St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: St. CYR 171 (Royer) (stcyr171-il) Reynolds number: 50,000 Max Cl/Cd: 23.13 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stcyr171-il-50000-n5.txt Download as CSV file: xf-stcyr171-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6576 0.10002 0.09182 -0.0137 1.0000 0.0815
-11.250 -0.6757 0.09213 0.08399 -0.0176 1.0000 0.0827
-10.750 -0.8505 0.05774 0.04926 -0.0378 1.0000 0.0776
-10.500 -0.8546 0.05555 0.04705 -0.0362 1.0000 0.0791
-10.250 -0.8605 0.05285 0.04425 -0.0347 1.0000 0.0808
-10.000 -0.8649 0.04999 0.04121 -0.0332 1.0000 0.0831
-9.750 -0.8673 0.04694 0.03787 -0.0315 1.0000 0.0859
-9.500 -0.8668 0.04371 0.03421 -0.0296 1.0000 0.0892
-9.250 -0.8547 0.04237 0.03294 -0.0279 1.0000 0.0923
-9.000 -0.8437 0.04080 0.03128 -0.0261 1.0000 0.0967
-8.750 -0.8345 0.03850 0.02859 -0.0241 1.0000 0.1035
-8.500 -0.8209 0.03752 0.02773 -0.0222 1.0000 0.1097
-8.250 -0.8085 0.03598 0.02596 -0.0203 1.0000 0.1204
-8.000 -0.7941 0.03513 0.02506 -0.0186 1.0000 0.1317
-7.750 -0.7790 0.03430 0.02417 -0.0168 1.0000 0.1427
-7.500 -0.7633 0.03328 0.02285 -0.0152 1.0000 0.1544
-7.250 -0.7464 0.03278 0.02236 -0.0135 1.0000 0.1650
-7.000 -0.7292 0.03208 0.02155 -0.0119 1.0000 0.1754
-6.750 -0.7117 0.03148 0.02076 -0.0104 1.0000 0.1870
-6.500 -0.6938 0.03102 0.02033 -0.0088 1.0000 0.1974
-6.250 -0.6756 0.03037 0.01949 -0.0073 1.0000 0.2087
-6.000 -0.6568 0.02975 0.01881 -0.0058 1.0000 0.2181
-5.750 -0.6376 0.02901 0.01795 -0.0044 1.0000 0.2268
-5.500 -0.6181 0.02828 0.01717 -0.0029 1.0000 0.2347
-5.250 -0.5976 0.02754 0.01624 -0.0016 1.0000 0.2417
-5.000 -0.5777 0.02683 0.01555 -0.0001 1.0000 0.2477
-4.750 -0.5570 0.02620 0.01481 0.0013 1.0000 0.2547
-4.500 -0.5371 0.02558 0.01419 0.0028 1.0000 0.2618
-4.250 -0.5173 0.02500 0.01358 0.0043 1.0000 0.2712
-4.000 -0.4981 0.02446 0.01310 0.0059 1.0000 0.2806
-3.750 -0.4785 0.02398 0.01264 0.0075 1.0000 0.2917
-3.500 -0.4605 0.02364 0.01249 0.0094 1.0000 0.3021
-3.250 -0.4427 0.02352 0.01260 0.0115 1.0000 0.3137
-3.000 -0.4254 0.02373 0.01314 0.0137 1.0000 0.3267
-2.750 -0.4076 0.02419 0.01391 0.0161 1.0000 0.3404
-2.250 -0.3696 0.02672 0.01588 0.0196 1.0000 0.4281
-2.000 -0.3533 0.02732 0.01629 0.0216 1.0000 0.4457
-1.750 -0.3375 0.02734 0.01618 0.0235 1.0000 0.4604
-1.500 -0.3223 0.02707 0.01577 0.0254 1.0000 0.4748
-1.250 -0.3072 0.02663 0.01520 0.0271 1.0000 0.4884
-1.000 -0.2738 0.02590 0.01433 0.0251 0.9901 0.5051
-0.750 -0.2371 0.02505 0.01336 0.0225 0.9783 0.5208
-0.500 -0.1991 0.02414 0.01237 0.0198 0.9666 0.5349
-0.250 -0.1626 0.02342 0.01160 0.0175 0.9536 0.5467
