St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: St. CYR 172 (Royer) (stcyr172-il) Reynolds number: 50,000 Max Cl/Cd: 26.99 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stcyr172-il-50000-n5.txt Download as CSV file: xf-stcyr172-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7365 0.09455 0.08586 -0.0269 1.0000 0.0942
-12.750 -0.8193 0.07581 0.06688 -0.0385 1.0000 0.0936
-12.500 -0.8578 0.06703 0.05784 -0.0431 1.0000 0.0938
-12.250 -0.8835 0.06105 0.05161 -0.0452 1.0000 0.0945
-12.000 -0.9010 0.05656 0.04685 -0.0457 1.0000 0.0955
-11.750 -0.9037 0.05377 0.04397 -0.0450 1.0000 0.0969
-11.500 -0.9009 0.05168 0.04186 -0.0440 1.0000 0.0986
-11.250 -0.9016 0.04952 0.03962 -0.0427 1.0000 0.1008
-11.000 -0.9037 0.04732 0.03729 -0.0409 1.0000 0.1034
-10.750 -0.9059 0.04512 0.03486 -0.0388 1.0000 0.1064
-10.500 -0.9036 0.04349 0.03320 -0.0365 1.0000 0.1095
-10.250 -0.9003 0.04211 0.03183 -0.0339 1.0000 0.1130
-10.000 -0.8966 0.04049 0.03008 -0.0314 1.0000 0.1176
-9.750 -0.8901 0.03899 0.02851 -0.0290 1.0000 0.1225
-9.500 -0.8836 0.03771 0.02723 -0.0266 1.0000 0.1289
-9.250 -0.8764 0.03634 0.02578 -0.0241 1.0000 0.1369
-9.000 -0.8691 0.03507 0.02443 -0.0215 1.0000 0.1473
-8.750 -0.8608 0.03396 0.02339 -0.0189 1.0000 0.1580
-8.500 -0.8519 0.03291 0.02234 -0.0164 1.0000 0.1707
-8.250 -0.8422 0.03199 0.02139 -0.0138 1.0000 0.1845
-8.000 -0.8312 0.03117 0.02051 -0.0113 1.0000 0.1984
-7.750 -0.8191 0.03044 0.01969 -0.0090 1.0000 0.2122
-7.500 -0.8058 0.02987 0.01913 -0.0067 1.0000 0.2250
-7.250 -0.7916 0.02934 0.01861 -0.0044 1.0000 0.2373
-7.000 -0.7776 0.02887 0.01810 -0.0022 1.0000 0.2508
-6.750 -0.7638 0.02846 0.01769 0.0001 1.0000 0.2654
-6.500 -0.7498 0.02811 0.01731 0.0025 1.0000 0.2804
-6.250 -0.7352 0.02770 0.01683 0.0047 1.0000 0.2947
-6.000 -0.7185 0.02733 0.01648 0.0067 1.0000 0.3073
-5.750 -0.7010 0.02688 0.01604 0.0086 1.0000 0.3189
-5.500 -0.6834 0.02632 0.01538 0.0104 1.0000 0.3305
-5.250 -0.6642 0.02580 0.01485 0.0119 1.0000 0.3407
-5.000 -0.6448 0.02525 0.01426 0.0134 1.0000 0.3511
-4.750 -0.6264 0.02474 0.01364 0.0151 1.0000 0.3638
-4.500 -0.6067 0.02429 0.01325 0.0166 1.0000 0.3755
-4.250 -0.5873 0.02385 0.01279 0.0181 1.0000 0.3883
-4.000 -0.5681 0.02342 0.01233 0.0196 1.0000 0.4022
-3.750 -0.5486 0.02303 0.01195 0.0210 1.0000 0.4165
-3.500 -0.5286 0.02266 0.01164 0.0224 1.0000 0.4310
-3.250 -0.5087 0.02233 0.01135 0.0237 1.0000 0.4464
-3.000 -0.4889 0.02203 0.01111 0.0251 1.0000 0.4628
-2.750 -0.4691 0.02176 0.01091 0.0264 1.0000 0.4798
-2.500 -0.4498 0.02152 0.01076 0.0278 1.0000 0.4980
-2.250 -0.4317 0.02133 0.01068 0.0293 1.0000 0.5172
-1.750 -0.3588 0.02105 0.01075 0.0255 0.9804 0.5739
-1.500 -0.3165 0.02087 0.01080 0.0228 0.9645 0.6104
-1.250 -0.2738 0.02069 0.01083 0.0202 0.9480 0.6522
