GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 50,000 Max Cl/Cd: 42.69 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe372-il-50000-n5.txt Download as CSV file: xf-goe372-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3565 0.10709 0.10038 -0.0294 1.0000 0.0820
-8.000 -0.3599 0.10527 0.09867 -0.0301 1.0000 0.0824
-7.750 -0.3639 0.10334 0.09687 -0.0305 1.0000 0.0826
-7.500 -0.3644 0.10084 0.09447 -0.0318 1.0000 0.0828
-7.250 -0.3625 0.09804 0.09176 -0.0331 1.0000 0.0829
-7.000 -0.3596 0.09496 0.08875 -0.0342 1.0000 0.0829
-6.500 -0.3493 0.08502 0.07888 -0.0357 1.0000 0.0544
-6.250 -0.3455 0.08173 0.07564 -0.0368 1.0000 0.0544
-6.000 -0.3402 0.07840 0.07234 -0.0388 1.0000 0.0546
-5.750 -0.3330 0.07480 0.06875 -0.0410 1.0000 0.0548
-5.500 -0.3238 0.07102 0.06494 -0.0433 1.0000 0.0549
-5.250 -0.3147 0.06722 0.06111 -0.0444 1.0000 0.0548
-5.000 -0.3044 0.06344 0.05728 -0.0454 1.0000 0.0546
-4.750 -0.2895 0.05918 0.05291 -0.0477 1.0000 0.0546
-4.500 -0.2842 0.05758 0.05134 -0.0453 1.0000 0.0592
-4.250 -0.2653 0.05413 0.04772 -0.0478 1.0000 0.0643
-4.000 -0.2398 0.04937 0.04265 -0.0518 1.0000 0.0658
-3.750 -0.2052 0.04345 0.03604 -0.0574 1.0000 0.0688
-3.500 -0.1858 0.04232 0.03493 -0.0575 0.9977 0.0787
-3.250 -0.1390 0.03724 0.02904 -0.0636 0.9918 0.0805
-3.000 -0.0936 0.03297 0.02376 -0.0683 0.9863 0.0834
-2.750 -0.0573 0.03111 0.02158 -0.0709 0.9791 0.0883
-2.500 -0.0204 0.02969 0.01965 -0.0734 0.9717 0.1003
-2.250 0.0180 0.02808 0.01758 -0.0759 0.9654 0.1050
-2.000 0.0544 0.02661 0.01553 -0.0777 0.9578 0.1097
-1.750 0.0906 0.02553 0.01413 -0.0795 0.9507 0.1157
-1.500 0.1264 0.02471 0.01294 -0.0810 0.9428 0.1261
-1.250 0.1621 0.02423 0.01234 -0.0828 0.9348 0.1434
-1.000 0.2006 0.02370 0.01164 -0.0849 0.9275 0.1633
-0.750 0.2347 0.02323 0.01105 -0.0862 0.9185 0.1834
-0.500 0.2742 0.02274 0.01057 -0.0886 0.9117 0.2119
-0.250 0.3071 0.02229 0.01020 -0.0897 0.9020 0.2426
0.000 0.3427 0.02169 0.00995 -0.0914 0.8937 0.3122
0.250 0.3836 0.01988 0.00961 -0.0938 0.8867 1.0000
0.500 0.4158 0.02005 0.00948 -0.0945 0.8762 1.0000
0.750 0.4493 0.02020 0.00942 -0.0955 0.8665 1.0000
1.000 0.4849 0.02030 0.00937 -0.0968 0.8576 1.0000
1.250 0.5141 0.02050 0.00948 -0.0970 0.8462 1.0000
1.500 0.5438 0.02069 0.00962 -0.0973 0.8351 1.0000
1.750 0.5745 0.02087 0.00976 -0.0977 0.8245 1.0000
2.000 0.6084 0.02098 0.00989 -0.0985 0.8156 1.0000
2.250 0.6358 0.02123 0.01018 -0.0983 0.8036 1.0000
2.500 0.6630 0.02151 0.01051 -0.0981 0.7918 1.0000
2.750 0.6908 0.02178 0.01090 -0.0979 0.7805 1.0000
3.000 0.7199 0.02201 0.01124 -0.0979 0.7701 1.0000
3.250 0.7493 0.02224 0.01160 -0.0979 0.7598 1.0000
3.500 0.7746 0.02259 0.01212 -0.0973 0.7475 1.0000
3.750 0.8007 0.02286 0.01263 -0.0967 0.7345 1.0000
4.000 0.8276 0.02299 0.01296 -0.0958 0.7198 1.0000
4.250 0.8539 0.02283 0.01301 -0.0943 0.6995 1.0000
4.500 0.8745 0.02165 0.01178 -0.0895 0.6450 1.0000
4.750 0.8930 0.02135 0.01153 -0.0859 0.5921 1.0000
5.000 0.9119 0.02136 0.01138 -0.0826 0.5295 1.0000
5.250 0.9231 0.02203 0.01153 -0.0786 0.4120 1.0000
5.500 0.9256 0.02417 0.01230 -0.0747 0.2177 1.0000
5.750 0.9263 0.02753 0.01431 -0.0719 0.0527 1.0000
6.000 0.9406 0.02921 0.01601 -0.0699 0.0423 1.0000
6.250 0.9553 0.03072 0.01771 -0.0680 0.0372 1.0000
6.500 0.9683 0.03238 0.01965 -0.0659 0.0352 1.0000
6.750 0.9816 0.03390 0.02144 -0.0638 0.0338 1.0000
7.000 0.9937 0.03555 0.02332 -0.0616 0.0326 1.0000
7.250 1.0058 0.03726 0.02525 -0.0594 0.0310 1.0000
7.500 1.0184 0.03918 0.02730 -0.0574 0.0290 1.0000
7.750 1.0367 0.04141 0.02959 -0.0559 0.0276 1.0000
8.000 1.0659 0.04349 0.03190 -0.0551 0.0271 1.0000
8.250 1.0992 0.04612 0.03478 -0.0548 0.0269 1.0000
8.500 1.1279 0.04914 0.03810 -0.0544 0.0268 1.0000
8.750 1.1504 0.05247 0.04194 -0.0534 0.0269 1.0000
9.000 1.1664 0.05582 0.04567 -0.0519 0.0270 1.0000
9.250 1.1761 0.05920 0.04949 -0.0500 0.0269 1.0000
9.500 1.1804 0.06257 0.05329 -0.0478 0.0268 1.0000
9.750 1.1807 0.06603 0.05714 -0.0455 0.0267 1.0000
10.000 1.1768 0.06949 0.06095 -0.0432 0.0267 1.0000
10.250 1.1671 0.07283 0.06460 -0.0405 0.0266 1.0000
10.500 1.1556 0.07630 0.06833 -0.0383 0.0267 1.0000
10.750 1.1411 0.08004 0.07232 -0.0368 0.0267 1.0000
11.000 1.1266 0.08414 0.07664 -0.0363 0.0268 1.0000
11.250 1.1113 0.08862 0.08132 -0.0365 0.0270 1.0000
11.500 1.0958 0.09352 0.08639 -0.0376 0.0271 1.0000
11.750 1.0817 0.09875 0.09176 -0.0393 0.0273 1.0000
12.000 1.0673 0.10444 0.09758 -0.0417 0.0274 1.0000
12.250 1.0543 0.11048 0.10371 -0.0446 0.0276 1.0000
12.500 1.0423 0.11669 0.11008 -0.0480 0.0279 1.0000
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Polar data table (+)
Polar graphs
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