0.000 -0.1231 0.02259 0.01080 0.0148 0.9412 0.5579
0.250 -0.0770 0.02201 0.01031 0.0110 0.9292 0.5673
0.500 -0.0237 0.02145 0.00987 0.0063 0.9100 0.5749
0.750 0.0372 0.02077 0.00935 0.0011 0.8810 0.5804
1.000 0.0882 0.02022 0.00892 -0.0020 0.8465 0.5839
1.250 0.1328 0.01986 0.00867 -0.0041 0.8163 0.5869
1.500 0.1706 0.01961 0.00852 -0.0050 0.7850 0.5903
1.750 0.2057 0.01941 0.00842 -0.0054 0.7512 0.5936
2.000 0.2366 0.01927 0.00838 -0.0050 0.7145 0.5974
2.250 0.2630 0.01923 0.00841 -0.0038 0.6722 0.6010
2.500 0.2867 0.01926 0.00850 -0.0022 0.6233 0.6039
2.750 0.3097 0.01939 0.00852 -0.0003 0.5643 0.6060
3.000 0.3316 0.01972 0.00859 0.0015 0.5001 0.6071
3.250 0.3527 0.02021 0.00882 0.0032 0.4326 0.6069
3.500 0.3745 0.02086 0.00907 0.0045 0.3773 0.6053
3.750 0.3974 0.02160 0.00944 0.0054 0.3421 0.6034
4.000 0.4219 0.02233 0.00996 0.0060 0.3181 0.6016
4.250 0.4474 0.02307 0.01056 0.0064 0.3011 0.6000
4.500 0.4736 0.02383 0.01119 0.0067 0.2870 0.5985
4.750 0.5003 0.02453 0.01191 0.0070 0.2736 0.5971
5.000 0.5269 0.02529 0.01265 0.0073 0.2631 0.5958
5.250 0.5540 0.02606 0.01346 0.0075 0.2542 0.5947
5.500 0.5811 0.02692 0.01427 0.0077 0.2468 0.5935
5.750 0.6068 0.02772 0.01527 0.0082 0.2381 0.5925
6.000 0.6327 0.02860 0.01612 0.0085 0.2304 0.5915
6.250 0.6580 0.02957 0.01728 0.0090 0.2236 0.5905
6.500 0.6820 0.03048 0.01836 0.0097 0.2155 0.5896
6.750 0.7041 0.03133 0.01930 0.0105 0.2051 0.5888
7.000 0.7244 0.03191 0.01987 0.0116 0.1923 0.5879
7.250 0.7420 0.03250 0.02068 0.0130 0.1782 0.5870
7.500 0.7598 0.03308 0.02137 0.0144 0.1652 0.5862
7.750 0.7791 0.03369 0.02196 0.0155 0.1549 0.5854
8.000 0.7968 0.03482 0.02348 0.0169 0.1437 0.5846
8.250 0.8144 0.03581 0.02455 0.0182 0.1339 0.5838
8.500 0.8302 0.03688 0.02579 0.0198 0.1229 0.5830
8.750 0.8444 0.03837 0.02751 0.0213 0.1126 0.5823
9.000 0.8596 0.03920 0.02828 0.0228 0.1054 0.5816
9.250 0.8710 0.04145 0.03094 0.0244 0.0984 0.5809
9.500 0.8832 0.04315 0.03280 0.0260 0.0938 0.5802
9.750 0.8973 0.04444 0.03405 0.0274 0.0906 0.5795
10.000 0.8996 0.04759 0.03764 0.0293 0.0876 0.5789
10.250 0.8972 0.05074 0.04115 0.0313 0.0851 0.5783
10.500 0.8920 0.05368 0.04436 0.0332 0.0829 0.5777
10.750 0.8829 0.05646 0.04733 0.0354 0.0814 0.5771
11.000 0.8783 0.05874 0.04970 0.0370 0.0795 0.5764
11.250 0.8753 0.06112 0.05213 0.0380 0.0781 0.5758
11.500 0.8650 0.06451 0.05558 0.0382 0.0771 0.5753
11.750 0.8323 0.07111 0.06238 0.0357 0.0772 0.5748
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Polar data table (+)
Polar graphs
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