GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Reynolds number: 500,000 Max Cl/Cd: 102.16 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe79-il-500000.txt Download as CSV file: xf-goe79-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 79 (PFALZ 11) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3035 0.09740 0.09514 -0.0118 1.0000 0.0184
-7.750 -0.2972 0.09485 0.09262 -0.0127 1.0000 0.0187
-7.500 -0.2915 0.09242 0.09022 -0.0136 1.0000 0.0192
-7.250 -0.2814 0.08987 0.08770 -0.0164 1.0000 0.0195
-7.000 -0.1925 0.07323 0.07126 -0.0299 0.9875 0.0196
-6.750 -0.1762 0.06841 0.06644 -0.0303 0.9793 0.0197
-6.500 -0.1569 0.06410 0.06213 -0.0334 0.9645 0.0199
-6.250 -0.2164 0.07698 0.07487 -0.0318 0.9928 0.0197
-6.000 -0.1909 0.07311 0.07099 -0.0359 0.9844 0.0199
-5.750 -0.1608 0.06948 0.06734 -0.0415 0.9716 0.0202
-5.500 -0.1267 0.06585 0.06367 -0.0480 0.9534 0.0207
-5.250 -0.0900 0.06214 0.05988 -0.0549 0.9313 0.0213
-5.000 -0.0588 0.05894 0.05655 -0.0599 0.9063 0.0220
-4.750 -0.0176 0.05599 0.05341 -0.0673 0.8841 0.0225
-4.250 0.0456 0.04983 0.04693 -0.0757 0.8470 0.0227
-4.000 0.0634 0.04719 0.04423 -0.0760 0.8289 0.0229
-3.750 0.0875 0.04480 0.04173 -0.0775 0.8101 0.0231
-3.500 0.1154 0.04249 0.03931 -0.0798 0.7909 0.0234
-3.250 0.1452 0.04024 0.03691 -0.0821 0.7709 0.0239
-3.000 0.1764 0.03804 0.03454 -0.0845 0.7502 0.0245
-2.750 0.2129 0.03596 0.03223 -0.0871 0.7300 0.0256
-2.500 0.2590 0.03411 0.03001 -0.0903 0.7120 0.0259
-2.250 0.2838 0.03152 0.02733 -0.0916 0.6955 0.0261
-2.000 0.3092 0.02967 0.02539 -0.0926 0.6803 0.0264
-1.750 0.3380 0.02805 0.02364 -0.0937 0.6669 0.0268
-1.500 0.3683 0.02655 0.02199 -0.0948 0.6545 0.0273
-1.000 0.4394 0.02408 0.01896 -0.0961 0.6318 0.0297
-0.750 0.4686 0.02207 0.01682 -0.0972 0.6220 0.0300
-0.500 0.4963 0.02077 0.01546 -0.0980 0.6113 0.0304
-0.250 0.5254 0.01973 0.01431 -0.0985 0.6008 0.0312
0.000 0.5554 0.01880 0.01320 -0.0989 0.5895 0.0325
0.250 0.5894 0.01811 0.01214 -0.0985 0.5782 0.0343
0.500 0.6175 0.01685 0.01085 -0.0992 0.5658 0.0349
0.750 0.6460 0.01610 0.00999 -0.0995 0.5540 0.0358
1.000 0.6753 0.01549 0.00923 -0.0996 0.5414 0.0376
1.250 0.7057 0.01480 0.00830 -0.0994 0.5285 0.0401
1.500 0.7340 0.01419 0.00764 -0.0997 0.5145 0.0417
1.750 0.7632 0.01380 0.00702 -0.0995 0.4986 0.0464
2.000 0.7910 0.01334 0.00650 -0.0996 0.4781 0.0491
2.250 0.8189 0.01303 0.00601 -0.0995 0.4520 0.0553
2.500 0.8459 0.01291 0.00569 -0.0994 0.4145 0.0646
2.750 0.8723 0.01290 0.00548 -0.0993 0.3776 0.0768
3.750 0.9823 0.01246 0.00450 -0.0978 0.3133 0.0515
4.000 1.0100 0.01234 0.00434 -0.0976 0.3041 0.0466
4.500 1.0646 0.01241 0.00439 -0.0974 0.2876 0.0474
4.750 1.0915 0.01254 0.00450 -0.0972 0.2796 0.0472
