GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 359 AIRFOIL (goe359-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.6 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe359-il-1000000.txt Download as CSV file: xf-goe359-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 359 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2755 0.09981 0.09829 -0.0256 1.0000 0.0103
-8.250 -0.2721 0.09718 0.09568 -0.0258 1.0000 0.0109
-8.000 -0.2701 0.09448 0.09300 -0.0264 0.9999 0.0115
-7.750 -0.2498 0.09004 0.08857 -0.0335 0.9951 0.0116
-7.500 -0.2327 0.08601 0.08454 -0.0388 0.9828 0.0117
-7.250 -0.2061 0.08107 0.07958 -0.0468 0.9563 0.0117
-7.000 -0.1758 0.07418 0.07257 -0.0570 0.9158 0.0119
-6.750 -0.1616 0.07155 0.06976 -0.0586 0.8793 0.0121
-6.500 -0.1457 0.06900 0.06710 -0.0611 0.8574 0.0124
-6.250 -0.1273 0.06623 0.06424 -0.0645 0.8403 0.0128
-6.000 -0.1064 0.06314 0.06108 -0.0686 0.8259 0.0138
-5.750 -0.0690 0.05771 0.05553 -0.0793 0.8128 0.0155
-5.500 -0.0420 0.05343 0.05115 -0.0846 0.8007 0.0155
-5.250 -0.0139 0.04899 0.04660 -0.0897 0.7891 0.0156
-5.000 0.0164 0.02823 0.02584 -0.0865 0.7466 0.0164
-4.750 0.0390 0.02604 0.02358 -0.0886 0.7346 0.0172
-4.500 0.0755 0.02235 0.01970 -0.0942 0.7246 0.0202
-4.250 0.1045 0.01832 0.01550 -0.0978 0.7144 0.0203
-4.000 0.1284 0.01378 0.01076 -0.1010 0.7047 0.0195
-3.750 0.1639 0.02391 0.02036 -0.1098 0.7195 0.0215
-3.500 0.1875 0.02458 0.02102 -0.1097 0.7056 0.0226
-3.250 0.2188 0.02394 0.02018 -0.1095 0.6919 0.0266
-2.750 0.2752 0.01578 0.01096 -0.1111 0.6672 0.0279
-2.500 0.3014 0.01479 0.00987 -0.1112 0.6534 0.0290
-2.250 0.3282 0.01430 0.00929 -0.1112 0.6404 0.0303
-2.000 0.3556 0.01381 0.00865 -0.1112 0.6286 0.0327
-1.750 0.3840 0.01513 0.00990 -0.1107 0.6163 0.0359
-1.500 0.4117 0.01428 0.00881 -0.1105 0.6047 0.0360
-1.250 0.4393 0.01347 0.00780 -0.1104 0.5933 0.0361
-1.000 0.4667 0.01063 0.00467 -0.1105 0.5832 0.0331
-0.750 0.4944 0.01018 0.00410 -0.1103 0.5725 0.0335
-0.500 0.5220 0.00970 0.00350 -0.1101 0.5614 0.0335
-0.250 0.5494 0.00943 0.00314 -0.1099 0.5498 0.0341
0.000 0.5769 0.00922 0.00286 -0.1098 0.5385 0.0346
0.250 0.6043 0.00903 0.00262 -0.1096 0.5278 0.0349
0.500 0.6315 0.00888 0.00241 -0.1094 0.5139 0.0351
0.750 0.6585 0.00878 0.00223 -0.1092 0.4973 0.0353
1.000 0.6855 0.00878 0.00216 -0.1090 0.4816 0.0358
1.250 0.7127 0.00876 0.00208 -0.1089 0.4693 0.0361
1.500 0.7400 0.00857 0.00184 -0.1088 0.4595 0.0369
1.750 0.7674 0.00848 0.00169 -0.1086 0.4506 0.0395
2.000 0.7949 0.00847 0.00167 -0.1085 0.4427 0.0419
2.250 0.8221 0.00852 0.00168 -0.1084 0.4345 0.0439
2.500 0.8497 0.00855 0.00169 -0.1083 0.4268 0.0461
2.750 0.8769 0.00861 0.00172 -0.1082 0.4187 0.0544
