GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.12 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe381-il-1000000-n5.txt Download as CSV file: xf-goe381-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1793 0.08817 0.08643 -0.0305 0.8709 0.0055
-8.500 -0.1748 0.08491 0.08316 -0.0312 0.8640 0.0055
-8.250 -0.1702 0.08166 0.07989 -0.0320 0.8566 0.0055
-8.000 -0.1654 0.07842 0.07662 -0.0329 0.8497 0.0055
-7.750 -0.1606 0.07517 0.07335 -0.0338 0.8421 0.0055
-7.500 -0.1557 0.07190 0.07007 -0.0347 0.8343 0.0055
-7.250 -0.1508 0.06865 0.06678 -0.0358 0.8253 0.0055
-6.250 -0.1741 0.07142 0.06943 -0.0460 0.8195 0.0034
-6.000 -0.1524 0.06752 0.06546 -0.0510 0.8087 0.0034
-5.500 -0.1005 0.05842 0.05622 -0.0627 0.7867 0.0036
-5.250 -0.0731 0.05489 0.05261 -0.0675 0.7748 0.0037
-5.000 -0.0454 0.05182 0.04944 -0.0715 0.7590 0.0040
-4.750 -0.0156 0.04830 0.04577 -0.0759 0.7391 0.0042
-4.500 0.0160 0.04455 0.04186 -0.0803 0.7155 0.0045
-4.250 0.0513 0.03967 0.03676 -0.0854 0.6913 0.0051
-4.000 0.0954 0.03117 0.02786 -0.0924 0.6714 0.0058
-3.500 0.1685 0.01037 0.00498 -0.0996 0.6375 0.0098
-3.250 0.1955 0.01039 0.00487 -0.0995 0.6006 0.0121
-3.000 0.2230 0.01098 0.00542 -0.0993 0.5703 0.0136
-2.500 0.2783 0.01137 0.00563 -0.0992 0.5360 0.0177
-2.000 0.3335 0.01178 0.00585 -0.0990 0.5040 0.0198
-1.750 0.3610 0.01102 0.00485 -0.0992 0.4893 0.0210
-1.500 0.3887 0.01086 0.00460 -0.0992 0.4760 0.0219
-1.250 0.4165 0.01073 0.00441 -0.0993 0.4663 0.0228
-1.000 0.4443 0.01051 0.00409 -0.0993 0.4569 0.0235
-0.750 0.4721 0.01013 0.00357 -0.0993 0.4461 0.0237
-0.500 0.4998 0.00990 0.00323 -0.0993 0.4334 0.0242
-0.250 0.5273 0.00959 0.00278 -0.0992 0.4176 0.0240
0.000 0.5546 0.00940 0.00244 -0.0992 0.3965 0.0238
0.250 0.5815 0.00933 0.00221 -0.0991 0.3689 0.0238
0.500 0.6083 0.00935 0.00205 -0.0990 0.3381 0.0239
0.750 0.6350 0.00942 0.00196 -0.0989 0.3085 0.0242
1.000 0.6618 0.00952 0.00191 -0.0988 0.2840 0.0250
1.250 0.6889 0.00960 0.00190 -0.0987 0.2656 0.0266
1.500 0.7160 0.00971 0.00193 -0.0987 0.2523 0.0283
1.750 0.7432 0.00982 0.00199 -0.0987 0.2417 0.0293
2.250 0.7975 0.01002 0.00212 -0.0986 0.2241 0.0302
2.500 0.8247 0.01010 0.00216 -0.0986 0.2178 0.0311
2.750 0.8520 0.01018 0.00221 -0.0985 0.2128 0.0318
3.000 0.8792 0.01027 0.00228 -0.0985 0.2075 0.0325
3.250 0.9061 0.01038 0.00237 -0.0985 0.2019 0.0344
3.500 0.9333 0.01047 0.00247 -0.0984 0.1983 0.0358
