1042 0.9549 0.0310
-11.500 -0.7385 0.01680 0.01261 -0.1057 0.9413 0.0318
-11.250 -0.7077 0.01655 0.01225 -0.1063 0.9239 0.0327
-11.000 -0.6811 0.01635 0.01191 -0.1061 0.9050 0.0333
-10.750 -0.6587 0.01589 0.01133 -0.1052 0.8875 0.0342
-10.250 -0.6075 0.01593 0.01128 -0.1040 0.8601 0.0356
-10.000 -0.5820 0.01588 0.01117 -0.1035 0.8494 0.0362
-9.750 -0.5572 0.01575 0.01094 -0.1028 0.8392 0.0370
-9.500 -0.5316 0.01563 0.01074 -0.1023 0.8303 0.0378
-9.250 -0.5059 0.01563 0.01062 -0.1017 0.8214 0.0383
-9.000 -0.4837 0.01483 0.00972 -0.1009 0.8135 0.0393
-8.750 -0.4585 0.01463 0.00948 -0.1004 0.8057 0.0399
-8.500 -0.4322 0.01456 0.00939 -0.1000 0.7986 0.0405
-8.250 -0.4062 0.01446 0.00924 -0.0995 0.7909 0.0412
-8.000 -0.3801 0.01435 0.00906 -0.0991 0.7841 0.0420
-7.750 -0.3542 0.01411 0.00875 -0.0986 0.7771 0.0428
-7.500 -0.3282 0.01396 0.00850 -0.0982 0.7701 0.0435
-7.250 -0.3013 0.01390 0.00838 -0.0978 0.7632 0.0440
-7.000 -0.2777 0.01304 0.00740 -0.0971 0.7561 0.0450
-6.750 -0.2521 0.01267 0.00700 -0.0967 0.7497 0.0458
-6.500 -0.2255 0.01248 0.00679 -0.0964 0.7427 0.0465
-6.250 -0.1993 0.01227 0.00652 -0.0959 0.7357 0.0472
-6.000 -0.1725 0.01207 0.00629 -0.0956 0.7288 0.0480
-5.750 -0.1460 0.01185 0.00601 -0.0952 0.7217 0.0488
-5.500 -0.1194 0.01161 0.00570 -0.0948 0.7153 0.0495
-5.250 -0.0925 0.01138 0.00542 -0.0945 0.7082 0.0501
-5.000 -0.0657 0.01129 0.00526 -0.0941 0.7012 0.0506
-4.750 -0.0392 0.01090 0.00482 -0.0937 0.6945 0.0512
-4.500 -0.0143 0.01033 0.00421 -0.0931 0.6877 0.0522
-4.250 0.0121 0.01006 0.00391 -0.0927 0.6814 0.0530
-4.000 0.0389 0.00986 0.00369 -0.0924 0.6747 0.0538
-3.500 0.0927 0.00955 0.00333 -0.0917 0.6619 0.0555
-3.250 0.1195 0.00940 0.00315 -0.0914 0.6555 0.0564
-3.000 0.1464 0.00927 0.00297 -0.0910 0.6494 0.0571
-2.750 0.1737 0.00914 0.00282 -0.0907 0.6432 0.0578
-2.500 0.2006 0.00905 0.00269 -0.0904 0.6369 0.0583
-2.250 0.2275 0.00891 0.00252 -0.0901 0.6311 0.0590
-2.000 0.2538 0.00867 0.00225 -0.0896 0.6246 0.0607
-1.750 0.2803 0.00858 0.00213 -0.0892 0.6178 0.0623
-1.500 0.3078 0.00847 0.00202 -0.0890 0.6117 0.0635
-1.250 0.3349 0.00841 0.00193 -0.0887 0.6055 0.0650
-1.000 0.3620 0.00837 0.00187 -0.0884 0.5998 0.0664
-0.750 0.3897 0.00831 0.00180 -0.0882 0.5943 0.0676
-0.500 0.4165 0.00823 0.00170 -0.0879 0.5885 0.0706
-0.250 0.4435 0.00818 0.00166 -0.0876 0.5831 0.0746
0.000 0.4710 0.00812 0.00161 -0.0874 0.5776 0.0806
0.250 0.4972 0.00798 0.00158 -0.0870 0.5719 0.1147
0.500 0.5228 0.00778 0.00160 -0.0865 0.5667 0.1930
0.750 0.5494 0.00764 0.00162 -0.0862 0.5610 0.2436
1.000 0.5747 0.00747 0.00165 -0.0857 0.5553 0.3269
1.250 0.5991 0.00721 0.00169 -0.0851 0.5498 0.4445
1.500 0.6172 0.00654 0.00177 -0.0832 0.5446 0.7126
1.750 0.6756 0.00612 0.00196 -0.0895 0.5374 0.9697
2.000 0.7243 0.00622 0.00203 -0.0940 0.5312 0.9887
2.250 0.7705 0.00632 0.00208 -0.0979 0.5241 0.9970
2.500 0.8105 0.00641 0.00212 -0.1005 0.5174 1.0000
2.750 0.8349 0.00647 0.00217 -0.0997 0.5109 1.0000
3.000 0.8584 0.00658 0.00223 -0.0988 0.5041 1.0000
3.250 0.8827 0.00665 0.00228 -0.0980 0.4964 1.0000