5.000 1.1189 0.01260 0.00458 -0.0970 0.2723 0.0484
5.250 1.1457 0.01277 0.00472 -0.0968 0.2647 0.0506
5.500 1.1726 0.01290 0.00485 -0.0967 0.2585 0.0565
5.750 1.1995 0.01304 0.00505 -0.0965 0.2515 0.1108
6.000 1.2217 0.01204 0.00537 -0.0956 0.2451 1.0000
6.250 1.2483 0.01224 0.00555 -0.0953 0.2377 1.0000
6.500 1.2742 0.01252 0.00579 -0.0950 0.2302 1.0000
6.750 1.3005 0.01273 0.00600 -0.0948 0.2221 1.0000
7.000 1.3263 0.01302 0.00626 -0.0945 0.2136 1.0000
7.250 1.3519 0.01331 0.00652 -0.0942 0.2025 1.0000
7.500 1.3769 0.01367 0.00683 -0.0938 0.1867 1.0000
7.750 1.4012 0.01411 0.00718 -0.0933 0.1645 1.0000
8.000 1.4222 0.01499 0.00778 -0.0925 0.1220 1.0000
8.250 1.4432 0.01583 0.00847 -0.0916 0.1028 1.0000
8.500 1.4654 0.01647 0.00908 -0.0909 0.0970 1.0000
8.750 1.4873 0.01711 0.00973 -0.0901 0.0923 1.0000
9.000 1.5097 0.01766 0.01034 -0.0894 0.0890 1.0000
9.250 1.5302 0.01839 0.01109 -0.0884 0.0851 1.0000
9.500 1.5486 0.01930 0.01201 -0.0872 0.0810 1.0000
9.750 1.5699 0.01984 0.01264 -0.0863 0.0792 1.0000
10.000 1.5911 0.02037 0.01325 -0.0855 0.0772 1.0000
10.250 1.6111 0.02098 0.01394 -0.0845 0.0747 1.0000
10.500 1.6290 0.02174 0.01475 -0.0832 0.0721 1.0000
10.750 1.6418 0.02290 0.01595 -0.0813 0.0690 1.0000
11.000 1.6608 0.02346 0.01660 -0.0802 0.0672 1.0000
11.250 1.6813 0.02385 0.01709 -0.0793 0.0649 1.0000
11.500 1.7000 0.02434 0.01764 -0.0782 0.0620 1.0000
11.750 1.7139 0.02513 0.01845 -0.0764 0.0591 1.0000
12.000 1.7265 0.02588 0.01927 -0.0744 0.0566 1.0000
12.250 1.7437 0.02627 0.01975 -0.0731 0.0533 1.0000
12.500 1.7556 0.02703 0.02051 -0.0711 0.0496 1.0000
12.750 1.7675 0.02785 0.02139 -0.0693 0.0455 1.0000
13.000 1.7745 0.02908 0.02260 -0.0673 0.0408 1.0000
13.250 1.7809 0.03046 0.02404 -0.0654 0.0368 1.0000
13.500 1.7815 0.03248 0.02611 -0.0636 0.0335 1.0000
13.750 1.7829 0.03460 0.02831 -0.0621 0.0309 1.0000
14.000 1.7778 0.03755 0.03132 -0.0609 0.0289 1.0000
14.250 1.7768 0.04029 0.03419 -0.0602 0.0274 1.0000
14.500 1.7741 0.04338 0.03741 -0.0598 0.0261 1.0000
14.750 1.7677 0.04709 0.04121 -0.0598 0.0251 1.0000
15.000 1.7567 0.05160 0.04583 -0.0602 0.0243 1.0000
15.250 1.7422 0.05670 0.05106 -0.0609 0.0236 1.0000
15.500 1.7345 0.06100 0.05551 -0.0616 0.0231 1.0000
15.750 1.7235 0.06580 0.06045 -0.0625 0.0226 1.0000
16.000 1.7106 0.07097 0.06576 -0.0636 0.0221 1.0000
16.250 1.6966 0.07649 0.07141 -0.0650 0.0217 1.0000
16.500 1.6810 0.08239 0.07744 -0.0667 0.0214 1.0000
16.750 1.6650 0.08853 0.08370 -0.0686 0.0210 1.0000
17.000 1.6482 0.09496 0.09025 -0.0707 0.0207 1.0000
17.250 1.6309 0.10155 0.09695 -0.0730 0.0205 1.0000
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Polar data table (+)
Polar graphs
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