GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.64 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe372-il-1000000-n5.txt Download as CSV file: xf-goe372-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 372 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3886 0.09291 0.09138 -0.0275 1.0000 0.0026
-8.750 -0.3923 0.08900 0.08750 -0.0283 1.0000 0.0026
-8.500 -0.4047 0.08420 0.08274 -0.0287 1.0000 0.0027
-8.250 -0.3970 0.07889 0.07745 -0.0343 0.9950 0.0028
-8.000 -0.4009 0.05906 0.05753 -0.0601 0.9789 0.0028
-7.750 -0.3798 0.01984 0.01692 -0.1019 0.9596 0.0025
-7.500 -0.3522 0.01648 0.01314 -0.1039 0.9513 0.0025
-7.250 -0.3251 0.01419 0.01046 -0.1050 0.9398 0.0027
-7.000 -0.2980 0.01296 0.00897 -0.1053 0.9253 0.0029
-6.750 -0.2716 0.01222 0.00805 -0.1053 0.9089 0.0032
-6.500 -0.2458 0.01157 0.00721 -0.1051 0.8924 0.0036
-6.250 -0.2203 0.01099 0.00642 -0.1047 0.8764 0.0039
-6.000 -0.1948 0.01050 0.00574 -0.1043 0.8610 0.0042
-5.750 -0.1695 0.00992 0.00492 -0.1038 0.8463 0.0046
-5.500 -0.1440 0.00940 0.00423 -0.1033 0.8326 0.0054
-5.250 -0.1180 0.00904 0.00373 -0.1029 0.8210 0.0062
-5.000 -0.0918 0.00877 0.00332 -0.1025 0.8098 0.0069
-4.750 -0.0657 0.00838 0.00287 -0.1021 0.7994 0.0102
-4.500 -0.0393 0.00811 0.00260 -0.1019 0.7906 0.0192
-4.250 -0.0124 0.00796 0.00237 -0.1016 0.7829 0.0221
-4.000 0.0144 0.00783 0.00221 -0.1014 0.7752 0.0272
-3.750 0.0416 0.00776 0.00208 -0.1012 0.7676 0.0302
-3.500 0.0686 0.00772 0.00197 -0.1010 0.7601 0.0318
-3.250 0.0960 0.00772 0.00193 -0.1009 0.7531 0.0324
-3.000 0.1228 0.00752 0.00165 -0.1006 0.7460 0.0339
-2.750 0.1499 0.00738 0.00145 -0.1004 0.7389 0.0350
-2.500 0.1768 0.00728 0.00128 -0.1001 0.7314 0.0361
-2.250 0.2041 0.00719 0.00114 -0.0999 0.7240 0.0372
-2.000 0.2310 0.00712 0.00103 -0.0997 0.7165 0.0385
-1.750 0.2582 0.00704 0.00093 -0.0995 0.7083 0.0402
-1.500 0.2852 0.00699 0.00084 -0.0993 0.7001 0.0436
-1.250 0.3121 0.00691 0.00079 -0.0991 0.6901 0.0558
-1.000 0.3390 0.00688 0.00076 -0.0988 0.6782 0.0671
-0.750 0.3657 0.00689 0.00071 -0.0985 0.6627 0.0705
-0.500 0.3921 0.00690 0.00068 -0.0982 0.6452 0.0760
-0.250 0.4186 0.00694 0.00066 -0.0979 0.6249 0.0806
0.000 0.4447 0.00701 0.00064 -0.0975 0.6009 0.0833
0.250 0.4706 0.00709 0.00065 -0.0971 0.5770 0.0890
0.500 0.4966 0.00718 0.00068 -0.0968 0.5558 0.0953
0.750 0.5229 0.00724 0.00072 -0.0965 0.5396 0.1059
1.000 0.5491 0.00730 0.00077 -0.0961 0.5241 0.1241
