GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 200,000 Max Cl/Cd: 77.11 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe372-il-200000-n5.txt Download as CSV file: xf-goe372-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3507 0.08837 0.08500 -0.0289 1.0000 0.0090
-7.500 -0.3551 0.08587 0.08257 -0.0282 1.0000 0.0089
-7.250 -0.3626 0.08373 0.08051 -0.0268 1.0000 0.0088
-7.000 -0.3684 0.08109 0.07795 -0.0263 1.0000 0.0089
-6.750 -0.3692 0.07764 0.07456 -0.0278 0.9989 0.0092
-6.500 -0.3428 0.07154 0.06844 -0.0372 0.9919 0.0092
-6.250 -0.3130 0.06418 0.06105 -0.0484 0.9841 0.0097
-6.000 -0.2776 0.05509 0.05185 -0.0617 0.9763 0.0103
-5.750 -0.2300 0.03305 0.02924 -0.0858 0.9655 0.0114
-5.500 -0.2042 0.04214 0.03858 -0.0802 0.9604 0.0169
-5.250 -0.1627 0.02286 0.01790 -0.0943 0.9531 0.0206
-5.000 -0.1316 0.02455 0.01971 -0.0947 0.9455 0.0255
-4.750 -0.0995 0.01846 0.01239 -0.0972 0.9398 0.0276
-4.500 -0.0704 0.01664 0.01017 -0.0978 0.9313 0.0304
-4.250 -0.0370 0.01583 0.00913 -0.0990 0.9247 0.0333
-4.000 -0.0064 0.01490 0.00792 -0.0996 0.9159 0.0360
-3.750 0.0245 0.01417 0.00694 -0.1002 0.9080 0.0395
-3.500 0.0559 0.01377 0.00647 -0.1009 0.9008 0.0441
-3.250 0.0853 0.01317 0.00570 -0.1011 0.8922 0.0486
-3.000 0.1159 0.01264 0.00506 -0.1016 0.8846 0.0538
-2.750 0.1450 0.01235 0.00460 -0.1017 0.8756 0.0605
-2.500 0.1737 0.01207 0.00425 -0.1018 0.8667 0.0673
-2.250 0.2029 0.01193 0.00399 -0.1020 0.8582 0.0758
-2.000 0.2305 0.01167 0.00372 -0.1019 0.8490 0.0830
-1.750 0.2581 0.01148 0.00345 -0.1017 0.8399 0.0904
-1.500 0.2857 0.01127 0.00321 -0.1016 0.8311 0.0966
-1.250 0.3128 0.01112 0.00294 -0.1013 0.8217 0.1030
-1.000 0.3396 0.01096 0.00279 -0.1011 0.8124 0.1114
-0.750 0.3665 0.01083 0.00263 -0.1008 0.8035 0.1195
-0.500 0.3933 0.01073 0.00251 -0.1005 0.7940 0.1298
-0.250 0.4197 0.01062 0.00243 -0.1001 0.7843 0.1443
0.000 0.4462 0.01051 0.00238 -0.0998 0.7750 0.1688
0.250 0.4725 0.01037 0.00235 -0.0994 0.7654 0.2088
0.500 0.4979 0.01015 0.00237 -0.0990 0.7549 0.2880
0.750 0.5213 0.00961 0.00243 -0.0983 0.7448 0.5069
1.000 0.5672 0.00870 0.00242 -0.1019 0.7345 1.0000
1.250 0.5930 0.00880 0.00242 -0.1014 0.7219 1.0000
1.500 0.6187 0.00891 0.00245 -0.1008 0.7082 1.0000
1.750 0.6443 0.00901 0.00250 -0.1002 0.6933 1.0000
2.000 0.6695 0.00913 0.00255 -0.0995 0.6757 1.0000
2.250 0.6932 0.00928 0.00262 -0.0984 0.6436 1.0000
2.500 0.7162 0.00949 0.00264 -0.0972 0.6041 1.0000
2.750 0.7406 0.00969 0.00275 -0.0964 0.5805 1.0000
3.000 0.7645 0.00993 0.00290 -0.0955 0.5572 1.0000
3.250 0.7881 0.01022 0.00308 -0.0946 0.5328 1.0000
3.500 0.8109 0.01056 0.00331 -0.0936 0.5008 1.0000
3.750 0.8266 0.01139 0.00356 -0.0913 0.3868 1.0000
4.000 0.8364 0.01307 0.00425 -0.0886 0.2073 1.0000
4.250 0.8462 0.01505 0.00529 -0.0860 0.0284 1.0000
4.500 0.8684 0.01565 0.00596 -0.0848 0.0215 1.0000
4.750 0.8887 0.01647 0.00707 -0.0834 0.0157 1.0000
5.000 0.9098 0.01721 0.00798 -0.0821 0.0137 1.0000
5.250 0.9299 0.01804 0.00897 -0.0806 0.0123 1.0000
5.500 0.9481 0.01904 0.01009 -0.0789 0.0114 1.0000
5.750 0.9645 0.02022 0.01135 -0.0769 0.0107 1.0000
6.000 0.9799 0.02151 0.01265 -0.0750 0.0090 1.0000
6.250 0.9945 0.02319 0.01432 -0.0730 0.0075 1.0000
6.500 1.0150 0.02416 0.01540 -0.0716 0.0066 1.0000
6.750 1.0352 0.02574 0.01706 -0.0702 0.0062 1.0000
7.000 1.0572 0.02750 0.01894 -0.0690 0.0060 1.0000
7.250 1.0803 0.02950 0.02112 -0.0679 0.0058 1.0000
7.500 1.1027 0.03166 0.02349 -0.0667 0.0057 1.0000
7.750 1.1235 0.03399 0.02608 -0.0654 0.0057 1.0000
8.000 1.1419 0.03647 0.02887 -0.0637 0.0057 1.0000
8.250 1.1575 0.03913 0.03184 -0.0618 0.0058 1.0000
8.500 1.1701 0.04201 0.03506 -0.0596 0.0059 1.0000
8.750 1.1791 0.04504 0.03859 -0.0572 0.0060 1.0000
9.000 1.1846 0.04811 0.04199 -0.0545 0.0061 1.0000
9.250 1.1862 0.05127 0.04546 -0.0516 0.0062 1.0000
9.500 1.1842 0.05441 0.04890 -0.0486 0.0063 1.0000
9.750 1.1772 0.05739 0.05214 -0.0452 0.0063 1.0000
10.000 1.1649 0.06038 0.05536 -0.0416 0.0064 1.0000
10.250 1.1522 0.06337 0.05855 -0.0388 0.0065 1.0000
10.500 1.1370 0.06685 0.06223 -0.0368 0.0065 1.0000
10.750 1.1215 0.07065 0.06622 -0.0359 0.0066 1.0000
11.000 1.1044 0.07507 0.07081 -0.0359 0.0066 1.0000
11.250 1.0875 0.07988 0.07579 -0.0369 0.0066 1.0000
11.500 1.0702 0.08529 0.08136 -0.0389 0.0067 1.0000
11.750 1.0531 0.09134 0.08756 -0.0419 0.0067 1.0000
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Polar data table (+)
Polar graphs
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