GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 500,000 Max Cl/Cd: 112.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe584-il-500000.txt Download as CSV file: xf-goe584-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3013 0.10239 0.10004 -0.0461 1.0000 0.0393
-10.500 -0.2917 0.10103 0.09871 -0.0453 1.0000 0.0401
-10.250 -0.5346 0.03224 0.02880 -0.1061 0.9501 0.0388
-10.000 -0.4926 0.03321 0.02993 -0.1080 0.9418 0.0394
-9.750 -0.4445 0.03577 0.03272 -0.1089 0.9334 0.0398
-9.250 -0.2647 0.06828 0.06594 -0.0805 0.9508 0.0438
-9.000 -0.4172 0.02757 0.02332 -0.1078 0.8782 0.0438
-8.750 -0.4062 0.02538 0.02080 -0.1065 0.8659 0.0450
-8.500 -0.3814 0.02533 0.02076 -0.1060 0.8559 0.0457
-8.250 -0.3560 0.02542 0.02089 -0.1056 0.8461 0.0465
-8.000 -0.3343 0.02481 0.02014 -0.1048 0.8373 0.0476
-7.750 -0.3166 0.02340 0.01846 -0.1036 0.8279 0.0490
-7.500 -0.2968 0.02244 0.01712 -0.1024 0.8198 0.0504
-7.250 -0.2796 0.02055 0.01492 -0.1012 0.8112 0.0516
-7.000 -0.2562 0.01977 0.01406 -0.1007 0.8039 0.0526
-6.750 -0.2311 0.01944 0.01374 -0.1003 0.7961 0.0536
-6.500 -0.2065 0.01896 0.01317 -0.0997 0.7887 0.0548
-6.250 -0.1826 0.01821 0.01226 -0.0990 0.7814 0.0559
-6.000 -0.1582 0.01759 0.01145 -0.0983 0.7739 0.0570
-5.750 -0.1328 0.01719 0.01087 -0.0977 0.7674 0.0580
-5.500 -0.1071 0.01695 0.01048 -0.0971 0.7599 0.0586
-5.250 -0.0838 0.01530 0.00865 -0.0965 0.7534 0.0597
-5.000 -0.0582 0.01466 0.00800 -0.0961 0.7463 0.0609
-4.750 -0.0322 0.01425 0.00753 -0.0957 0.7393 0.0619
-4.500 -0.0058 0.01384 0.00704 -0.0953 0.7331 0.0628
-4.250 0.0205 0.01342 0.00657 -0.0949 0.7260 0.0638
-4.000 0.0469 0.01306 0.00612 -0.0944 0.7195 0.0647
-3.750 0.0736 0.01275 0.00577 -0.0940 0.7128 0.0658
-3.500 0.1003 0.01248 0.00543 -0.0936 0.7062 0.0668
-3.250 0.1271 0.01225 0.00512 -0.0932 0.7002 0.0674
-3.000 0.1532 0.01183 0.00468 -0.0928 0.6934 0.0682
-2.750 0.1787 0.01134 0.00415 -0.0922 0.6873 0.0697
-2.500 0.2049 0.01107 0.00387 -0.0918 0.6813 0.0711
-2.250 0.2313 0.01087 0.00367 -0.0914 0.6747 0.0728
-2.000 0.2579 0.01074 0.00348 -0.0910 0.6689 0.0745
-1.750 0.2845 0.01057 0.00331 -0.0906 0.6627 0.0760
-1.500 0.3112 0.01044 0.00315 -0.0902 0.6563 0.0775
-1.250 0.3376 0.01030 0.00295 -0.0897 0.6504 0.0794
-1.000 0.3638 0.01010 0.00279 -0.0893 0.6436 0.0828
-0.750 0.3904 0.01001 0.00267 -0.0889 0.6373 0.0868
-0.500 0.4171 0.00993 0.00258 -0.0885 0.6313 0.0923
-0.250 0.4435 0.00978 0.00250 -0.0881 0.6251 0.1061
0.000 0.4684 0.00948 0.00248 -0.0875 0.6195 0.1948
0.250 0.4936 0.00923 0.00250 -0.0870 0.6138 0.2756
0.500 0.5177 0.00889 0.00252 -0.0864 0.6077 0.3987
0.750 0.5345 0.00816 0.00258 -0.0842 0.6025 0.6742
1.000 0.6032 0.00762 0.00277 -0.0923 0.5958 0.9665
1.250 0.6615 0.00773 0.00280 -0.0987 0.5890 0.9946
1.500 0.7022 0.00781 0.00280 -0.1015 0.5828 1.0000
1.750 0.7261 0.00787 0.00284 -0.1006 0.5765 1.0000
2.000 0.7498 0.00796 0.00286 -0.0996 0.5706 1.0000
2.250 0.7738 0.00805 0.00292 -0.0988 0.5646 1.0000
2.500 0.7978 0.00812 0.00298 -0.0979 0.5581 1.0000
