GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 411 AIRFOIL (goe411-il) Reynolds number: 500,000 Max Cl/Cd: 42.89 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe411-il-500000-n5.txt Download as CSV file: xf-goe411-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 411 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6395 0.10953 0.10715 -0.0264 1.0000 0.0033
-13.750 -0.6623 0.09910 0.09662 -0.0323 1.0000 0.0033
-13.500 -0.6842 0.09000 0.08742 -0.0378 1.0000 0.0032
-13.250 -0.7036 0.08238 0.07968 -0.0425 1.0000 0.0032
-13.000 -0.7203 0.07601 0.07320 -0.0463 1.0000 0.0031
-12.750 -0.7418 0.06942 0.06646 -0.0498 1.0000 0.0031
-12.500 -0.7579 0.06433 0.06124 -0.0521 1.0000 0.0031
-12.250 -0.7732 0.05988 0.05666 -0.0535 1.0000 0.0031
-12.000 -0.7910 0.05558 0.05220 -0.0540 1.0000 0.0030
-11.750 -0.8077 0.05190 0.04835 -0.0534 1.0000 0.0030
-11.500 -0.8248 0.04850 0.04477 -0.0518 1.0000 0.0030
-11.250 -0.8400 0.04557 0.04167 -0.0492 1.0000 0.0029
-11.000 -0.8540 0.04299 0.03890 -0.0458 1.0000 0.0029
-10.750 -0.8669 0.04074 0.03647 -0.0417 1.0000 0.0030
-10.500 -0.8791 0.03863 0.03417 -0.0369 1.0000 0.0030
-10.250 -0.8886 0.03708 0.03247 -0.0318 1.0000 0.0030
-10.000 -0.9003 0.03513 0.03032 -0.0259 1.0000 0.0029
-9.750 -0.9083 0.03365 0.02868 -0.0202 1.0000 0.0029
-9.500 -0.9097 0.03194 0.02680 -0.0157 1.0000 0.0030
-9.250 -0.9077 0.03024 0.02492 -0.0116 1.0000 0.0030
-9.000 -0.9032 0.02852 0.02302 -0.0078 1.0000 0.0030
-8.750 -0.8814 0.02635 0.02064 -0.0076 0.9985 0.0031
-8.500 -0.8582 0.02465 0.01879 -0.0075 0.9968 0.0032
-8.250 -0.8344 0.02312 0.01710 -0.0075 0.9950 0.0036
-8.000 -0.8117 0.02174 0.01561 -0.0072 0.9928 0.0037
-7.750 -0.7868 0.02056 0.01433 -0.0073 0.9899 0.0040
-7.500 -0.7600 0.01929 0.01295 -0.0079 0.9871 0.0043
-7.250 -0.7328 0.01853 0.01211 -0.0084 0.9837 0.0046
-7.000 -0.7045 0.01795 0.01147 -0.0090 0.9801 0.0048
-6.750 -0.6846 0.01617 0.00957 -0.0084 0.9769 0.0057
-6.500 -0.6619 0.01561 0.00892 -0.0078 0.9715 0.0065
-6.250 -0.6341 0.01488 0.00813 -0.0082 0.9686 0.0074
-6.000 -0.6095 0.01425 0.00743 -0.0079 0.9639 0.0089
-5.750 -0.5817 0.01370 0.00681 -0.0082 0.9597 0.0108
-5.500 -0.5492 0.01333 0.00639 -0.0094 0.9572 0.0119
-5.250 -0.5262 0.01290 0.00592 -0.0087 0.9507 0.0134
-5.000 -0.4967 0.01239 0.00533 -0.0094 0.9473 0.0160
-4.750 -0.4698 0.01205 0.00493 -0.0094 0.9418 0.0173
-4.500 -0.4388 0.01174 0.00455 -0.0103 0.9369 0.0182
-4.250 -0.4074 0.01147 0.00417 -0.0113 0.9323 0.0183
-4.000 -0.3781 0.01123 0.00387 -0.0117 0.9254 0.0186
-3.750 -0.3460 0.01100 0.00358 -0.0128 0.9194 0.0191
-3.500 -0.3148 0.01078 0.00333 -0.0136 0.9114 0.0234
-3.250 -0.2936 0.00984 0.00284 -0.0128 0.9008 0.1449
-3.000 -0.2664 0.00933 0.00256 -0.0131 0.8903 0.2001
-2.750 -0.2443 0.00860 0.00225 -0.0124 0.8778 0.3016
-2.500 -0.2184 0.00826 0.00205 -0.0123 0.8644 0.3518
-2.250 -0.1950 0.00793 0.00191 -0.0116 0.8498 0.4100
-2.000 -0.1699 0.00778 0.00181 -0.0111 0.8343 0.4394
-1.750 -0.1488 0.00755 0.00174 -0.0098 0.8180 0.4917
-1.500 -0.1264 0.00742 0.00166 -0.0087 0.8017 0.5236
-1.250 -0.1023 0.00739 0.00160 -0.0079 0.7837 0.5385
-1.000 -0.0787 0.00737 0.00155 -0.0070 0.7620 0.5504
