Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 50,000 Max Cl/Cd: 23.75 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-50000.txt Download as CSV file: xf-joukowsk0009-jf-50000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6406 0.11284 0.10575 0.0390 1.0000 0.3101
-9.000 -0.6432 0.11001 0.10296 0.0383 1.0000 0.3228
-8.750 -0.7752 0.07881 0.07200 -0.0018 1.0000 0.1473
-8.500 -0.7707 0.07322 0.06637 -0.0031 1.0000 0.1462
-8.250 -0.7715 0.06726 0.06031 -0.0051 1.0000 0.1443
-8.000 -0.7754 0.06076 0.05358 -0.0077 1.0000 0.1417
-7.750 -0.7782 0.05397 0.04633 -0.0100 1.0000 0.1391
-7.500 -0.7718 0.04831 0.04014 -0.0111 1.0000 0.1388
-7.250 -0.7588 0.04402 0.03532 -0.0114 1.0000 0.1433
-7.000 -0.7430 0.03997 0.03068 -0.0114 1.0000 0.1491
-6.750 -0.7210 0.03707 0.02759 -0.0110 1.0000 0.1566
-6.500 -0.6993 0.03441 0.02465 -0.0105 1.0000 0.1682
-6.250 -0.6761 0.03181 0.02176 -0.0100 1.0000 0.1811
-6.000 -0.6524 0.02980 0.01964 -0.0094 1.0000 0.2000
-5.750 -0.6281 0.02778 0.01753 -0.0087 1.0000 0.2227
-5.500 -0.6043 0.02618 0.01600 -0.0078 1.0000 0.2533
-5.250 -0.5809 0.02471 0.01459 -0.0068 1.0000 0.2936
-5.000 -0.5583 0.02351 0.01371 -0.0054 1.0000 0.3405
-4.750 -0.5363 0.02259 0.01308 -0.0036 1.0000 0.3938
-4.500 -0.5147 0.02188 0.01262 -0.0015 1.0000 0.4484
-4.250 -0.4933 0.02134 0.01225 0.0008 1.0000 0.5028
-4.000 -0.4725 0.02097 0.01209 0.0036 1.0000 0.5515
-3.750 -0.4521 0.02065 0.01191 0.0066 1.0000 0.5975
-3.500 -0.4322 0.02035 0.01167 0.0097 1.0000 0.6413
-3.250 -0.4131 0.02009 0.01150 0.0131 1.0000 0.6820
-3.000 -0.3942 0.01983 0.01130 0.0167 1.0000 0.7210
-2.750 -0.3759 0.01951 0.01099 0.0201 1.0000 0.7610
-2.500 -0.3560 0.01926 0.01075 0.0237 1.0000 0.7980
-2.250 -0.3333 0.01895 0.01042 0.0264 1.0000 0.8381
-2.000 -0.2950 0.01874 0.01012 0.0264 1.0000 0.8790
-1.750 -0.2241 0.01857 0.00971 0.0198 1.0000 0.9209
-1.500 -0.1262 0.01806 0.00889 0.0067 1.0000 0.9610
-1.250 -0.0327 0.01701 0.00764 -0.0071 1.0000 0.9996
-1.000 -0.0194 0.01644 0.00709 -0.0072 1.0000 1.0000
-0.750 -0.0081 0.01598 0.00667 -0.0066 1.0000 1.0000
-0.500 0.0010 0.01562 0.00636 -0.0055 1.0000 1.0000
-0.250 0.0048 0.01537 0.00618 -0.0035 1.0000 1.0000
0.000 0.0000 0.01528 0.00613 0.0000 1.0000 1.0000
0.250 -0.0048 0.01537 0.00618 0.0035 1.0000 1.0000
0.500 -0.0009 0.01562 0.00636 0.0055 1.0000 1.0000
0.750 0.0081 0.01598 0.00667 0.0066 1.0000 1.0000
1.000 0.0194 0.01644 0.00709 0.0072 1.0000 1.0000
1.250 0.0327 0.01701 0.00763 0.0071 0.9996 1.0000
1.500 0.1262 0.01806 0.00889 -0.0067 0.9610 1.0000
1.750 0.2241 0.01857 0.00970 -0.0198 0.9210 1.0000
2.000 0.2950 0.01874 0.01012 -0.0264 0.8791 1.0000
2.250 0.3333 0.01895 0.01042 -0.0264 0.8381 1.0000
2.500 0.3560 0.01926 0.01075 -0.0237 0.7979 1.0000
2.750 0.3760 0.01951 0.01099 -0.0201 0.7609 1.0000
3.000 0.3943 0.01983 0.01130 -0.0167 0.7210 1.0000
3.250 0.4132 0.02010 0.01150 -0.0132 0.6820 1.0000
3.500 0.4323 0.02035 0.01167 -0.0097 0.6413 1.0000
3.750 0.4522 0.02065 0.01191 -0.0066 0.5974 1.0000
4.000 0.4725 0.02097 0.01208 -0.0036 0.5514 1.0000
4.250 0.4934 0.02134 0.01225 -0.0008 0.5028 1.0000
4.500 0.5147 0.02188 0.01262 0.0015 0.4484 1.0000
4.750 0.5363 0.02259 0.01308 0.0036 0.3937 1.0000
5.000 0.5583 0.02351 0.01371 0.0054 0.3404 1.0000
5.250 0.5809 0.02471 0.01459 0.0068 0.2936 1.0000
5.500 0.6044 0.02618 0.01601 0.0078 0.2533 1.0000
5.750 0.6281 0.02779 0.01753 0.0087 0.2227 1.0000
6.000 0.6523 0.02980 0.01963 0.0094 0.2000 1.0000
6.250 0.6761 0.03181 0.02176 0.0100 0.1811 1.0000
6.500 0.6993 0.03441 0.02465 0.0105 0.1682 1.0000
6.750 0.7210 0.03706 0.02758 0.0110 0.1565 1.0000
7.000 0.7430 0.03997 0.03067 0.0114 0.1491 1.0000
7.250 0.7588 0.04402 0.03532 0.0114 0.1432 1.0000
7.500 0.7717 0.04830 0.04014 0.0111 0.1388 1.0000
7.750 0.7781 0.05396 0.04633 0.0100 0.1390 1.0000
8.000 0.7752 0.06079 0.05361 0.0076 0.1416 1.0000
8.250 0.7717 0.06726 0.06032 0.0051 0.1444 1.0000
8.500 0.7708 0.07324 0.06640 0.0031 0.1462 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Joukovsky f=0% t=9% (joukowsk0009-jf)