3.000 0.9009 0.00701 0.00205 -0.1080 0.4101 1.0000
3.250 0.9280 0.00714 0.00213 -0.1079 0.4004 1.0000
3.500 0.9547 0.00731 0.00222 -0.1077 0.3874 1.0000
3.750 0.9804 0.00757 0.00233 -0.1073 0.3604 1.0000
4.000 1.0053 0.00793 0.00249 -0.1069 0.3223 1.0000
4.250 1.0281 0.00852 0.00279 -0.1062 0.2681 1.0000
4.500 1.0513 0.00907 0.00311 -0.1055 0.2305 1.0000
4.750 1.0754 0.00951 0.00339 -0.1050 0.2047 1.0000
5.000 1.0997 0.00991 0.00365 -0.1045 0.1798 1.0000
5.250 1.1190 0.01088 0.00422 -0.1033 0.1130 1.0000
5.500 1.1379 0.01188 0.00490 -0.1020 0.0526 1.0000
5.750 1.1619 0.01228 0.00524 -0.1014 0.0399 1.0000
6.000 1.1841 0.01288 0.00571 -0.1006 0.0152 1.0000
6.250 1.2087 0.01321 0.00607 -0.1001 0.0140 1.0000
6.500 1.2327 0.01358 0.00651 -0.0995 0.0128 1.0000
6.750 1.2559 0.01404 0.00703 -0.0987 0.0115 1.0000
7.000 1.2783 0.01456 0.00761 -0.0979 0.0106 1.0000
7.250 1.3012 0.01500 0.00809 -0.0972 0.0101 1.0000
7.500 1.3232 0.01551 0.00866 -0.0963 0.0096 1.0000
7.750 1.3445 0.01608 0.00928 -0.0953 0.0092 1.0000
8.000 1.3649 0.01671 0.00996 -0.0942 0.0087 1.0000
8.250 1.3837 0.01744 0.01076 -0.0929 0.0082 1.0000
8.500 1.3987 0.01847 0.01187 -0.0910 0.0078 1.0000
8.750 1.4040 0.02019 0.01373 -0.0877 0.0073 1.0000
9.000 1.4243 0.02063 0.01420 -0.0867 0.0070 1.0000
9.250 1.4383 0.02148 0.01511 -0.0847 0.0069 1.0000
9.500 1.4475 0.02241 0.01612 -0.0820 0.0067 1.0000
9.750 1.4543 0.02349 0.01726 -0.0790 0.0066 1.0000
10.000 1.4601 0.02468 0.01852 -0.0761 0.0064 1.0000
10.250 1.4645 0.02605 0.01997 -0.0734 0.0063 1.0000
10.500 1.4687 0.02756 0.02157 -0.0710 0.0061 1.0000
10.750 1.4723 0.02926 0.02335 -0.0690 0.0059 1.0000
11.000 1.4754 0.03116 0.02532 -0.0672 0.0058 1.0000
11.250 1.4786 0.03317 0.02739 -0.0657 0.0056 1.0000
11.500 1.4810 0.03534 0.02963 -0.0644 0.0055 1.0000
11.750 1.4829 0.03764 0.03200 -0.0632 0.0054 1.0000
12.000 1.4843 0.04006 0.03448 -0.0621 0.0053 1.0000
12.250 1.4846 0.04262 0.03709 -0.0609 0.0051 1.0000
12.500 1.4855 0.04512 0.03965 -0.0595 0.0051 1.0000
12.750 1.4880 0.04744 0.04200 -0.0577 0.0050 1.0000
13.000 1.5049 0.04882 0.04332 -0.0539 0.0049 1.0000
13.250 1.4997 0.05192 0.04662 -0.0534 0.0047 1.0000
13.500 1.4978 0.05475 0.04959 -0.0533 0.0046 1.0000
13.750 1.4991 0.05743 0.05238 -0.0527 0.0046 1.0000
14.000 1.5025 0.06004 0.05510 -0.0514 0.0046 1.0000
14.250 1.5036 0.06293 0.05810 -0.0505 0.0046 1.0000
14.500 1.5332 0.06326 0.05835 -0.0479 0.0050 1.0000
14.750 1.5246 0.06677 0.06203 -0.0481 0.0051 1.0000
15.750 1.4575 0.08881 0.08510 -0.0520 0.0058 1.0000
16.000 1.4469 0.09384 0.09027 -0.0536 0.0058 1.0000
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Polar data table (+)
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