St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: St. CYR 172 (Royer) (stcyr172-il) Reynolds number: 100,000 Max Cl/Cd: 37.69 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr172-il-100000.txt Download as CSV file: xf-stcyr172-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: St. CYR 172 (Royer)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8820 0.07696 0.07077 -0.0440 1.0000 0.0919
-13.250 -0.9255 0.06851 0.06213 -0.0484 1.0000 0.0911
-13.000 -0.9639 0.06220 0.05560 -0.0503 1.0000 0.0906
-12.750 -0.9951 0.05751 0.05067 -0.0498 1.0000 0.0903
-12.500 -1.0204 0.05385 0.04676 -0.0476 1.0000 0.0903
-12.250 -1.0416 0.05083 0.04349 -0.0441 1.0000 0.0904
-12.000 -1.0581 0.04826 0.04066 -0.0399 1.0000 0.0908
-11.750 -1.0689 0.04577 0.03785 -0.0362 1.0000 0.0915
-11.500 -1.0754 0.04353 0.03524 -0.0325 1.0000 0.0924
-11.250 -1.0616 0.04124 0.03295 -0.0312 1.0000 0.0942
-11.000 -1.0479 0.03963 0.03130 -0.0297 1.0000 0.0961
-10.750 -1.0372 0.03796 0.02949 -0.0276 1.0000 0.0980
-10.500 -1.0265 0.03622 0.02757 -0.0254 1.0000 0.1000
-10.250 -1.0157 0.03458 0.02567 -0.0231 1.0000 0.1023
-10.000 -1.0003 0.03298 0.02396 -0.0214 1.0000 0.1051
-9.750 -0.9824 0.03186 0.02294 -0.0200 1.0000 0.1085
-9.500 -0.9670 0.03066 0.02164 -0.0181 1.0000 0.1124
-9.250 -0.9512 0.02932 0.02013 -0.0162 1.0000 0.1164
-9.000 -0.9339 0.02831 0.01925 -0.0146 1.0000 0.1213
-8.750 -0.9193 0.02733 0.01810 -0.0123 1.0000 0.1282
-8.500 -0.9036 0.02634 0.01729 -0.0104 1.0000 0.1357
-8.250 -0.8892 0.02531 0.01626 -0.0081 1.0000 0.1460
-8.000 -0.8766 0.02430 0.01533 -0.0055 1.0000 0.1611
-7.750 -0.8665 0.02341 0.01456 -0.0025 1.0000 0.1832
-7.500 -0.8563 0.02275 0.01399 0.0005 1.0000 0.2068
-7.250 -0.8435 0.02237 0.01367 0.0032 1.0000 0.2258
-7.000 -0.8290 0.02208 0.01336 0.0056 1.0000 0.2415
-6.750 -0.8135 0.02179 0.01302 0.0079 1.0000 0.2552
-6.500 -0.7976 0.02154 0.01267 0.0102 1.0000 0.2679
-6.250 -0.7797 0.02126 0.01250 0.0120 1.0000 0.2787
-6.000 -0.7626 0.02099 0.01220 0.0140 1.0000 0.2902
-5.750 -0.7462 0.02076 0.01185 0.0162 1.0000 0.3026
-5.500 -0.7277 0.02052 0.01173 0.0180 1.0000 0.3137
-5.250 -0.7097 0.02023 0.01145 0.0198 1.0000 0.3253
-5.000 -0.6922 0.01993 0.01107 0.0218 1.0000 0.3379
-4.750 -0.6739 0.01969 0.01089 0.0236 1.0000 0.3509
-4.500 -0.6556 0.01941 0.01069 0.0254 1.0000 0.3646
-4.250 -0.6374 0.01909 0.01040 0.0271 1.0000 0.3792
-4.000 -0.6191 0.01874 0.01007 0.0289 1.0000 0.3944
-3.750 -0.6005 0.01839 0.00973 0.0305 1.0000 0.4103
-3.500 -0.5821 0.01807 0.00944 0.0322 1.0000 0.4271
-3.250 -0.5636 0.01776 0.00920 0.0338 1.0000 0.4442
-3.000 -0.5454 0.01746 0.00901 0.0355 1.0000 0.4619
-2.750 -0.5275 0.01720 0.00885 0.0371 1.0000 0.4797
-2.500 -0.5099 0.01697 0.00873 0.0388 1.0000 0.4977
-2.250 -0.4929 0.01679 0.00865 0.0404 1.0000 0.5163
-2.000 -0.4764 0.01665 0.00864 0.0421 1.0000 0.5357
-1.750 -0.4324 0.01668 0.00890 0.0386 0.9904 0.5633
-1.500 -0.3807 0.01667 0.00912 0.0338 0.9764 0.5965
-1.250 -0.3299 0.01653 0.00921 0.0294 0.9617 0.6342
-1.000 -0.2788 0.01625 0.00920 0.0253 0.9466 0.6808
