GOE 443 AIRFOIL (goe443-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 443 AIRFOIL (goe443-il) Reynolds number: 200,000 Max Cl/Cd: 34.03 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe443-il-200000.txt Download as CSV file: xf-goe443-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 443 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6433 0.09343 0.08994 -0.0009 1.0000 0.0265
-8.250 -0.6466 0.08903 0.08555 -0.0047 1.0000 0.0266
-8.000 -0.6466 0.08484 0.08130 -0.0072 1.0000 0.0266
-7.750 -0.6447 0.08074 0.07712 -0.0092 1.0000 0.0267
-7.500 -0.6414 0.07665 0.07292 -0.0106 1.0000 0.0267
-7.250 -0.6364 0.07260 0.06872 -0.0116 1.0000 0.0268
-7.000 -0.6404 0.06451 0.06059 -0.0131 1.0000 0.0275
-6.750 -0.6343 0.05968 0.05579 -0.0131 1.0000 0.0286
-6.500 -0.6250 0.05591 0.05195 -0.0131 1.0000 0.0297
-6.250 -0.6136 0.05218 0.04809 -0.0132 1.0000 0.0312
-6.000 -0.6000 0.04846 0.04417 -0.0131 1.0000 0.0330
-5.750 -0.5837 0.04484 0.04027 -0.0127 1.0000 0.0357
-5.500 -0.5587 0.04496 0.03965 -0.0108 1.0000 0.0394
-5.250 -0.5502 0.03732 0.03196 -0.0109 1.0000 0.0416
-5.000 -0.5327 0.03434 0.02891 -0.0102 1.0000 0.0454
-4.750 -0.5150 0.03190 0.02622 -0.0093 1.0000 0.0588
-4.500 -0.4957 0.02929 0.02327 -0.0081 1.0000 0.0696
-4.250 -0.4757 0.02703 0.02069 -0.0071 1.0000 0.0825
-4.000 -0.4552 0.02501 0.01854 -0.0061 1.0000 0.0978
-3.750 -0.4175 0.01979 0.01225 -0.0021 1.0000 0.0325
-3.500 -0.3913 0.01748 0.00952 -0.0004 1.0000 0.0290
-3.250 -0.3670 0.01571 0.00759 0.0009 1.0000 0.0296
-3.000 -0.3436 0.01443 0.00627 0.0020 1.0000 0.0332
-2.750 -0.3196 0.01377 0.00552 0.0031 1.0000 0.0399
-2.500 -0.2992 0.01223 0.00403 0.0046 1.0000 0.0459
-2.250 -0.2774 0.01123 0.00297 0.0060 1.0000 0.0656
-2.000 -0.2730 0.00805 0.00229 0.0098 1.0000 0.6152
-1.750 -0.1887 0.00761 0.00259 0.0008 1.0000 0.9747
-1.500 -0.1116 0.00766 0.00237 -0.0097 1.0000 1.0000
-1.250 -0.0940 0.00752 0.00215 -0.0081 1.0000 1.0000
-1.000 -0.0759 0.00742 0.00199 -0.0064 1.0000 1.0000
-0.750 -0.0573 0.00735 0.00185 -0.0048 1.0000 1.0000
-0.500 -0.0385 0.00730 0.00176 -0.0032 1.0000 1.0000
-0.250 -0.0193 0.00727 0.00171 -0.0016 1.0000 1.0000
0.000 0.0000 0.00726 0.00169 0.0000 1.0000 1.0000
0.250 0.0194 0.00727 0.00170 0.0016 1.0000 1.0000
0.500 0.0385 0.00730 0.00176 0.0031 1.0000 1.0000
0.750 0.0574 0.00735 0.00184 0.0048 1.0000 1.0000
1.000 0.0760 0.00742 0.00199 0.0064 1.0000 1.0000
1.250 0.0941 0.00752 0.00215 0.0080 1.0000 1.0000
1.500 0.1118 0.00766 0.00237 0.0097 1.0000 1.0000
1.750 0.1897 0.00760 0.00258 -0.0010 0.9741 1.0000
2.000 0.2729 0.00802 0.00229 -0.0098 0.6227 1.0000
2.250 0.2771 0.01119 0.00294 -0.0060 0.0667 1.0000
2.500 0.2989 0.01221 0.00401 -0.0046 0.0462 1.0000
2.750 0.3192 0.01376 0.00551 -0.0030 0.0399 1.0000
3.000 0.3432 0.01442 0.00626 -0.0019 0.0332 1.0000
3.250 0.3666 0.01570 0.00758 -0.0008 0.0295 1.0000
3.500 0.3910 0.01747 0.00950 0.0005 0.0289 1.0000
3.750 0.4171 0.01976 0.01221 0.0021 0.0324 1.0000
5.500 0.5589 0.04495 0.03965 0.0108 0.0394 1.0000
5.750 0.5840 0.04485 0.04029 0.0127 0.0356 1.0000
6.000 0.6002 0.04848 0.04419 0.0131 0.0330 1.0000
6.250 0.6138 0.05222 0.04812 0.0131 0.0311 1.0000
6.500 0.6253 0.05594 0.05198 0.0131 0.0297 1.0000
6.750 0.6345 0.05972 0.05582 0.0131 0.0285 1.0000
7.000 0.6409 0.06451 0.06060 0.0130 0.0276 1.0000
7.250 0.6368 0.07264 0.06877 0.0115 0.0268 1.0000
7.500 0.6418 0.07671 0.07298 0.0105 0.0267 1.0000
7.750 0.6454 0.08076 0.07714 0.0091 0.0267 1.0000
8.000 0.6474 0.08488 0.08135 0.0071 0.0266 1.0000
8.250 0.6472 0.08912 0.08564 0.0045 0.0266 1.0000
8.500 0.6444 0.09344 0.08996 0.0009 0.0265 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 443 AIRFOIL (goe443-il)