3.750 0.9299 0.00687 0.00243 -0.0961 0.4770 1.0000
4.000 0.9531 0.00701 0.00251 -0.0952 0.4657 1.0000
4.250 0.9759 0.00717 0.00261 -0.0941 0.4544 1.0000
4.500 0.9999 0.00728 0.00271 -0.0933 0.4448 1.0000
4.750 1.0230 0.00744 0.00283 -0.0923 0.4344 1.0000
5.000 1.0455 0.00763 0.00296 -0.0912 0.4223 1.0000
5.250 1.0681 0.00781 0.00309 -0.0902 0.4086 1.0000
5.500 1.0907 0.00800 0.00324 -0.0891 0.3958 1.0000
5.750 1.1128 0.00821 0.00340 -0.0880 0.3826 1.0000
6.000 1.1345 0.00845 0.00358 -0.0869 0.3694 1.0000
6.250 1.1557 0.00870 0.00378 -0.0856 0.3556 1.0000
6.500 1.1765 0.00898 0.00400 -0.0843 0.3415 1.0000
6.750 1.1967 0.00927 0.00422 -0.0829 0.3271 1.0000
7.000 1.2164 0.00959 0.00447 -0.0814 0.3114 1.0000
7.500 1.2556 0.01021 0.00498 -0.0785 0.2833 1.0000
7.750 1.2750 0.01052 0.00524 -0.0770 0.2702 1.0000
8.000 1.2935 0.01085 0.00552 -0.0754 0.2571 1.0000
8.250 1.3111 0.01121 0.00583 -0.0736 0.2435 1.0000
8.500 1.3272 0.01161 0.00616 -0.0716 0.2283 1.0000
8.750 1.3403 0.01203 0.00651 -0.0690 0.2141 1.0000
9.000 1.3514 0.01248 0.00690 -0.0661 0.1990 1.0000
9.250 1.3629 0.01296 0.00731 -0.0633 0.1851 1.0000
9.500 1.3744 0.01348 0.00778 -0.0607 0.1716 1.0000
9.750 1.3851 0.01408 0.00831 -0.0581 0.1578 1.0000
10.000 1.3954 0.01474 0.00890 -0.0555 0.1445 1.0000
10.250 1.4061 0.01542 0.00954 -0.0532 0.1339 1.0000
10.500 1.4183 0.01607 0.01016 -0.0512 0.1253 1.0000
10.750 1.4305 0.01677 0.01085 -0.0493 0.1182 1.0000
11.000 1.4430 0.01750 0.01157 -0.0476 0.1123 1.0000
11.250 1.4543 0.01833 0.01240 -0.0458 0.1048 1.0000
11.500 1.4647 0.01927 0.01331 -0.0441 0.0979 1.0000
11.750 1.4767 0.02017 0.01421 -0.0427 0.0914 1.0000
12.000 1.4855 0.02132 0.01533 -0.0411 0.0830 1.0000
12.250 1.4911 0.02275 0.01670 -0.0394 0.0704 1.0000
12.500 1.4867 0.02499 0.01879 -0.0372 0.0496 1.0000
12.750 1.4800 0.02751 0.02122 -0.0350 0.0345 1.0000
13.000 1.4824 0.02942 0.02314 -0.0336 0.0298 1.0000
13.250 1.4861 0.03128 0.02503 -0.0324 0.0275 1.0000
13.500 1.4915 0.03303 0.02683 -0.0314 0.0259 1.0000
13.750 1.4968 0.03483 0.02869 -0.0305 0.0247 1.0000
14.000 1.4996 0.03690 0.03080 -0.0296 0.0235 1.0000
14.250 1.5006 0.03919 0.03315 -0.0287 0.0224 1.0000
14.500 1.5067 0.04107 0.03510 -0.0281 0.0219 1.0000
14.750 1.5115 0.04311 0.03720 -0.0276 0.0211 1.0000
15.000 1.5147 0.04534 0.03948 -0.0271 0.0204 1.0000
15.250 1.5154 0.04788 0.04208 -0.0266 0.0198 1.0000
15.500 1.5128 0.05084 0.04512 -0.0262 0.0191 1.0000
15.750 1.5127 0.05359 0.04795 -0.0260 0.0187 1.0000
16.000 1.5155 0.05606 0.05048 -0.0258 0.0183 1.0000
16.250 1.5160 0.05883 0.05333 -0.0257 0.0180 1.0000
16.500 1.5165 0.06163 0.05620 -0.0257 0.0175 1.0000
16.750 1.5156 0.06463 0.05927 -0.0258 0.0171 1.0000
17.000 1.5124 0.06796 0.06267 -0.0259 0.0167 1.0000
17.250 1.5078 0.07152 0.06630 -0.0262 0.0165 1.0000
17.500 1.4991 0.07567 0.07054 -0.0267 0.0161 1.0000
17.750 1.4850 0.08060 0.07557 -0.0273 0.0157 1.0000
18.000 1.4815 0.08417 0.07923 -0.0279 0.0156 1.0000
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Polar data table (+)
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