3.000 0.8457 0.00832 0.00311 -0.0962 0.5454 1.0000
3.250 0.8695 0.00843 0.00318 -0.0953 0.5388 1.0000
3.500 0.8934 0.00854 0.00327 -0.0944 0.5322 1.0000
3.750 0.9173 0.00864 0.00335 -0.0935 0.5248 1.0000
4.000 0.9408 0.00878 0.00345 -0.0926 0.5176 1.0000
4.250 0.9642 0.00887 0.00354 -0.0916 0.5080 1.0000
4.500 0.9871 0.00900 0.00364 -0.0906 0.4978 1.0000
5.000 1.0324 0.00929 0.00386 -0.0884 0.4758 1.0000
5.250 1.0551 0.00945 0.00400 -0.0874 0.4661 1.0000
5.500 1.0772 0.00963 0.00415 -0.0863 0.4559 1.0000
5.750 1.0998 0.00979 0.00432 -0.0852 0.4446 1.0000
6.000 1.1214 0.01000 0.00449 -0.0840 0.4327 1.0000
6.250 1.1424 0.01023 0.00468 -0.0827 0.4200 1.0000
6.750 1.1836 0.01074 0.00512 -0.0800 0.3936 1.0000
7.000 1.2037 0.01102 0.00537 -0.0786 0.3803 1.0000
7.250 1.2229 0.01133 0.00564 -0.0771 0.3668 1.0000
7.500 1.2411 0.01167 0.00594 -0.0754 0.3522 1.0000
7.750 1.2580 0.01206 0.00626 -0.0735 0.3364 1.0000
8.000 1.2743 0.01245 0.00660 -0.0715 0.3215 1.0000
8.250 1.2898 0.01286 0.00697 -0.0694 0.3075 1.0000
8.500 1.3026 0.01328 0.00734 -0.0668 0.2951 1.0000
8.750 1.3149 0.01372 0.00774 -0.0641 0.2819 1.0000
9.000 1.3276 0.01416 0.00816 -0.0616 0.2683 1.0000
9.250 1.3398 0.01467 0.00863 -0.0591 0.2547 1.0000
9.500 1.3515 0.01522 0.00914 -0.0567 0.2414 1.0000
9.750 1.3622 0.01585 0.00973 -0.0542 0.2276 1.0000
10.000 1.3721 0.01656 0.01039 -0.0518 0.2135 1.0000
10.250 1.3810 0.01736 0.01115 -0.0493 0.1990 1.0000
10.500 1.3894 0.01825 0.01199 -0.0470 0.1853 1.0000
10.750 1.3971 0.01922 0.01292 -0.0448 0.1725 1.0000
11.000 1.4043 0.02031 0.01396 -0.0427 0.1610 1.0000
11.250 1.4133 0.02134 0.01499 -0.0409 0.1509 1.0000
11.500 1.4219 0.02246 0.01611 -0.0392 0.1427 1.0000
12.000 1.4374 0.02495 0.01859 -0.0361 0.1270 1.0000
12.250 1.4434 0.02640 0.02003 -0.0346 0.1199 1.0000
12.500 1.4518 0.02772 0.02138 -0.0333 0.1130 1.0000
12.750 1.4574 0.02929 0.02295 -0.0320 0.1057 1.0000
13.000 1.4629 0.03092 0.02458 -0.0308 0.0982 1.0000
13.250 1.4678 0.03264 0.02631 -0.0297 0.0889 1.0000
13.500 1.4667 0.03492 0.02852 -0.0284 0.0751 1.0000
13.750 1.4590 0.03787 0.03135 -0.0270 0.0550 1.0000
14.000 1.4482 0.04125 0.03463 -0.0258 0.0417 1.0000
14.250 1.4426 0.04427 0.03766 -0.0250 0.0367 1.0000
14.500 1.4412 0.04699 0.04044 -0.0243 0.0343 1.0000
14.750 1.4373 0.05005 0.04355 -0.0239 0.0323 1.0000
15.000 1.4336 0.05320 0.04676 -0.0235 0.0309 1.0000
15.250 1.4330 0.05605 0.04972 -0.0233 0.0298 1.0000
15.500 1.4304 0.05921 0.05296 -0.0232 0.0288 1.0000
15.750 1.4239 0.06291 0.05673 -0.0233 0.0277 1.0000
16.000 1.4167 0.06679 0.06069 -0.0236 0.0271 1.0000
16.250 1.4076 0.07101 0.06500 -0.0240 0.0265 1.0000
16.500 1.4055 0.07441 0.06851 -0.0244 0.0260 1.0000
16.750 1.4015 0.07812 0.07232 -0.0249 0.0253 1.0000
17.000 1.3969 0.08195 0.07624 -0.0256 0.0247 1.0000
17.250 1.3914 0.08598 0.08036 -0.0264 0.0243 1.0000
17.500 1.3844 0.09030 0.08477 -0.0273 0.0239 1.0000
17.750 1.3760 0.09489 0.08943 -0.0285 0.0234 1.0000
18.000 1.3663 0.09970 0.09431 -0.0298 0.0230 1.0000
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