GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 200,000 Max Cl/Cd: 70.32 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe585-il-200000.txt Download as CSV file: xf-goe585-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3921 0.08673 0.08321 -0.0264 1.0000 0.0553
-7.750 -0.3994 0.08423 0.08077 -0.0266 1.0000 0.0571
-7.500 -0.4165 0.08138 0.07802 -0.0307 1.0000 0.0592
-7.250 -0.4253 0.07722 0.07381 -0.0385 1.0000 0.0600
-7.000 -0.4295 0.07229 0.06894 -0.0368 1.0000 0.0608
-6.750 -0.4244 0.07096 0.06769 -0.0311 1.0000 0.0622
-6.500 -0.4213 0.06909 0.06585 -0.0287 1.0000 0.0637
-6.250 -0.4193 0.06664 0.06341 -0.0280 1.0000 0.0655
-6.000 -0.4162 0.06360 0.06034 -0.0287 1.0000 0.0683
-5.750 -0.4105 0.05617 0.05250 -0.0368 1.0000 0.0734
-5.500 -0.4044 0.05386 0.05029 -0.0343 1.0000 0.0744
-5.250 -0.3968 0.05210 0.04856 -0.0322 1.0000 0.0758
-5.000 -0.3876 0.05032 0.04676 -0.0308 1.0000 0.0787
-4.750 -0.3469 0.04408 0.04007 -0.0389 0.9953 0.0884
-4.500 -0.3158 0.04167 0.03765 -0.0412 0.9910 0.0917
-4.250 -0.2767 0.03722 0.03266 -0.0464 0.9858 0.1025
-4.000 -0.2441 0.03506 0.03052 -0.0485 0.9816 0.1063
-3.750 -0.2057 0.02341 0.01675 -0.0494 0.9775 0.0602
-3.500 -0.1700 0.02108 0.01403 -0.0512 0.9736 0.0605
-3.250 -0.1320 0.01919 0.01192 -0.0535 0.9709 0.0623
-3.000 -0.1006 0.01807 0.01064 -0.0541 0.9639 0.0632
-2.750 -0.0602 0.01708 0.00953 -0.0564 0.9595 0.0647
-2.500 -0.0206 0.01620 0.00858 -0.0584 0.9521 0.0668
-2.250 0.0256 0.01544 0.00775 -0.0616 0.9455 0.0714
-2.000 0.0652 0.01444 0.00678 -0.0636 0.9380 0.0757
-1.750 0.1068 0.01376 0.00614 -0.0660 0.9320 0.0832
-1.500 0.1512 0.01295 0.00547 -0.0690 0.9288 0.1052
-1.250 0.1816 0.01226 0.00507 -0.0693 0.9193 0.1731
-1.000 0.2209 0.01152 0.00476 -0.0715 0.9143 0.2737
-0.750 0.2477 0.01077 0.00459 -0.0712 0.9037 0.4329
-0.500 0.3413 0.00917 0.00437 -0.0840 0.9059 1.0000
-0.250 0.3755 0.00902 0.00409 -0.0848 0.8946 1.0000
0.000 0.4068 0.00891 0.00386 -0.0849 0.8815 1.0000
0.250 0.4341 0.00884 0.00369 -0.0843 0.8660 1.0000
0.500 0.4598 0.00881 0.00357 -0.0833 0.8492 1.0000
0.750 0.4849 0.00879 0.00346 -0.0822 0.8312 1.0000
1.000 0.5102 0.00878 0.00335 -0.0812 0.8123 1.0000
1.250 0.5357 0.00879 0.00325 -0.0801 0.7926 1.0000
1.500 0.5596 0.00884 0.00320 -0.0789 0.7704 1.0000
1.750 0.5843 0.00893 0.00315 -0.0777 0.7479 1.0000
2.000 0.6077 0.00905 0.00315 -0.0764 0.7222 1.0000
2.250 0.6306 0.00920 0.00319 -0.0749 0.6941 1.0000
2.500 0.6528 0.00939 0.00323 -0.0734 0.6622 1.0000
2.750 0.6744 0.00961 0.00329 -0.0717 0.6251 1.0000
3.000 0.6948 0.00988 0.00336 -0.0699 0.5790 1.0000
3.250 0.7141 0.01026 0.00348 -0.0679 0.5257 1.0000
3.500 0.7330 0.01073 0.00365 -0.0660 0.4784 1.0000
3.750 0.7533 0.01121 0.00390 -0.0644 0.4433 1.0000
4.000 0.7744 0.01170 0.00419 -0.0630 0.4174 1.0000
