GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 500,000 Max Cl/Cd: 42.09 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe780-il-500000-n5.txt Download as CSV file: xf-goe780-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4782 0.10367 0.10148 -0.0433 1.0000 0.0037
-11.000 -0.4802 0.09963 0.09746 -0.0449 1.0000 0.0035
-10.750 -0.4764 0.09368 0.09152 -0.0497 0.9740 0.0035
-10.500 -0.4680 0.08592 0.08375 -0.0585 0.9575 0.0034
-10.250 -0.4545 0.07790 0.07569 -0.0702 0.9409 0.0032
-10.000 -0.4586 0.06659 0.06419 -0.0847 0.9082 0.0033
-9.750 -0.4668 0.06239 0.05973 -0.0868 0.8727 0.0032
-9.500 -0.4847 0.05903 0.05617 -0.0844 0.8534 0.0032
-9.250 -0.4928 0.05729 0.05429 -0.0817 0.8423 0.0029
-9.000 -0.5158 0.05397 0.05079 -0.0761 0.8326 0.0030
-8.750 -0.5295 0.05141 0.04809 -0.0711 0.8260 0.0030
-8.500 -0.5384 0.04843 0.04493 -0.0668 0.8206 0.0029
-8.250 -0.5474 0.04483 0.04110 -0.0619 0.8163 0.0028
-8.000 -0.5520 0.04125 0.03729 -0.0572 0.8124 0.0027
-7.750 -0.5555 0.03722 0.03296 -0.0522 0.8086 0.0027
-7.500 -0.5556 0.03312 0.02851 -0.0472 0.8052 0.0029
-7.250 -0.5559 0.02749 0.02234 -0.0414 0.8023 0.0026
-7.000 -0.5434 0.02387 0.01827 -0.0382 0.7994 0.0032
-6.750 -0.5240 0.02106 0.01502 -0.0365 0.7968 0.0034
-6.500 -0.4993 0.01897 0.01255 -0.0359 0.7945 0.0037
-6.250 -0.4737 0.01734 0.01066 -0.0358 0.7924 0.0042
-6.000 -0.4475 0.01600 0.00908 -0.0358 0.7904 0.0043
-5.750 -0.4235 0.01511 0.00807 -0.0353 0.7884 0.0048
-5.500 -0.4012 0.01418 0.00700 -0.0345 0.7861 0.0047
-5.250 -0.3800 0.01350 0.00624 -0.0334 0.7836 0.0055
-5.000 -0.3594 0.01294 0.00557 -0.0321 0.7811 0.0062
-4.750 -0.3397 0.01236 0.00487 -0.0307 0.7788 0.0070
-4.500 -0.3193 0.01190 0.00432 -0.0294 0.7768 0.0092
-4.250 -0.2976 0.01157 0.00388 -0.0283 0.7750 0.0111
-4.000 -0.2764 0.01121 0.00352 -0.0271 0.7729 0.0198
-3.750 -0.2539 0.01098 0.00333 -0.0263 0.7705 0.0352
-3.500 -0.2306 0.01081 0.00313 -0.0257 0.7682 0.0425
-3.250 -0.2077 0.01062 0.00288 -0.0249 0.7660 0.0511
-3.000 -0.1852 0.01039 0.00268 -0.0241 0.7641 0.0631
-2.750 -0.1630 0.01016 0.00252 -0.0232 0.7622 0.1027
-2.250 -0.1230 0.00945 0.00217 -0.0207 0.7582 0.2237
-2.000 -0.1130 0.00864 0.00196 -0.0175 0.7557 0.3912
-1.750 -0.1187 0.00763 0.00175 -0.0107 0.7531 0.5926
-1.500 -0.1127 0.00715 0.00166 -0.0059 0.7507 0.6992
-1.250 -0.0916 0.00680 0.00173 -0.0044 0.7488 0.7930
-1.000 -0.0603 0.00685 0.00186 -0.0052 0.7472 0.8413
-0.750 -0.0342 0.00693 0.00194 -0.0049 0.7454 0.8623
-0.500 -0.0058 0.00703 0.00207 -0.0051 0.7434 0.8799
-0.250 0.0256 0.00717 0.00222 -0.0060 0.7413 0.8924
0.000 0.0475 0.00719 0.00224 -0.0049 0.7390 0.8988
0.250 0.0773 0.00723 0.00226 -0.0056 0.7370 0.9017
0.500 0.1126 0.00728 0.00230 -0.0075 0.7331 0.9042
0.750 0.1438 0.00731 0.00235 -0.0085 0.7274 0.9071
1.000 0.1681 0.00734 0.00239 -0.0079 0.7235 0.9117
1.250 0.1922 0.00735 0.00242 -0.0073 0.7203 0.9150
1.500 0.2272 0.00740 0.00250 -0.0092 0.7149 0.9164
1.750 0.2611 0.00744 0.00259 -0.0109 0.7091 0.9178
2.000 0.2894 0.00742 0.00256 -0.0111 0.6835 0.9196
2.250 0.3148 0.00748 0.00257 -0.0107 0.6555 0.9221
2.500 0.3097 0.00817 0.00262 -0.0036 0.5043 0.9288
2.750 0.2999 0.01083 0.00374 0.0027 0.0891 0.9336
3.000 0.3197 0.01134 0.00404 0.0039 0.0240 0.9372
3.250 0.3357 0.01161 0.00434 0.0062 0.0144 0.9422
3.500 0.3632 0.01198 0.00479 0.0059 0.0114 0.9432
3.750 0.3864 0.01258 0.00551 0.0065 0.0086 0.9446
4.000 0.4111 0.01304 0.00602 0.0067 0.0076 0.9463
4.250 0.4313 0.01361 0.00666 0.0079 0.0065 0.9487
4.500 0.4356 0.01403 0.00714 0.0126 0.0064 0.9552
4.750 0.4580 0.01490 0.00806 0.0131 0.0059 0.9565
5.000 0.4797 0.01585 0.00907 0.0137 0.0056 0.9581
5.250 0.5040 0.01659 0.00990 0.0140 0.0042 0.9597
5.500 0.5287 0.01774 0.01118 0.0143 0.0040 0.9611
5.750 0.5551 0.01878 0.01231 0.0143 0.0035 0.9621
6.000 0.5874 0.02050 0.01422 0.0135 0.0036 0.9619
6.250 0.6194 0.02265 0.01663 0.0129 0.0036 0.9619
6.500 0.6484 0.02578 0.02013 0.0133 0.0038 0.9623
6.750 0.6689 0.02862 0.02329 0.0150 0.0042 0.9644
7.000 0.6813 0.03165 0.02662 0.0183 0.0044 0.9678
7.250 0.6965 0.03495 0.03022 0.0197 0.0048 0.9692
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Polar data table (+)
Polar graphs
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