3.750 0.9603 0.01058 0.00257 -0.0984 0.1932 0.0372
4.000 0.9871 0.01072 0.00271 -0.0983 0.1869 0.0405
4.250 1.0128 0.01097 0.00293 -0.0982 0.1632 0.0836
4.500 1.0358 0.01165 0.00337 -0.0977 0.1166 0.0939
4.750 1.0616 0.01189 0.00360 -0.0975 0.1104 0.1056
5.000 1.0877 0.01209 0.00383 -0.0974 0.1046 0.1205
5.500 1.1296 0.01213 0.00502 -0.0959 0.0211 1.0000
5.750 1.1551 0.01241 0.00532 -0.0956 0.0132 1.0000
6.000 1.1802 0.01274 0.00568 -0.0953 0.0103 1.0000
6.250 1.2051 0.01309 0.00606 -0.0949 0.0082 1.0000
6.500 1.2299 0.01341 0.00641 -0.0946 0.0070 1.0000
6.750 1.2540 0.01383 0.00685 -0.0942 0.0057 1.0000
7.000 1.2780 0.01424 0.00730 -0.0937 0.0051 1.0000
7.250 1.3017 0.01467 0.00777 -0.0933 0.0046 1.0000
7.500 1.3251 0.01512 0.00826 -0.0927 0.0041 1.0000
7.750 1.3471 0.01570 0.00889 -0.0920 0.0035 1.0000
8.000 1.3697 0.01620 0.00944 -0.0914 0.0032 1.0000
8.250 1.3914 0.01677 0.01008 -0.0907 0.0030 1.0000
8.500 1.4123 0.01740 0.01077 -0.0898 0.0027 1.0000
8.750 1.4328 0.01803 0.01146 -0.0889 0.0025 1.0000
9.000 1.4527 0.01869 0.01218 -0.0880 0.0024 1.0000
9.250 1.4707 0.01947 0.01306 -0.0868 0.0022 1.0000
9.500 1.4833 0.02073 0.01444 -0.0847 0.0020 1.0000
9.750 1.4978 0.02168 0.01550 -0.0830 0.0020 1.0000
10.000 1.5090 0.02280 0.01673 -0.0809 0.0019 1.0000
10.250 1.5141 0.02403 0.01809 -0.0778 0.0018 1.0000
10.500 1.5171 0.02543 0.01961 -0.0746 0.0018 1.0000
10.750 1.5198 0.02695 0.02125 -0.0718 0.0017 1.0000
11.000 1.5220 0.02862 0.02303 -0.0694 0.0016 1.0000
11.250 1.5254 0.03032 0.02484 -0.0673 0.0015 1.0000
11.500 1.5277 0.03221 0.02684 -0.0655 0.0014 1.0000
11.750 1.5285 0.03438 0.02912 -0.0639 0.0014 1.0000
12.000 1.5285 0.03675 0.03160 -0.0625 0.0013 1.0000
12.250 1.5271 0.03942 0.03439 -0.0614 0.0013 1.0000
12.500 1.5253 0.04228 0.03736 -0.0606 0.0013 1.0000
12.750 1.5230 0.04536 0.04058 -0.0601 0.0013 1.0000
13.000 1.5180 0.04888 0.04423 -0.0598 0.0012 1.0000
13.250 1.5132 0.05257 0.04804 -0.0599 0.0012 1.0000
13.500 1.5085 0.05638 0.05196 -0.0602 0.0012 1.0000
13.750 1.5011 0.06061 0.05632 -0.0606 0.0012 1.0000
14.000 1.4933 0.06505 0.06088 -0.0613 0.0012 1.0000
14.250 1.4845 0.06972 0.06568 -0.0621 0.0011 1.0000
14.500 1.4742 0.07466 0.07074 -0.0629 0.0011 1.0000
14.750 1.4628 0.07986 0.07608 -0.0639 0.0011 1.0000
15.000 1.4487 0.08545 0.08181 -0.0649 0.0011 1.0000
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Polar data table (+)
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