cr001sm (cr001sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 500,000 Max Cl/Cd: 105.23 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr001sm-il-500000-n5.txt Download as CSV file: xf-cr001sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: cr001sm
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3585 0.10024 0.09796 -0.0289 1.0000 0.0100
-8.500 -0.3587 0.09767 0.09541 -0.0285 1.0000 0.0100
-8.250 -0.3607 0.09517 0.09295 -0.0278 1.0000 0.0100
-8.000 -0.3492 0.09115 0.08894 -0.0313 0.9984 0.0100
-7.750 -0.3348 0.08697 0.08477 -0.0356 0.9955 0.0100
-7.500 -0.3224 0.08290 0.08070 -0.0397 0.9913 0.0100
-7.000 -0.2908 0.07461 0.07240 -0.0486 0.9835 0.0095
-6.750 -0.2731 0.07039 0.06818 -0.0541 0.9783 0.0090
-6.500 -0.2475 0.06485 0.06262 -0.0629 0.9744 0.0086
-6.250 -0.2214 0.05900 0.05673 -0.0721 0.9693 0.0081
-6.000 -0.1905 0.05228 0.04994 -0.0826 0.9635 0.0081
-5.750 -0.1501 0.04426 0.04177 -0.0950 0.9601 0.0083
-5.500 -0.1154 0.03649 0.03374 -0.1037 0.9537 0.0085
-5.250 -0.0795 0.02848 0.02527 -0.1105 0.9485 0.0087
-5.000 -0.0452 0.02144 0.01757 -0.1144 0.9443 0.0095
-4.750 -0.0188 0.01730 0.01281 -0.1151 0.9368 0.0096
-4.500 0.0133 0.01465 0.00965 -0.1165 0.9324 0.0098
-4.250 0.0414 0.01327 0.00796 -0.1166 0.9255 0.0100
-4.000 0.0719 0.01184 0.00627 -0.1173 0.9196 0.0107
-3.750 0.1010 0.01128 0.00562 -0.1176 0.9124 0.0113
-3.500 0.1316 0.01073 0.00496 -0.1182 0.9052 0.0121
-3.250 0.1599 0.01020 0.00433 -0.1182 0.8965 0.0130
-3.000 0.1896 0.00991 0.00394 -0.1185 0.8882 0.0143
-2.750 0.2174 0.00932 0.00326 -0.1184 0.8785 0.0157
-2.500 0.2451 0.00895 0.00283 -0.1183 0.8684 0.0170
-2.250 0.2731 0.00869 0.00250 -0.1183 0.8579 0.0185
-2.000 0.3009 0.00848 0.00220 -0.1181 0.8469 0.0201
-1.750 0.3282 0.00830 0.00194 -0.1179 0.8350 0.0222
-1.500 0.3552 0.00811 0.00168 -0.1175 0.8223 0.0252
-1.250 0.3822 0.00801 0.00151 -0.1172 0.8095 0.0288
-1.000 0.4088 0.00790 0.00136 -0.1168 0.7959 0.0413
-0.750 0.4349 0.00764 0.00127 -0.1165 0.7819 0.1147
-0.500 0.4605 0.00739 0.00123 -0.1161 0.7672 0.2147
-0.250 0.4860 0.00720 0.00123 -0.1156 0.7516 0.3085
0.000 0.5097 0.00680 0.00130 -0.1150 0.7349 0.5025
0.250 0.5313 0.00639 0.00139 -0.1136 0.7162 0.6963
0.750 0.5922 0.00607 0.00139 -0.1143 0.6700 1.0000
1.000 0.6170 0.00623 0.00141 -0.1136 0.6474 1.0000
1.250 0.6420 0.00640 0.00145 -0.1129 0.6255 1.0000
1.500 0.6670 0.00657 0.00150 -0.1122 0.6043 1.0000
1.750 0.6919 0.00676 0.00157 -0.1115 0.5826 1.0000
2.000 0.7169 0.00694 0.00164 -0.1109 0.5618 1.0000
2.250 0.7419 0.00713 0.00173 -0.1103 0.5409 1.0000
2.500 0.7669 0.00733 0.00183 -0.1096 0.5204 1.0000
2.750 0.7917 0.00754 0.00196 -0.1090 0.4986 1.0000
3.000 0.8166 0.00776 0.00208 -0.1084 0.4775 1.0000
3.250 0.8411 0.00800 0.00222 -0.1077 0.4538 1.0000
3.500 0.8657 0.00824 0.00238 -0.1070 0.4305 1.0000
3.750 0.8900 0.00851 0.00255 -0.1064 0.4060 1.0000
4.000 0.9140 0.00881 0.00275 -0.1056 0.3785 1.0000
4.250 0.9376 0.00915 0.00297 -0.1049 0.3485 1.0000
4.500 0.9608 0.00953 0.00320 -0.1041 0.3159 1.0000
