PW106 (pw106-pw) Xfoil prediction polar at RE=2,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PW106 (pw106-pw) Reynolds number: 2,000,000 Max Cl/Cd: 94.69 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw106-pw-2000000.txt Download as CSV file: xf-pw106-pw-2000000.csv |
XFOIL Version 6.96
Calculated polar for: PW106
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 2.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5585 0.13391 0.13290 0.0304 1.0000 0.0021
-11.250 -0.7021 0.11593 0.11492 0.0379 1.0000 0.0021
-11.000 -0.7094 0.10936 0.10836 0.0347 1.0000 0.0022
-10.750 -0.7262 0.10061 0.09963 0.0301 1.0000 0.0022
-10.500 -0.7411 0.09266 0.09170 0.0254 1.0000 0.0023
-10.250 -0.7593 0.08416 0.08322 0.0196 1.0000 0.0024
-10.000 -0.7772 0.07564 0.07473 0.0117 1.0000 0.0025
-9.750 -0.8187 0.05612 0.05504 -0.0078 1.0000 0.0025
-9.500 -0.8706 0.03121 0.02934 -0.0138 1.0000 0.0028
-9.250 -0.8575 0.02750 0.02533 -0.0135 1.0000 0.0029
-9.000 -0.8377 0.02547 0.02312 -0.0133 1.0000 0.0031
-8.750 -0.8153 0.02413 0.02164 -0.0130 1.0000 0.0033
-5.500 -0.4870 0.01979 0.01619 -0.0091 0.8219 0.0019
-5.250 -0.4584 0.02132 0.01771 -0.0095 0.7991 0.0018
-5.000 -0.4317 0.02176 0.01795 -0.0097 0.7775 0.0018
-4.750 -0.4058 0.02126 0.01720 -0.0097 0.7571 0.0018
-2.250 -0.1357 0.01267 0.00700 -0.0077 0.5921 0.0018
-1.750 -0.0818 0.00722 0.00106 -0.0042 0.5682 0.0037
-1.500 -0.0534 0.00719 0.00102 -0.0042 0.5542 0.0046
-1.250 -0.0249 0.00720 0.00106 -0.0044 0.5404 0.0057
-0.750 0.0320 0.00729 0.00125 -0.0047 0.5127 0.0074
-0.500 0.0604 0.00710 0.00092 -0.0046 0.4986 0.0088
-0.250 0.0891 0.00707 0.00082 -0.0046 0.4847 0.0083
0.000 0.1177 0.00705 0.00074 -0.0046 0.4711 0.0081
0.250 0.1464 0.00705 0.00068 -0.0047 0.4576 0.0085
0.500 0.1751 0.00705 0.00068 -0.0047 0.4448 0.0150
0.750 0.2035 0.00703 0.00069 -0.0048 0.4312 0.0303
1.000 0.2311 0.00669 0.00068 -0.0048 0.4185 0.1657
1.250 0.2571 0.00597 0.00067 -0.0049 0.4063 0.4384
1.500 0.2702 0.00450 0.00076 -0.0017 0.3954 0.9541
1.750 0.3067 0.00460 0.00083 -0.0034 0.3810 0.9884
2.000 0.3434 0.00472 0.00088 -0.0053 0.3657 0.9940
2.250 0.3821 0.00485 0.00092 -0.0077 0.3496 0.9971
2.500 0.4212 0.00497 0.00098 -0.0102 0.3345 0.9998
2.750 0.4493 0.00507 0.00102 -0.0103 0.3214 1.0000
3.000 0.4761 0.00517 0.00107 -0.0101 0.3100 1.0000
3.250 0.5028 0.00531 0.00112 -0.0099 0.2926 1.0000
3.500 0.5285 0.00598 0.00133 -0.0099 0.1969 1.0000
3.750 0.5526 0.00713 0.00183 -0.0099 0.0649 1.0000
4.000 0.5777 0.00774 0.00221 -0.0096 0.0078 1.0000
4.250 0.6039 0.00794 0.00238 -0.0093 0.0013 1.0000
4.500 0.6303 0.00807 0.00248 -0.0090 0.0012 1.0000
4.750 0.6566 0.00822 0.00260 -0.0087 0.0011 1.0000
5.000 0.6831 0.00837 0.00273 -0.0085 0.0011 1.0000
5.250 0.7096 0.00854 0.00286 -0.0083 0.0012 1.0000
5.500 0.7363 0.00870 0.00301 -0.0081 0.0012 1.0000
5.750 0.7630 0.00890 0.00319 -0.0080 0.0013 1.0000
6.000 0.7898 0.00911 0.00339 -0.0079 0.0014 1.0000
6.250 0.8165 0.00933 0.00361 -0.0078 0.0015 1.0000
6.500 0.8432 0.00958 0.00388 -0.0076 0.0022 1.0000
6.750 0.8706 0.00966 0.00399 -0.0076 0.0021 1.0000
7.250 0.9246 0.01009 0.00448 -0.0074 0.0029 1.0000
7.500 0.9513 0.01037 0.00479 -0.0073 0.0032 1.0000
7.750 0.9780 0.01066 0.00512 -0.0072 0.0036 1.0000
8.000 1.0045 0.01098 0.00549 -0.0071 0.0040 1.0000
8.250 1.0308 0.01135 0.00594 -0.0070 0.0041 1.0000
8.500 1.0567 0.01180 0.00646 -0.0068 0.0038 1.0000
8.750 1.0819 0.01236 0.00713 -0.0065 0.0034 1.0000
9.000 1.1060 0.01313 0.00803 -0.0062 0.0030 1.0000
9.250 1.1266 0.01452 0.00965 -0.0055 0.0025 1.0000
9.500 1.1510 0.01505 0.01022 -0.0053 0.0023 1.0000
9.750 1.1729 0.01600 0.01130 -0.0048 0.0022 1.0000
10.000 1.1948 0.01687 0.01226 -0.0044 0.0020 1.0000
10.250 1.2158 0.01781 0.01329 -0.0039 0.0018 1.0000
10.500 1.2358 0.01882 0.01438 -0.0034 0.0016 1.0000
10.750 1.2552 0.01984 0.01548 -0.0029 0.0014 1.0000
11.000 1.2736 0.02089 0.01662 -0.0024 0.0013 1.0000
11.250 1.2911 0.02199 0.01779 -0.0018 0.0011 1.0000
11.500 1.3071 0.02315 0.01903 -0.0012 0.0010 1.0000
11.750 1.3207 0.02449 0.02045 -0.0004 0.0009 1.0000
12.000 1.3296 0.02614 0.02223 0.0007 0.0008 1.0000
12.250 1.3295 0.02816 0.02438 0.0022 0.0008 1.0000
12.500 1.3253 0.03096 0.02733 0.0026 0.0007 1.0000
12.750 1.3212 0.03430 0.03082 0.0019 0.0007 1.0000
13.000 1.3151 0.03836 0.03503 0.0002 0.0007 1.0000
13.250 1.3069 0.04300 0.03982 -0.0021 0.0007 1.0000
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Polar data table (+)
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