-0.750 -0.0567 0.00736 0.00150 -0.0057 0.7354 0.5665
-0.500 -0.0368 0.00737 0.00145 -0.0040 0.7013 0.5881
-0.250 -0.0185 0.00738 0.00142 -0.0020 0.6661 0.6115
0.000 0.0000 0.00738 0.00141 0.0000 0.6370 0.6372
0.250 0.0185 0.00738 0.00142 0.0020 0.6116 0.6661
0.500 0.0371 0.00738 0.00145 0.0040 0.5881 0.6989
0.750 0.0568 0.00737 0.00150 0.0057 0.5663 0.7339
1.000 0.0788 0.00737 0.00155 0.0070 0.5504 0.7616
1.250 0.1023 0.00739 0.00160 0.0079 0.5384 0.7836
1.500 0.1267 0.00741 0.00167 0.0086 0.5265 0.8016
1.750 0.1473 0.00760 0.00173 0.0101 0.4803 0.8185
2.000 0.1695 0.00779 0.00181 0.0112 0.4366 0.8344
2.250 0.1940 0.00797 0.00191 0.0118 0.4014 0.8502
2.500 0.2202 0.00817 0.00204 0.0120 0.3694 0.8641
2.750 0.2445 0.00858 0.00225 0.0124 0.3044 0.8772
3.000 0.2670 0.00929 0.00255 0.0130 0.2060 0.8901
3.250 0.2932 0.00986 0.00285 0.0129 0.1419 0.9008
3.500 0.3147 0.01078 0.00333 0.0137 0.0226 0.9113
3.750 0.3460 0.01100 0.00358 0.0128 0.0191 0.9193
4.000 0.3782 0.01123 0.00387 0.0117 0.0187 0.9253
4.250 0.4074 0.01147 0.00417 0.0112 0.0183 0.9323
4.500 0.4392 0.01174 0.00455 0.0102 0.0182 0.9370
4.750 0.4700 0.01205 0.00493 0.0094 0.0173 0.9418
5.000 0.4968 0.01238 0.00533 0.0094 0.0160 0.9473
5.250 0.5260 0.01293 0.00594 0.0087 0.0130 0.9507
5.500 0.5490 0.01335 0.00642 0.0095 0.0119 0.9573
5.750 0.5819 0.01370 0.00681 0.0081 0.0107 0.9597
6.000 0.6099 0.01422 0.00740 0.0078 0.0088 0.9638
6.250 0.6342 0.01487 0.00813 0.0082 0.0079 0.9685
6.500 0.6620 0.01560 0.00891 0.0078 0.0066 0.9715
6.750 0.6838 0.01628 0.00970 0.0086 0.0061 0.9770
7.000 0.7042 0.01798 0.01150 0.0090 0.0048 0.9802
7.250 0.7327 0.01855 0.01213 0.0084 0.0046 0.9837
7.500 0.7592 0.01945 0.01311 0.0080 0.0044 0.9872
7.750 0.7884 0.02035 0.01411 0.0070 0.0039 0.9898
8.000 0.8117 0.02179 0.01566 0.0072 0.0038 0.9928
8.250 0.8346 0.02314 0.01711 0.0075 0.0036 0.9950
8.500 0.8579 0.02477 0.01891 0.0076 0.0034 0.9967
8.750 0.8816 0.02628 0.02057 0.0075 0.0031 0.9986
9.000 0.9035 0.02834 0.02283 0.0078 0.0030 1.0000
9.250 0.9080 0.02998 0.02463 0.0115 0.0030 1.0000
9.500 0.9098 0.03175 0.02659 0.0157 0.0029 1.0000
9.750 0.9086 0.03356 0.02858 0.0202 0.0029 1.0000
10.000 0.9003 0.03519 0.03039 0.0259 0.0029 1.0000
10.250 0.8908 0.03668 0.03203 0.0315 0.0029 1.0000
10.500 0.8796 0.03853 0.03407 0.0368 0.0029 1.0000
10.750 0.8670 0.04073 0.03646 0.0417 0.0030 1.0000
11.000 0.8534 0.04310 0.03902 0.0459 0.0029 1.0000
11.250 0.8425 0.04532 0.04140 0.0490 0.0030 1.0000
11.500 0.8248 0.04853 0.04480 0.0518 0.0030 1.0000
11.750 0.8097 0.05169 0.04813 0.0533 0.0030 1.0000
12.000 0.7926 0.05545 0.05206 0.0540 0.0030 1.0000
12.250 0.7716 0.06019 0.05698 0.0534 0.0030 1.0000
12.500 0.7599 0.06413 0.06103 0.0521 0.0031 1.0000
12.750 0.7385 0.07011 0.06717 0.0494 0.0031 1.0000
13.000 0.7220 0.07585 0.07303 0.0462 0.0031 1.0000
13.250 0.6970 0.08392 0.08125 0.0414 0.0032 1.0000
13.500 0.6815 0.09082 0.08825 0.0372 0.0032 1.0000
13.750 0.6622 0.09941 0.09694 0.0320 0.0033 1.0000
14.000 0.6388 0.11015 0.10777 0.0260 0.0033 1.0000
14.250 0.6216 0.11998 0.11764 0.0212 0.0034 1.0000
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