GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 382 AIRFOIL (goe382-il) Reynolds number: 100,000 Max Cl/Cd: 39.74 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe382-il-100000-n5.txt Download as CSV file: xf-goe382-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 382 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0596 0.09497 0.08944 -0.0953 0.8297 0.0552
-10.500 -0.0570 0.09156 0.08602 -0.0964 0.8184 0.0548
-10.000 -0.1467 0.06388 0.05810 -0.1168 0.8031 0.0503
-9.750 -0.1733 0.05774 0.05172 -0.1211 0.7928 0.0500
-9.500 -0.1983 0.05377 0.04753 -0.1212 0.7821 0.0498
-9.250 -0.2142 0.05022 0.04365 -0.1203 0.7737 0.0497
-9.000 -0.2223 0.04709 0.04018 -0.1191 0.7649 0.0496
-8.750 -0.2239 0.04426 0.03697 -0.1177 0.7571 0.0496
-8.500 -0.2199 0.04169 0.03398 -0.1162 0.7507 0.0498
-8.250 -0.2139 0.03943 0.03131 -0.1146 0.7425 0.0501
-8.000 -0.1993 0.03778 0.02938 -0.1136 0.7362 0.0507
-7.750 -0.1804 0.03668 0.02815 -0.1129 0.7298 0.0513
-7.500 -0.1626 0.03549 0.02679 -0.1119 0.7227 0.0519
-7.250 -0.1433 0.03415 0.02519 -0.1111 0.7169 0.0525
-7.000 -0.1235 0.03288 0.02365 -0.1102 0.7109 0.0529
-6.750 -0.1034 0.03172 0.02227 -0.1093 0.7042 0.0534
-6.500 -0.0809 0.03059 0.02088 -0.1086 0.6986 0.0539
-6.250 -0.0572 0.02956 0.01960 -0.1080 0.6935 0.0545
-6.000 -0.0351 0.02871 0.01858 -0.1072 0.6869 0.0551
-5.750 -0.0107 0.02793 0.01767 -0.1067 0.6813 0.0558
-5.500 0.0153 0.02725 0.01690 -0.1064 0.6767 0.0567
-5.250 0.0385 0.02676 0.01636 -0.1058 0.6709 0.0580
-5.000 0.0624 0.02625 0.01575 -0.1052 0.6650 0.0597
-4.750 0.0879 0.02571 0.01509 -0.1048 0.6601 0.0614
-4.500 0.1142 0.02518 0.01450 -0.1045 0.6558 0.0630
-4.250 0.1360 0.02482 0.01414 -0.1036 0.6497 0.0646
-4.000 0.1600 0.02443 0.01366 -0.1029 0.6442 0.0665
-3.750 0.1848 0.02396 0.01317 -0.1024 0.6395 0.0686
-3.500 0.2098 0.02359 0.01269 -0.1019 0.6351 0.0717
-3.250 0.2305 0.02329 0.01243 -0.1008 0.6290 0.0755
-3.000 0.2536 0.02292 0.01202 -0.1001 0.6237 0.0814
-2.750 0.2782 0.02242 0.01150 -0.0996 0.6193 0.0901
-2.500 0.3018 0.02199 0.01123 -0.0990 0.6148 0.1045
-2.250 0.3227 0.02183 0.01126 -0.0980 0.6086 0.1463
-2.000 0.3467 0.02159 0.01112 -0.0974 0.6033 0.1852
-1.750 0.3715 0.02116 0.01098 -0.0971 0.5990 0.2560
-1.500 0.3944 0.02092 0.01097 -0.0965 0.5941 0.3284
-1.250 0.4142 0.02073 0.01109 -0.0953 0.5880 0.3996
-1.000 0.4347 0.02031 0.01123 -0.0939 0.5829 0.5419
-0.750 0.4595 0.02010 0.01123 -0.0928 0.5787 0.6455
-0.500 0.4803 0.02015 0.01147 -0.0912 0.5733 0.7084
-0.250 0.5019 0.02028 0.01169 -0.0898 0.5674 0.7558