-0.750 -0.2239 0.01592 0.00924 0.0210 0.9319 0.7373
-0.500 -0.1603 0.01581 0.00948 0.0158 0.9185 0.8039
-0.250 -0.0816 0.01584 0.00964 0.0082 0.9077 0.8597
0.000 -0.0001 0.01586 0.00969 0.0000 0.8899 0.8900
0.250 0.0817 0.01584 0.00964 -0.0082 0.8596 0.9077
0.500 0.1600 0.01581 0.00948 -0.0158 0.8036 0.9184
0.750 0.2238 0.01591 0.00924 -0.0210 0.7371 0.9319
1.000 0.2788 0.01625 0.00920 -0.0253 0.6806 0.9466
1.250 0.3299 0.01653 0.00921 -0.0294 0.6341 0.9618
1.500 0.3809 0.01667 0.00912 -0.0338 0.5965 0.9765
1.750 0.4324 0.01668 0.00890 -0.0386 0.5633 0.9904
2.000 0.4763 0.01664 0.00864 -0.0421 0.5359 1.0000
2.250 0.4928 0.01679 0.00865 -0.0404 0.5165 1.0000
2.500 0.5099 0.01697 0.00872 -0.0388 0.4978 1.0000
2.750 0.5274 0.01720 0.00885 -0.0371 0.4797 1.0000
3.000 0.5453 0.01746 0.00901 -0.0355 0.4619 1.0000
3.250 0.5636 0.01776 0.00920 -0.0338 0.4442 1.0000
3.500 0.5820 0.01807 0.00943 -0.0322 0.4271 1.0000
3.750 0.6005 0.01839 0.00973 -0.0305 0.4104 1.0000
4.000 0.6190 0.01874 0.01007 -0.0288 0.3945 1.0000
4.250 0.6374 0.01909 0.01040 -0.0271 0.3792 1.0000
4.500 0.6555 0.01940 0.01068 -0.0253 0.3645 1.0000
4.750 0.6738 0.01968 0.01088 -0.0235 0.3507 1.0000
5.000 0.6922 0.01993 0.01107 -0.0218 0.3379 1.0000
5.250 0.7097 0.02024 0.01146 -0.0198 0.3255 1.0000
5.500 0.7277 0.02052 0.01173 -0.0180 0.3139 1.0000
5.750 0.7462 0.02076 0.01186 -0.0162 0.3027 1.0000
6.000 0.7626 0.02099 0.01220 -0.0140 0.2902 1.0000
6.250 0.7796 0.02126 0.01250 -0.0120 0.2787 1.0000
6.500 0.7977 0.02154 0.01267 -0.0102 0.2680 1.0000
6.750 0.8135 0.02179 0.01302 -0.0079 0.2552 1.0000
7.000 0.8290 0.02207 0.01335 -0.0056 0.2415 1.0000
7.250 0.8435 0.02238 0.01367 -0.0032 0.2259 1.0000
7.500 0.8563 0.02275 0.01399 -0.0005 0.2069 1.0000
7.750 0.8665 0.02341 0.01456 0.0025 0.1833 1.0000
8.000 0.8767 0.02430 0.01533 0.0055 0.1611 1.0000
8.250 0.8894 0.02531 0.01626 0.0081 0.1462 1.0000
8.500 0.9036 0.02635 0.01729 0.0104 0.1357 1.0000
8.750 0.9195 0.02734 0.01810 0.0123 0.1283 1.0000
9.000 0.9340 0.02831 0.01925 0.0146 0.1214 1.0000
9.250 0.9513 0.02932 0.02013 0.0162 0.1165 1.0000
9.500 0.9671 0.03066 0.02163 0.0181 0.1124 1.0000
9.750 0.9825 0.03187 0.02295 0.0200 0.1086 1.0000
10.000 1.0004 0.03298 0.02397 0.0214 0.1051 1.0000
10.250 1.0158 0.03458 0.02567 0.0231 0.1023 1.0000
10.500 1.0266 0.03622 0.02756 0.0254 0.1000 1.0000
10.750 1.0374 0.03796 0.02950 0.0276 0.0980 1.0000
11.000 1.0481 0.03963 0.03130 0.0297 0.0961 1.0000
11.250 1.0620 0.04122 0.03293 0.0312 0.0942 1.0000
11.500 1.0759 0.04356 0.03528 0.0324 0.0924 1.0000
11.750 1.0687 0.04580 0.03789 0.0362 0.0915 1.0000
12.000 1.0586 0.04829 0.04068 0.0399 0.0908 1.0000
12.250 1.0417 0.05085 0.04351 0.0441 0.0904 1.0000
12.500 1.0212 0.05384 0.04675 0.0475 0.0903 1.0000
12.750 0.9950 0.05757 0.05073 0.0497 0.0903 1.0000
13.000 0.9648 0.06221 0.05561 0.0502 0.0906 1.0000
13.250 0.9267 0.06851 0.06213 0.0484 0.0911 1.0000
13.500 0.8819 0.07711 0.07092 0.0438 0.0919 1.0000
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Polar data table (+)
Polar graphs
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