PW51 (pw51-pw) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: PW51 (pw51-pw) Reynolds number: 500,000 Max Cl/Cd: 76.62 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw51-pw-500000.txt Download as CSV file: xf-pw51-pw-500000.csv |
XFOIL Version 6.96
Calculated polar for: PW51
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5112 0.11690 0.11488 0.0176 1.0000 0.0177
-10.750 -0.5088 0.11368 0.11166 0.0172 1.0000 0.0180
-10.500 -0.5061 0.11047 0.10846 0.0167 1.0000 0.0184
-10.250 -0.5051 0.10676 0.10476 0.0159 1.0000 0.0187
-10.000 -0.5048 0.10289 0.10090 0.0149 1.0000 0.0193
-9.750 -0.5066 0.09842 0.09644 0.0135 1.0000 0.0197
-9.500 -0.5094 0.09370 0.09174 0.0120 1.0000 0.0202
-9.250 -0.5138 0.08860 0.08665 0.0102 1.0000 0.0206
-9.000 -0.5198 0.08311 0.08118 0.0081 1.0000 0.0211
-7.250 -0.6731 0.02943 0.02525 -0.0137 1.0000 0.0128
-7.000 -0.6553 0.02602 0.02143 -0.0130 1.0000 0.0128
-6.750 -0.6365 0.02255 0.01756 -0.0123 1.0000 0.0131
-6.500 -0.6140 0.02021 0.01490 -0.0117 1.0000 0.0132
-6.250 -0.5900 0.01818 0.01258 -0.0110 1.0000 0.0132
-6.000 -0.5654 0.01652 0.01075 -0.0105 1.0000 0.0135
-5.750 -0.5400 0.01536 0.00949 -0.0101 1.0000 0.0140
-5.500 -0.5141 0.01444 0.00848 -0.0097 1.0000 0.0148
-5.250 -0.4880 0.01359 0.00755 -0.0093 1.0000 0.0158
-5.000 -0.4617 0.01290 0.00677 -0.0089 1.0000 0.0168
-4.750 -0.4371 0.01180 0.00560 -0.0084 1.0000 0.0185
-4.500 -0.4109 0.01140 0.00523 -0.0081 1.0000 0.0212
-4.250 -0.3859 0.01080 0.00458 -0.0076 1.0000 0.0243
-4.000 -0.3508 0.01024 0.00401 -0.0092 0.9902 0.0303
-3.750 -0.3151 0.00974 0.00352 -0.0108 0.9763 0.0403
-3.500 -0.2836 0.00929 0.00310 -0.0114 0.9588 0.0567
-3.250 -0.2582 0.00891 0.00284 -0.0107 0.9378 0.0848
-3.000 -0.2353 0.00854 0.00261 -0.0095 0.9160 0.1300
-2.750 -0.2121 0.00819 0.00240 -0.0083 0.8946 0.1846
-2.500 -0.1883 0.00779 0.00222 -0.0074 0.8727 0.2577
-2.000 -0.1401 0.00685 0.00188 -0.0059 0.8288 0.4691
-1.750 -0.1164 0.00635 0.00176 -0.0050 0.8070 0.5959
-1.500 -0.0930 0.00595 0.00170 -0.0038 0.7850 0.7109
-1.250 -0.0699 0.00570 0.00167 -0.0023 0.7640 0.8017
-1.000 -0.0463 0.00560 0.00167 -0.0008 0.7431 0.8651
-0.750 -0.0218 0.00561 0.00167 0.0006 0.7229 0.9110
-0.500 0.0057 0.00568 0.00167 0.0012 0.7028 0.9441
-0.250 0.0397 0.00578 0.00166 0.0003 0.6821 0.9651
0.000 0.0767 0.00589 0.00164 -0.0014 0.6613 0.9797
0.250 0.1183 0.00599 0.00161 -0.0042 0.6393 0.9891
0.500 0.1609 0.00610 0.00158 -0.0073 0.6173 0.9969
0.750 0.1952 0.00617 0.00154 -0.0087 0.5958 1.0000
1.000 0.2219 0.00625 0.00151 -0.0085 0.5763 1.0000
1.250 0.2487 0.00633 0.00150 -0.0083 0.5571 1.0000
1.500 0.2753 0.00642 0.00150 -0.0081 0.5377 1.0000
1.750 0.3019 0.00652 0.00151 -0.0078 0.5187 1.0000
2.000 0.3285 0.00664 0.00154 -0.0076 0.4997 1.0000
2.250 0.3550 0.00675 0.00158 -0.0073 0.4803 1.0000
2.500 0.3815 0.00689 0.00163 -0.0071 0.4607 1.0000
2.750 0.4079 0.00703 0.00169 -0.0068 0.4414 1.0000
3.000 0.4344 0.00718 0.00177 -0.0065 0.4215 1.0000
3.250 0.4609 0.00734 0.00186 -0.0062 0.4022 1.0000
3.500 0.4874 0.00752 0.00196 -0.0060 0.3835 1.0000
3.750 0.5140 0.00769 0.00208 -0.0058 0.3645 1.0000
4.000 0.5406 0.00788 0.00222 -0.0056 0.3459 1.0000
4.250 0.5672 0.00810 0.00236 -0.0054 0.3278 1.0000
4.500 0.5940 0.00830 0.00252 -0.0052 0.3105 1.0000
