St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: St. CYR 171 (Royer) (stcyr171-il) Reynolds number: 50,000 Max Cl/Cd: 24.73 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr171-il-50000.txt Download as CSV file: xf-stcyr171-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: St. CYR 171 (Royer)
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 -0.6236 0.08533 0.07758 -0.0195 1.0000 0.1741
-9.000 -0.6370 0.07942 0.07174 -0.0214 1.0000 0.1728
-8.750 -0.6589 0.07330 0.06567 -0.0226 1.0000 0.1713
-8.500 -0.6867 0.06613 0.05846 -0.0242 1.0000 0.1694
-8.250 -0.7164 0.05871 0.05086 -0.0251 1.0000 0.1687
-8.000 -0.7365 0.05250 0.04428 -0.0243 1.0000 0.1708
-7.750 -0.7544 0.04689 0.03797 -0.0220 1.0000 0.1752
-7.500 -0.7350 0.04549 0.03677 -0.0202 1.0000 0.1882
-7.250 -0.7262 0.04285 0.03400 -0.0179 1.0000 0.2026
-7.000 -0.7177 0.04027 0.03121 -0.0153 1.0000 0.2207
-6.750 -0.7070 0.03823 0.02898 -0.0130 1.0000 0.2401
-6.500 -0.6940 0.03646 0.02707 -0.0108 1.0000 0.2581
-6.250 -0.6823 0.03473 0.02516 -0.0086 1.0000 0.2776
-6.000 -0.6643 0.03382 0.02444 -0.0065 1.0000 0.2961
-5.750 -0.6437 0.03389 0.02473 -0.0042 1.0000 0.3121
-5.500 -0.6194 0.03473 0.02575 -0.0020 1.0000 0.3233
-5.250 -0.5999 0.03395 0.02492 -0.0002 1.0000 0.3297
-5.000 -0.5786 0.03376 0.02469 0.0015 1.0000 0.3374
-4.750 -0.5573 0.03364 0.02456 0.0033 1.0000 0.3446
-4.500 -0.5374 0.03310 0.02394 0.0049 1.0000 0.3523
-4.250 -0.5163 0.03285 0.02367 0.0065 1.0000 0.3589
-4.000 -0.4966 0.03238 0.02314 0.0080 1.0000 0.3680
-3.750 -0.4762 0.03229 0.02301 0.0097 1.0000 0.3791
-3.500 -0.4562 0.03218 0.02284 0.0113 1.0000 0.3912
-3.250 -0.4370 0.03199 0.02255 0.0129 1.0000 0.4048
-3.000 -0.4192 0.03196 0.02232 0.0144 1.0000 0.4219
-2.750 -0.4030 0.03151 0.02179 0.0164 1.0000 0.4403
-2.500 -0.3901 0.03064 0.02070 0.0185 1.0000 0.4650
-2.250 -0.3808 0.02814 0.01801 0.0207 1.0000 0.4981
-2.000 -0.3720 0.02361 0.01318 0.0225 1.0000 0.5474
-1.750 -0.3320 0.01935 0.00962 0.0200 1.0000 0.6054
-1.500 -0.3162 0.01916 0.01010 0.0235 1.0000 0.6432
-1.250 -0.3027 0.01924 0.01016 0.0261 1.0000 0.6853
-1.000 -0.2878 0.01919 0.01010 0.0282 1.0000 0.7194
-0.750 -0.2694 0.01907 0.01010 0.0299 1.0000 0.7482
-0.500 -0.2490 0.01901 0.01018 0.0310 1.0000 0.7752
-0.250 -0.2238 0.01904 0.01042 0.0314 1.0000 0.8061
0.000 -0.1901 0.01924 0.01079 0.0299 1.0000 0.8434
0.250 -0.1430 0.01959 0.01130 0.0255 1.0000 0.8889
0.500 -0.0902 0.02003 0.01181 0.0195 1.0000 0.9350
0.750 -0.0400 0.02050 0.01232 0.0134 1.0000 0.9860
1.000 -0.0300 0.02089 0.01260 0.0140 1.0000 1.0000
1.250 -0.0243 0.02129 0.01291 0.0156 1.0000 1.0000
1.500 0.0565 0.02229 0.01400 0.0040 0.9734 1.0000
1.750 0.1480 0.02275 0.01462 -0.0082 0.9393 1.0000
2.000 0.2443 0.02245 0.01457 -0.0197 0.9028 1.0000
2.250 0.3483 0.02115 0.01361 -0.0304 0.8578 1.0000
2.500 0.4172 0.01981 0.01243 -0.0337 0.7961 1.0000
2.750 0.4530 0.01925 0.01167 -0.0312 0.7125 1.0000
3.000 0.4683 0.01945 0.01140 -0.0263 0.6114 1.0000
3.250 0.4872 0.02007 0.01135 -0.0231 0.5326 1.0000
3.500 0.5087 0.02094 0.01187 -0.0214 0.4807 1.0000
3.750 0.5306 0.02174 0.01248 -0.0200 0.4460 1.0000
4.000 0.5538 0.02253 0.01304 -0.0188 0.4210 1.0000
4.250 0.5772 0.02340 0.01385 -0.0178 0.4017 1.0000
4.500 0.6012 0.02431 0.01467 -0.0169 0.3858 1.0000
4.750 0.6239 0.02528 0.01568 -0.0158 0.3709 1.0000
5.000 0.6460 0.02639 0.01690 -0.0148 0.3582 1.0000
5.250 0.6697 0.02763 0.01813 -0.0139 0.3487 1.0000
5.500 0.6905 0.02893 0.01965 -0.0127 0.3384 1.0000
5.750 0.7113 0.03036 0.02117 -0.0116 0.3286 1.0000
6.000 0.7312 0.03189 0.02288 -0.0103 0.3195 1.0000
6.250 0.7486 0.03356 0.02474 -0.0087 0.3090 1.0000
6.500 0.7665 0.03477 0.02596 -0.0070 0.2922 1.0000
6.750 0.7822 0.03575 0.02696 -0.0049 0.2714 1.0000
7.000 0.7979 0.03686 0.02810 -0.0029 0.2517 1.0000
7.250 0.8124 0.03859 0.02995 -0.0009 0.2349 1.0000
7.500 0.8245 0.04062 0.03212 0.0014 0.2170 1.0000
7.750 0.8346 0.04289 0.03452 0.0038 0.1996 1.0000
8.000 0.8480 0.04532 0.03697 0.0058 0.1860 1.0000
8.250 0.8438 0.04906 0.04124 0.0088 0.1783 1.0000
8.500 0.8622 0.05142 0.04346 0.0100 0.1698 1.0000
8.750 0.8468 0.05594 0.04853 0.0130 0.1669 1.0000
9.000 0.8285 0.06074 0.05368 0.0152 0.1651 1.0000
9.250 0.8047 0.06601 0.05919 0.0167 0.1652 1.0000
9.500 0.7755 0.07170 0.06500 0.0174 0.1665 1.0000
9.750 0.7477 0.07746 0.07078 0.0173 0.1681 1.0000
10.000 0.7270 0.08392 0.07723 0.0153 0.1695 1.0000
10.250 0.7162 0.09043 0.08375 0.0128 0.1711 1.0000
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Polar data table (+)
Polar graphs
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