GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 50,000 Max Cl/Cd: 46.45 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe427-il-50000-n5.txt Download as CSV file: xf-goe427-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3283 0.11291 0.10608 -0.0279 1.0000 0.0550
-8.250 -0.3335 0.11213 0.10542 -0.0276 1.0000 0.0554
-8.000 -0.3391 0.11131 0.10472 -0.0272 1.0000 0.0556
-7.750 -0.3407 0.11020 0.10371 -0.0282 1.0000 0.0559
-7.500 -0.3400 0.10886 0.10247 -0.0298 1.0000 0.0560
-7.250 -0.3343 0.10275 0.09643 -0.0264 1.0000 0.0570
-7.000 -0.3297 0.09855 0.09226 -0.0240 1.0000 0.0586
-6.750 -0.3276 0.09589 0.08967 -0.0231 1.0000 0.0603
-6.500 -0.3260 0.09354 0.08739 -0.0227 1.0000 0.0627
-6.250 -0.3237 0.09140 0.08532 -0.0230 1.0000 0.0653
-6.000 -0.3187 0.08987 0.08384 -0.0256 1.0000 0.0686
-5.750 -0.3061 0.08899 0.08296 -0.0315 1.0000 0.0699
-5.500 -0.3054 0.08460 0.07867 -0.0284 1.0000 0.0715
-5.250 -0.3023 0.08144 0.07557 -0.0262 1.0000 0.0748
-5.000 -0.2919 0.07898 0.07311 -0.0278 1.0000 0.0799
-4.750 -0.2636 0.07730 0.07130 -0.0367 1.0000 0.0838
-4.500 -0.2638 0.07322 0.06730 -0.0328 1.0000 0.0859
-4.250 -0.2525 0.07028 0.06437 -0.0330 1.0000 0.0901
-4.000 -0.2134 0.06832 0.06219 -0.0425 1.0000 0.0971
-3.750 -0.2093 0.06435 0.05831 -0.0399 1.0000 0.0995
-3.500 -0.1871 0.06122 0.05511 -0.0421 0.9987 0.1056
-3.250 -0.1419 0.05719 0.05092 -0.0496 0.9920 0.1168
-2.750 -0.0301 0.04748 0.04038 -0.0666 0.9808 0.0670
-2.500 0.0303 0.04275 0.03495 -0.0745 0.9764 0.0559
-2.250 0.0637 0.03980 0.03191 -0.0776 0.9703 0.0603
-2.000 0.1078 0.03687 0.02854 -0.0819 0.9649 0.0639
-1.750 0.1512 0.03388 0.02498 -0.0854 0.9591 0.0640
-1.500 0.1959 0.03154 0.02198 -0.0890 0.9543 0.0727
-1.250 0.2320 0.02974 0.01972 -0.0907 0.9466 0.0765
-1.000 0.2744 0.02799 0.01735 -0.0932 0.9412 0.0797
-0.750 0.3089 0.02680 0.01564 -0.0943 0.9328 0.0849
-0.500 0.3482 0.02619 0.01472 -0.0965 0.9257 0.1008
-0.250 0.3840 0.02545 0.01363 -0.0978 0.9170 0.1068
0.000 0.4193 0.02482 0.01279 -0.0990 0.9081 0.1152
0.250 0.4581 0.02421 0.01208 -0.1009 0.9003 0.1333
0.500 0.4906 0.02368 0.01170 -0.1019 0.8895 0.1807
0.750 0.5253 0.02171 0.01143 -0.1035 0.8799 1.0000
1.000 0.5617 0.02177 0.01110 -0.1048 0.8694 1.0000
1.250 0.5991 0.02177 0.01086 -0.1063 0.8589 1.0000
1.500 0.6315 0.02180 0.01075 -0.1068 0.8462 1.0000
1.750 0.6637 0.02180 0.01067 -0.1073 0.8332 1.0000
2.000 0.6957 0.02180 0.01061 -0.1077 0.8198 1.0000
2.250 0.7274 0.02180 0.01057 -0.1080 0.8061 1.0000
2.500 0.7585 0.02181 0.01062 -0.1082 0.7922 1.0000
2.750 0.7893 0.02184 0.01068 -0.1083 0.7780 1.0000
3.000 0.8196 0.02191 0.01079 -0.1083 0.7637 1.0000
3.250 0.8494 0.02200 0.01096 -0.1082 0.7491 1.0000
3.500 0.8788 0.02212 0.01122 -0.1081 0.7342 1.0000
3.750 0.9076 0.02228 0.01150 -0.1079 0.7192 1.0000
4.000 0.9361 0.02246 0.01182 -0.1076 0.7040 1.0000
4.250 0.9640 0.02269 0.01227 -0.1072 0.6888 1.0000
4.500 0.9897 0.02302 0.01279 -0.1065 0.6725 1.0000
4.750 1.0151 0.02339 0.01337 -0.1058 0.6563 1.0000
5.000 1.0405 0.02344 0.01359 -0.1045 0.6330 1.0000
5.250 1.0607 0.02332 0.01358 -0.1017 0.5950 1.0000
5.500 1.0825 0.02337 0.01364 -0.0994 0.5581 1.0000
5.750 1.1028 0.02374 0.01412 -0.0973 0.5247 1.0000
6.000 1.1177 0.02421 0.01456 -0.0943 0.4755 1.0000
6.250 1.1272 0.02488 0.01520 -0.0906 0.4096 1.0000
6.500 1.1334 0.02601 0.01594 -0.0867 0.3095 1.0000
6.750 1.1304 0.02877 0.01765 -0.0826 0.1526 1.0000
7.000 1.1327 0.03174 0.02001 -0.0797 0.0943 1.0000
7.250 1.1385 0.03407 0.02228 -0.0769 0.0768 1.0000
7.500 1.1441 0.03621 0.02450 -0.0741 0.0645 1.0000
7.750 1.1507 0.03819 0.02668 -0.0713 0.0561 1.0000
8.000 1.1570 0.04039 0.02901 -0.0685 0.0501 1.0000
8.250 1.1664 0.04254 0.03128 -0.0663 0.0445 1.0000
8.500 1.1889 0.04527 0.03415 -0.0649 0.0405 1.0000
8.750 1.2164 0.04810 0.03720 -0.0646 0.0352 1.0000
9.000 1.2543 0.05264 0.04212 -0.0655 0.0327 1.0000
9.250 1.2696 0.05614 0.04622 -0.0637 0.0314 1.0000
9.500 1.2766 0.05967 0.05027 -0.0615 0.0298 1.0000
9.750 1.2780 0.06320 0.05424 -0.0590 0.0285 1.0000
10.000 1.2744 0.06667 0.05808 -0.0562 0.0277 1.0000
10.250 1.2668 0.07027 0.06202 -0.0534 0.0274 1.0000
10.500 1.2556 0.07402 0.06609 -0.0510 0.0273 1.0000
10.750 1.2416 0.07800 0.07038 -0.0492 0.0273 1.0000
11.000 1.2254 0.08234 0.07500 -0.0481 0.0274 1.0000
11.250 1.2076 0.08710 0.08002 -0.0481 0.0275 1.0000
11.500 1.1889 0.09237 0.08552 -0.0491 0.0277 1.0000
11.750 1.1695 0.09826 0.09162 -0.0512 0.0280 1.0000
12.000 1.1498 0.10483 0.09836 -0.0544 0.0282 1.0000
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Polar data table (+)
Polar graphs
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