4.250 0.7967 0.01212 0.00452 -0.0619 0.3956 1.0000
4.500 0.8192 0.01256 0.00485 -0.0609 0.3771 1.0000
4.750 0.8420 0.01299 0.00519 -0.0599 0.3607 1.0000
5.000 0.8652 0.01340 0.00555 -0.0589 0.3460 1.0000
5.250 0.8887 0.01382 0.00595 -0.0581 0.3331 1.0000
5.500 0.9121 0.01425 0.00634 -0.0572 0.3210 1.0000
5.750 0.9351 0.01465 0.00671 -0.0563 0.3083 1.0000
6.000 0.9578 0.01502 0.00706 -0.0554 0.2951 1.0000
6.250 0.9805 0.01538 0.00740 -0.0544 0.2830 1.0000
6.500 1.0038 0.01571 0.00781 -0.0536 0.2725 1.0000
6.750 1.0268 0.01612 0.00824 -0.0527 0.2630 1.0000
7.000 1.0495 0.01653 0.00865 -0.0518 0.2534 1.0000
7.250 1.0721 0.01683 0.00908 -0.0508 0.2430 1.0000
7.500 1.0938 0.01716 0.00945 -0.0497 0.2311 1.0000
7.750 1.1145 0.01741 0.00975 -0.0486 0.2167 1.0000
8.000 1.1352 0.01768 0.01009 -0.0474 0.2015 1.0000
8.250 1.1557 0.01801 0.01048 -0.0462 0.1858 1.0000
8.500 1.1752 0.01842 0.01089 -0.0449 0.1673 1.0000
8.750 1.1944 0.01891 0.01137 -0.0435 0.1408 1.0000
9.000 1.2100 0.01980 0.01210 -0.0418 0.1044 1.0000
9.250 1.2194 0.02130 0.01336 -0.0392 0.0766 1.0000
9.500 1.2275 0.02286 0.01488 -0.0364 0.0595 1.0000
9.750 1.2335 0.02445 0.01647 -0.0333 0.0504 1.0000
10.000 1.2414 0.02571 0.01778 -0.0304 0.0451 1.0000
10.250 1.2432 0.02737 0.01946 -0.0268 0.0419 1.0000
10.500 1.2525 0.02849 0.02071 -0.0242 0.0387 1.0000
10.750 1.2592 0.02977 0.02204 -0.0217 0.0362 1.0000
11.000 1.2612 0.03182 0.02409 -0.0189 0.0343 1.0000
11.250 1.2693 0.03345 0.02586 -0.0167 0.0331 1.0000
11.500 1.2776 0.03509 0.02765 -0.0146 0.0319 1.0000
11.750 1.2852 0.03686 0.02955 -0.0127 0.0307 1.0000
12.000 1.2922 0.03869 0.03150 -0.0110 0.0297 1.0000
12.250 1.2974 0.04049 0.03337 -0.0094 0.0285 1.0000
12.500 1.3036 0.04294 0.03586 -0.0080 0.0274 1.0000
12.750 1.3067 0.04592 0.03904 -0.0066 0.0266 1.0000
13.000 1.3061 0.04842 0.04179 -0.0051 0.0262 1.0000
13.250 1.3036 0.05128 0.04488 -0.0039 0.0259 1.0000
13.500 1.2987 0.05449 0.04834 -0.0030 0.0256 1.0000
13.750 1.2917 0.05806 0.05215 -0.0025 0.0254 1.0000
14.000 1.2815 0.06211 0.05643 -0.0026 0.0253 1.0000
14.250 1.2691 0.06659 0.06116 -0.0033 0.0252 1.0000
14.500 1.2542 0.07164 0.06644 -0.0047 0.0251 1.0000
14.750 1.2373 0.07730 0.07233 -0.0068 0.0252 1.0000
15.000 1.2187 0.08360 0.07884 -0.0098 0.0253 1.0000
15.250 1.1977 0.09075 0.08621 -0.0138 0.0253 1.0000
15.500 1.1758 0.09867 0.09433 -0.0185 0.0255 1.0000
15.750 1.1528 0.10738 0.10322 -0.0240 0.0257 1.0000
16.000 1.1291 0.11678 0.11279 -0.0301 0.0260 1.0000
16.250 1.1039 0.12708 0.12323 -0.0368 0.0263 1.0000
16.500 1.0776 0.13827 0.13452 -0.0438 0.0267 1.0000
16.750 0.9669 0.18232 0.17868 -0.0687 0.0338 1.0000
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Polar data table (+)
Polar graphs
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