0.000 0.5289 0.02033 0.01174 -0.0892 0.5624 0.7980
0.250 0.5621 0.02035 0.01169 -0.0896 0.5583 0.8467
0.500 0.5911 0.02069 0.01208 -0.0898 0.5516 0.8915
0.750 0.6295 0.02091 0.01224 -0.0918 0.5458 0.9294
1.000 0.6777 0.02103 0.01219 -0.0957 0.5411 0.9593
1.250 0.7271 0.02132 0.01239 -0.1003 0.5350 0.9844
1.500 0.7717 0.02157 0.01255 -0.1043 0.5284 1.0000
1.750 0.7879 0.02167 0.01252 -0.1025 0.5240 1.0000
2.000 0.8064 0.02178 0.01249 -0.1010 0.5200 1.0000
2.250 0.8135 0.02218 0.01289 -0.0978 0.5140 1.0000
2.500 0.8284 0.02241 0.01304 -0.0958 0.5090 1.0000
2.750 0.8491 0.02252 0.01301 -0.0946 0.5048 1.0000
3.000 0.8643 0.02282 0.01325 -0.0927 0.5000 1.0000
3.250 0.8760 0.02324 0.01365 -0.0903 0.4944 1.0000
3.500 0.8951 0.02348 0.01381 -0.0890 0.4899 1.0000
3.750 0.9196 0.02362 0.01382 -0.0886 0.4863 1.0000
4.000 0.9323 0.02411 0.01430 -0.0864 0.4813 1.0000
4.250 0.9455 0.02458 0.01476 -0.0844 0.4761 1.0000
4.500 0.9661 0.02485 0.01495 -0.0834 0.4718 1.0000
4.750 0.9928 0.02498 0.01495 -0.0834 0.4683 1.0000
5.000 0.9995 0.02566 0.01566 -0.0805 0.4633 1.0000
5.250 1.0107 0.02626 0.01627 -0.0783 0.4587 1.0000
5.500 1.0305 0.02664 0.01660 -0.0773 0.4548 1.0000
5.750 1.0570 0.02682 0.01668 -0.0774 0.4515 1.0000
6.000 1.0677 0.02754 0.01742 -0.0753 0.4471 1.0000
6.250 1.0743 0.02846 0.01839 -0.0729 0.4421 1.0000
6.500 1.0920 0.02899 0.01890 -0.0719 0.4380 1.0000
6.750 1.1171 0.02927 0.01910 -0.0718 0.4349 1.0000
7.000 1.1426 0.02959 0.01935 -0.0718 0.4320 1.0000
7.250 1.1369 0.03120 0.02111 -0.0683 0.4269 1.0000
7.500 1.1460 0.03224 0.02218 -0.0666 0.4226 1.0000
7.750 1.1666 0.03272 0.02263 -0.0661 0.4191 1.0000
8.000 1.1958 0.03282 0.02266 -0.0665 0.4163 1.0000
8.250 1.1997 0.03421 0.02412 -0.0645 0.4123 1.0000
8.500 1.1892 0.03653 0.02658 -0.0614 0.4073 1.0000
8.750 1.1994 0.03773 0.02782 -0.0602 0.4036 1.0000
9.000 1.2223 0.03815 0.02822 -0.0601 0.4008 1.0000
9.250 1.2541 0.03803 0.02804 -0.0606 0.3984 1.0000
9.500 1.2213 0.04218 0.03240 -0.0566 0.3924 1.0000
9.750 1.1999 0.04599 0.03636 -0.0540 0.3865 1.0000
10.000 1.2200 0.04659 0.03695 -0.0537 0.3838 1.0000
10.250 1.2496 0.04644 0.03679 -0.0539 0.3819 1.0000
10.500 1.2853 0.04587 0.03617 -0.0545 0.3803 1.0000
10.750 1.1495 0.06102 0.05174 -0.0488 0.3653 1.0000
11.000 1.1826 0.06014 0.05085 -0.0488 0.3642 1.0000
11.250 1.2179 0.05911 0.04979 -0.0489 0.3632 1.0000
11.750 1.1188 0.07627 0.06724 -0.0467 0.3447 1.0000
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Polar data table (+)
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