4.750 0.6207 0.00852 0.00270 -0.0050 0.2924 1.0000
5.000 0.6475 0.00875 0.00288 -0.0049 0.2749 1.0000
5.250 0.6742 0.00901 0.00308 -0.0048 0.2569 1.0000
5.500 0.7009 0.00927 0.00330 -0.0046 0.2393 1.0000
5.750 0.7276 0.00954 0.00354 -0.0045 0.2208 1.0000
6.000 0.7541 0.00985 0.00379 -0.0044 0.2017 1.0000
6.250 0.7804 0.01019 0.00407 -0.0043 0.1829 1.0000
6.500 0.8068 0.01053 0.00436 -0.0042 0.1644 1.0000
6.750 0.8329 0.01091 0.00470 -0.0041 0.1467 1.0000
7.000 0.8589 0.01132 0.00506 -0.0040 0.1305 1.0000
7.250 0.8848 0.01174 0.00545 -0.0038 0.1148 1.0000
7.500 0.9106 0.01218 0.00585 -0.0037 0.0994 1.0000
7.750 0.9360 0.01267 0.00632 -0.0036 0.0846 1.0000
8.000 0.9610 0.01323 0.00683 -0.0034 0.0699 1.0000
8.250 0.9856 0.01386 0.00741 -0.0031 0.0568 1.0000
8.500 1.0100 0.01451 0.00806 -0.0029 0.0469 1.0000
8.750 1.0339 0.01525 0.00882 -0.0026 0.0398 1.0000
9.000 1.0574 0.01599 0.00959 -0.0022 0.0347 1.0000
9.250 1.0803 0.01683 0.01051 -0.0018 0.0310 1.0000
9.500 1.1042 0.01742 0.01116 -0.0015 0.0278 1.0000
9.750 1.1238 0.01867 0.01247 -0.0009 0.0241 1.0000
10.000 1.1483 0.01910 0.01299 -0.0007 0.0220 1.0000
10.250 1.1708 0.01979 0.01372 -0.0004 0.0196 1.0000
10.500 1.1882 0.02118 0.01522 0.0003 0.0174 1.0000
10.750 1.2099 0.02190 0.01604 0.0008 0.0160 1.0000
11.000 1.2301 0.02275 0.01696 0.0012 0.0145 1.0000
11.250 1.2413 0.02465 0.01896 0.0023 0.0129 1.0000
11.500 1.2588 0.02569 0.02014 0.0030 0.0120 1.0000
11.750 1.2747 0.02681 0.02139 0.0037 0.0110 1.0000
12.000 1.2886 0.02804 0.02270 0.0045 0.0102 1.0000
12.250 1.2931 0.02988 0.02465 0.0058 0.0095 1.0000
12.500 1.2816 0.03321 0.02816 0.0072 0.0090 1.0000
12.750 1.2863 0.03536 0.03047 0.0071 0.0087 1.0000
13.000 1.2872 0.03820 0.03347 0.0064 0.0084 1.0000
13.250 1.2856 0.04164 0.03709 0.0051 0.0082 1.0000
13.500 1.2822 0.04558 0.04118 0.0032 0.0079 1.0000
13.750 1.2763 0.05004 0.04580 0.0009 0.0078 1.0000
14.000 1.2687 0.05492 0.05083 -0.0017 0.0076 1.0000
14.250 1.2589 0.06021 0.05626 -0.0046 0.0075 1.0000
14.500 1.2473 0.06586 0.06206 -0.0075 0.0074 1.0000
14.750 1.2340 0.07185 0.06819 -0.0106 0.0074 1.0000
15.000 1.2189 0.07820 0.07467 -0.0138 0.0074 1.0000
15.250 1.2029 0.08479 0.08139 -0.0171 0.0073 1.0000
15.500 1.1863 0.09175 0.08848 -0.0207 0.0073 1.0000
15.750 1.1692 0.09902 0.09588 -0.0244 0.0073 1.0000
16.000 1.1517 0.10662 0.10361 -0.0282 0.0073 1.0000
16.250 1.1335 0.11454 0.11166 -0.0323 0.0074 1.0000
16.500 1.1148 0.12288 0.12013 -0.0366 0.0074 1.0000
16.750 1.0944 0.13184 0.12923 -0.0412 0.0075 1.0000
17.000 1.0719 0.14172 0.13924 -0.0465 0.0076 1.0000
17.250 1.0458 0.15317 0.15084 -0.0526 0.0078 1.0000
17.500 1.0014 0.17084 0.16866 -0.0621 0.0083 1.0000
17.750 0.6552 0.18011 0.17807 -0.0439 0.0122 1.0000
18.000 0.6523 0.18456 0.18251 -0.0455 0.0124 1.0000
18.250 0.9109 0.23243 0.23015 -0.0887 0.0153 1.0000
18.500 0.9180 0.23642 0.23413 -0.0910 0.0148 1.0000
18.750 0.9255 0.24012 0.23784 -0.0932 0.0143 1.0000
19.000 0.9333 0.24347 0.24119 -0.0952 0.0139 1.0000
19.250 0.9418 0.24616 0.24389 -0.0968 0.0135 1.0000
19.500 0.9511 0.24801 0.24576 -0.0975 0.0131 1.0000
19.750 0.9557 0.25336 0.25110 -0.0997 0.0127 1.0000
20.000 0.9632 0.25764 0.25538 -0.1024 0.0127 1.0000
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