1.250 0.5752 0.00735 0.00083 -0.0958 0.5083 0.1472
1.500 0.6011 0.00740 0.00091 -0.0955 0.4916 0.1797
1.750 0.6259 0.00748 0.00102 -0.0950 0.4599 0.2436
2.000 0.6514 0.00748 0.00112 -0.0947 0.4378 0.3161
2.250 0.6759 0.00754 0.00125 -0.0941 0.4055 0.4060
2.750 0.7256 0.00833 0.00216 -0.0945 0.1353 1.0000
3.000 0.7445 0.00927 0.00264 -0.0930 0.0167 1.0000
3.250 0.7700 0.00947 0.00284 -0.0925 0.0121 1.0000
3.500 0.7954 0.00967 0.00307 -0.0920 0.0099 1.0000
3.750 0.8206 0.00989 0.00331 -0.0915 0.0082 1.0000
4.000 0.8453 0.01017 0.00361 -0.0909 0.0070 1.0000
4.250 0.8692 0.01056 0.00405 -0.0901 0.0060 1.0000
4.500 0.8939 0.01081 0.00433 -0.0895 0.0052 1.0000
4.750 0.9182 0.01112 0.00465 -0.0889 0.0046 1.0000
5.000 0.9418 0.01150 0.00505 -0.0881 0.0042 1.0000
5.250 0.9635 0.01211 0.00572 -0.0870 0.0037 1.0000
5.500 0.9858 0.01264 0.00632 -0.0859 0.0034 1.0000
5.750 1.0067 0.01332 0.00709 -0.0846 0.0033 1.0000
6.000 1.0261 0.01414 0.00800 -0.0830 0.0031 1.0000
6.250 1.0461 0.01488 0.00880 -0.0816 0.0028 1.0000
6.500 1.0693 0.01520 0.00914 -0.0810 0.0026 1.0000
6.750 1.0896 0.01586 0.00985 -0.0798 0.0024 1.0000
7.000 1.1087 0.01666 0.01070 -0.0784 0.0023 1.0000
7.250 1.1229 0.01822 0.01238 -0.0760 0.0021 1.0000
7.500 1.1409 0.01952 0.01379 -0.0743 0.0021 1.0000
7.750 1.1594 0.02178 0.01624 -0.0724 0.0019 1.0000
8.000 1.1808 0.02486 0.01953 -0.0709 0.0016 1.0000
8.250 1.2003 0.02785 0.02278 -0.0691 0.0015 1.0000
8.500 1.2164 0.03083 0.02603 -0.0671 0.0015 1.0000
8.750 1.2292 0.03422 0.02973 -0.0645 0.0015 1.0000
9.000 1.2387 0.03738 0.03316 -0.0618 0.0016 1.0000
9.250 1.2442 0.04090 0.03697 -0.0586 0.0016 1.0000
9.500 1.2461 0.04424 0.04058 -0.0554 0.0017 1.0000
9.750 1.2442 0.04761 0.04420 -0.0519 0.0017 1.0000
10.000 1.2393 0.05072 0.04753 -0.0484 0.0018 1.0000
10.250 1.2267 0.05359 0.05057 -0.0440 0.0018 1.0000
10.500 1.2114 0.05621 0.05335 -0.0398 0.0018 1.0000
10.750 1.1940 0.05924 0.05654 -0.0366 0.0018 1.0000
11.000 1.1765 0.06265 0.06011 -0.0345 0.0018 1.0000
11.250 1.1583 0.06657 0.06416 -0.0336 0.0019 1.0000
11.500 1.1392 0.07111 0.06884 -0.0338 0.0019 1.0000
11.750 1.1217 0.07595 0.07381 -0.0350 0.0019 1.0000
12.000 1.1020 0.08177 0.07976 -0.0374 0.0019 1.0000
12.250 1.0810 0.08873 0.08685 -0.0411 0.0019 1.0000
12.500 1.0647 0.09549 0.09371 -0.0453 0.0019 1.0000
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Polar data table (+)
Polar graphs
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