GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 50,000 Max Cl/Cd: 13.94 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe383-il-50000-n5.txt Download as CSV file: xf-goe383-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1408 0.10891 0.10140 -0.0837 0.9392 0.0856
-10.750 -0.1376 0.10403 0.09651 -0.0873 0.9287 0.0850
-10.500 -0.1349 0.09864 0.09110 -0.0916 0.9204 0.0848
-10.000 -0.2294 0.07470 0.06687 -0.1091 0.8936 0.0815
-9.750 -0.2592 0.06886 0.06083 -0.1121 0.8809 0.0811
-9.500 -0.2888 0.06502 0.05677 -0.1112 0.8672 0.0809
-9.250 -0.3128 0.06189 0.05339 -0.1092 0.8548 0.0809
-9.000 -0.3265 0.05851 0.04964 -0.1077 0.8462 0.0810
-8.750 -0.3379 0.05605 0.04686 -0.1051 0.8358 0.0812
-8.500 -0.3394 0.05345 0.04389 -0.1032 0.8277 0.0815
-8.250 -0.3233 0.05132 0.04155 -0.1029 0.8228 0.0821
-8.000 -0.3210 0.05017 0.04025 -0.1003 0.8127 0.0825
-7.750 -0.3065 0.04851 0.03839 -0.0993 0.8064 0.0832
-7.500 -0.2863 0.04670 0.03633 -0.0990 0.8020 0.0842
-7.250 -0.2796 0.04580 0.03527 -0.0966 0.7932 0.0852
-7.000 -0.2641 0.04452 0.03372 -0.0953 0.7865 0.0868
-6.750 -0.2417 0.04293 0.03177 -0.0948 0.7819 0.0889
-6.500 -0.2217 0.04219 0.03102 -0.0940 0.7760 0.0907
-6.250 -0.2090 0.04168 0.03043 -0.0920 0.7676 0.0925
-6.000 -0.1836 0.04057 0.02913 -0.0916 0.7622 0.0948
-5.750 -0.1522 0.03931 0.02766 -0.0919 0.7583 0.0974
-5.500 -0.1425 0.03918 0.02756 -0.0894 0.7489 0.0992
-5.250 -0.1195 0.03853 0.02683 -0.0886 0.7425 0.1029
-5.000 -0.0892 0.03762 0.02584 -0.0887 0.7380 0.1078
-4.750 -0.0711 0.03730 0.02548 -0.0872 0.7310 0.1126
-4.500 -0.0555 0.03706 0.02522 -0.0854 0.7232 0.1175
-4.250 -0.0280 0.03637 0.02444 -0.0851 0.7182 0.1259
-4.000 0.0030 0.03547 0.02356 -0.0852 0.7146 0.1389
-3.750 0.0068 0.03576 0.02393 -0.0821 0.7048 0.1492
-3.500 0.0281 0.03513 0.02346 -0.0812 0.6988 0.1718
-3.250 0.0559 0.03422 0.02279 -0.0812 0.6947 0.2131
-3.000 0.0710 0.03410 0.02290 -0.0796 0.6879 0.2584
-2.750 0.0812 0.03424 0.02322 -0.0772 0.6795 0.3032
-2.500 0.1046 0.03364 0.02293 -0.0764 0.6747 0.3723
-2.250 0.1301 0.03285 0.02266 -0.0752 0.6713 0.4697
-2.000 0.1273 0.03370 0.02387 -0.0709 0.6606 0.5295
-1.750 0.1456 0.03366 0.02419 -0.0681 0.6547 0.6155
-1.500 0.1732 0.03346 0.02406 -0.0664 0.6509 0.6905
-1.250 0.1879 0.03397 0.02461 -0.0636 0.6440 0.7395
-1.000 0.1978 0.03482 0.02553 -0.0606 0.6350 0.7816
-0.750 0.2332 0.03489 0.02553 -0.0603 0.6306 0.8319
-0.500 0.2854 0.03483 0.02530 -0.0625 0.6276 0.8847
-0.250 0.3163 0.03617 0.02658 -0.0640 0.6180 0.9221
0.000 0.3712 0.03665 0.02688 -0.0690 0.6118 0.9504
0.250 0.4370 0.03653 0.02651 -0.0756 0.6079 0.9689
0.500 0.5037 0.03614 0.02586 -0.0822 0.6049 0.9848
1.000 0.5053 0.03836 0.02799 -0.0774 0.5872 1.0000
1.250 0.5255 0.03818 0.02763 -0.0761 0.5836 1.0000
1.750 0.4718 0.04145 0.03079 -0.0626 0.5650 1.0000
2.000 0.5018 0.04126 0.03042 -0.0625 0.5622 1.0000
2.500 0.4753 0.04527 0.03430 -0.0544 0.5439 1.0000
2.750 0.4764 0.04712 0.03607 -0.0524 0.5367 1.0000
4.250 0.5544 0.05452 0.04299 -0.0468 0.5028 1.0000
4.750 0.5557 0.05941 0.04784 -0.0446 0.4871 1.0000
5.250 0.5599 0.06421 0.05259 -0.0428 0.4720 1.0000
5.500 0.5886 0.06425 0.05257 -0.0426 0.4691 1.0000
6.000 0.5937 0.06909 0.05737 -0.0411 0.4538 1.0000
6.250 0.6233 0.06900 0.05723 -0.0408 0.4510 1.0000
6.750 0.6279 0.07401 0.06223 -0.0395 0.4353 1.0000
7.000 0.6579 0.07382 0.06198 -0.0392 0.4325 1.0000
7.500 0.6600 0.07924 0.06743 -0.0381 0.4165 1.0000
7.750 0.6899 0.07902 0.06717 -0.0377 0.4139 1.0000
8.250 0.6889 0.08499 0.07318 -0.0369 0.3975 1.0000
8.500 0.7180 0.08481 0.07298 -0.0365 0.3950 1.0000
8.750 0.6916 0.09076 0.07900 -0.0363 0.3822 1.0000
9.000 0.7140 0.09134 0.07956 -0.0360 0.3786 1.0000
9.250 0.7422 0.09123 0.07943 -0.0356 0.3763 1.0000
9.500 0.7135 0.09770 0.08599 -0.0358 0.3634 1.0000
9.750 0.7350 0.09840 0.08668 -0.0355 0.3601 1.0000
10.000 0.7618 0.09847 0.08674 -0.0351 0.3580 1.0000
10.250 0.7313 0.10546 0.09381 -0.0358 0.3456 1.0000
10.500 0.7517 0.10628 0.09463 -0.0355 0.3424 1.0000
10.750 0.7750 0.10678 0.09513 -0.0352 0.3402 1.0000
11.000 0.7441 0.11425 0.10269 -0.0365 0.3292 1.0000
11.250 0.7616 0.11549 0.10395 -0.0364 0.3261 1.0000
11.500 0.7843 0.11606 0.10452 -0.0361 0.3239 1.0000
11.750 0.7558 0.12344 0.11199 -0.0378 0.3146 1.0000
12.000 0.7669 0.12568 0.11426 -0.0381 0.3114 1.0000
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Polar data table (+)
Polar graphs
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