4.750 0.9838 0.00994 0.00347 -0.1032 0.2838 1.0000
5.000 1.0068 0.01035 0.00377 -0.1024 0.2545 1.0000
5.500 1.0527 0.01118 0.00439 -0.1007 0.2020 1.0000
5.750 1.0757 0.01159 0.00471 -0.0999 0.1799 1.0000
6.000 1.0982 0.01204 0.00506 -0.0991 0.1577 1.0000
6.250 1.1202 0.01253 0.00546 -0.0981 0.1327 1.0000
6.500 1.1417 0.01306 0.00587 -0.0971 0.1075 1.0000
6.750 1.1632 0.01359 0.00630 -0.0961 0.0861 1.0000
7.000 1.1840 0.01417 0.00678 -0.0950 0.0673 1.0000
7.250 1.2052 0.01470 0.00727 -0.0940 0.0530 1.0000
7.500 1.2260 0.01526 0.00780 -0.0929 0.0409 1.0000
7.750 1.2464 0.01584 0.00836 -0.0917 0.0310 1.0000
8.000 1.2663 0.01645 0.00895 -0.0904 0.0232 1.0000
8.250 1.2859 0.01708 0.00959 -0.0891 0.0182 1.0000
8.500 1.3060 0.01764 0.01020 -0.0879 0.0157 1.0000
8.750 1.3248 0.01828 0.01090 -0.0865 0.0134 1.0000
9.000 1.3428 0.01899 0.01166 -0.0849 0.0115 1.0000
9.250 1.3612 0.01960 0.01236 -0.0835 0.0106 1.0000
9.500 1.3785 0.02028 0.01312 -0.0818 0.0097 1.0000
9.750 1.3943 0.02103 0.01393 -0.0800 0.0088 1.0000
10.000 1.4053 0.02202 0.01501 -0.0774 0.0079 1.0000
10.250 1.4191 0.02270 0.01579 -0.0752 0.0075 1.0000
10.500 1.4323 0.02342 0.01660 -0.0730 0.0069 1.0000
10.750 1.4433 0.02429 0.01758 -0.0706 0.0064 1.0000
11.000 1.4539 0.02518 0.01856 -0.0682 0.0060 1.0000
11.250 1.4625 0.02622 0.01970 -0.0656 0.0057 1.0000
11.500 1.4681 0.02751 0.02109 -0.0628 0.0054 1.0000
11.750 1.4694 0.02915 0.02286 -0.0597 0.0050 1.0000
12.000 1.4752 0.03049 0.02433 -0.0573 0.0049 1.0000
12.250 1.4792 0.03203 0.02601 -0.0549 0.0048 1.0000
12.500 1.4824 0.03369 0.02781 -0.0527 0.0046 1.0000
12.750 1.4846 0.03553 0.02979 -0.0507 0.0045 1.0000
13.000 1.4853 0.03760 0.03201 -0.0488 0.0043 1.0000
13.250 1.4846 0.03991 0.03447 -0.0472 0.0042 1.0000
13.500 1.4831 0.04243 0.03716 -0.0459 0.0041 1.0000
13.750 1.4815 0.04511 0.03999 -0.0449 0.0039 1.0000
14.000 1.4762 0.04836 0.04340 -0.0442 0.0039 1.0000
14.250 1.4715 0.05175 0.04694 -0.0439 0.0038 1.0000
14.500 1.4659 0.05544 0.05079 -0.0441 0.0037 1.0000
14.750 1.4583 0.05962 0.05513 -0.0447 0.0037 1.0000
15.000 1.4497 0.06421 0.05987 -0.0457 0.0036 1.0000
15.250 1.4402 0.06922 0.06504 -0.0473 0.0036 1.0000
15.500 1.4297 0.07465 0.07063 -0.0493 0.0035 1.0000
15.750 1.4174 0.08069 0.07683 -0.0518 0.0035 1.0000
16.000 1.4040 0.08723 0.08354 -0.0548 0.0035 1.0000
16.250 1.3895 0.09428 0.09074 -0.0583 0.0035 1.0000
16.500 1.3733 0.10194 0.09857 -0.0622 0.0035 1.0000
16.750 1.3568 0.10997 0.10676 -0.0665 0.0035 1.0000
17.000 1.3404 0.11826 0.11520 -0.0711 0.0035 1.0000
17.250 1.3237 0.12685 0.12394 -0.0760 0.0035 1.0000
17.500 1.3066 0.13580 0.13304 -0.0812 0.0035 1.0000
17.750 1.2897 0.14491 0.14229 -0.0866 0.0035 1.0000
18.000 1.2735 0.15414 0.15166 -0.0921 0.0035 1.0000
18.250 1.2566 0.16387 0.16152 -0.0981 0.0035 1.0000
18.500 1.2382 0.17442 0.17220 -0.1046 0.0036 1.0000
18.750 1.2164 0.18663 0.18456 -0.1120 0.0037 1.0000
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Polar data table (+)
Polar graphs
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