-1.000 -0.2271 0.02053 0.01094 0.0173 0.9319 0.6956
-0.750 -0.1742 0.02046 0.01112 0.0136 0.9159 0.7403
-0.500 -0.1134 0.02051 0.01134 0.0087 0.8996 0.7826
-0.250 -0.0517 0.02056 0.01146 0.0035 0.8804 0.8211
0.000 0.0000 0.02058 0.01149 0.0000 0.8535 0.8536
0.250 0.0518 0.02056 0.01146 -0.0035 0.8211 0.8805
0.500 0.1134 0.02051 0.01134 -0.0087 0.7827 0.8997
0.750 0.1742 0.02046 0.01112 -0.0136 0.7404 0.9159
1.000 0.2270 0.02053 0.01094 -0.0173 0.6957 0.9318
1.250 0.2737 0.02069 0.01083 -0.0202 0.6521 0.9480
1.500 0.3164 0.02087 0.01080 -0.0228 0.6103 0.9645
1.750 0.3589 0.02105 0.01075 -0.0255 0.5737 0.9804
2.000 0.4035 0.02118 0.01066 -0.0289 0.5416 0.9949
2.250 0.4316 0.02132 0.01068 -0.0293 0.5173 1.0000
2.500 0.4497 0.02152 0.01076 -0.0278 0.4982 1.0000
2.750 0.4691 0.02176 0.01091 -0.0264 0.4799 1.0000
3.000 0.4887 0.02202 0.01110 -0.0250 0.4626 1.0000
3.250 0.5087 0.02233 0.01135 -0.0238 0.4466 1.0000
3.500 0.5285 0.02266 0.01163 -0.0224 0.4310 1.0000
3.750 0.5485 0.02303 0.01194 -0.0210 0.4165 1.0000
4.000 0.5681 0.02342 0.01233 -0.0196 0.4022 1.0000
4.250 0.5873 0.02384 0.01279 -0.0181 0.3883 1.0000
4.500 0.6066 0.02429 0.01325 -0.0166 0.3754 1.0000
4.750 0.6264 0.02474 0.01364 -0.0151 0.3638 1.0000
5.000 0.6448 0.02525 0.01426 -0.0134 0.3512 1.0000
5.250 0.6641 0.02580 0.01484 -0.0119 0.3408 1.0000
5.500 0.6834 0.02632 0.01538 -0.0104 0.3305 1.0000
5.750 0.7010 0.02688 0.01604 -0.0086 0.3189 1.0000
6.000 0.7185 0.02733 0.01648 -0.0067 0.3074 1.0000
6.250 0.7352 0.02770 0.01683 -0.0047 0.2948 1.0000
6.500 0.7497 0.02810 0.01729 -0.0025 0.2803 1.0000
6.750 0.7637 0.02846 0.01768 -0.0001 0.2653 1.0000
7.000 0.7775 0.02886 0.01811 0.0022 0.2507 1.0000
7.250 0.7915 0.02933 0.01860 0.0045 0.2372 1.0000
7.500 0.8058 0.02987 0.01913 0.0067 0.2249 1.0000
7.750 0.8191 0.03044 0.01970 0.0089 0.2123 1.0000
8.000 0.8312 0.03117 0.02051 0.0113 0.1984 1.0000
8.250 0.8421 0.03198 0.02138 0.0138 0.1844 1.0000
8.500 0.8518 0.03291 0.02233 0.0164 0.1704 1.0000
8.750 0.8607 0.03397 0.02339 0.0189 0.1577 1.0000
9.000 0.8690 0.03507 0.02444 0.0215 0.1471 1.0000
9.250 0.8766 0.03633 0.02577 0.0241 0.1369 1.0000
9.500 0.8836 0.03770 0.02722 0.0265 0.1287 1.0000
9.750 0.8904 0.03898 0.02850 0.0290 0.1225 1.0000
10.000 0.8968 0.04050 0.03009 0.0313 0.1175 1.0000
10.250 0.9005 0.04211 0.03182 0.0339 0.1129 1.0000
10.500 0.9039 0.04347 0.03318 0.0364 0.1094 1.0000
10.750 0.9064 0.04513 0.03489 0.0387 0.1064 1.0000
11.000 0.9041 0.04732 0.03729 0.0409 0.1033 1.0000
11.250 0.9021 0.04951 0.03961 0.0426 0.1007 1.0000
11.500 0.9017 0.05168 0.04186 0.0439 0.0986 1.0000
11.750 0.9046 0.05376 0.04395 0.0449 0.0969 1.0000
12.000 0.9014 0.05660 0.04689 0.0456 0.0954 1.0000
12.250 0.8838 0.06110 0.05166 0.0451 0.0944 1.0000
12.500 0.8590 0.06699 0.05780 0.0430 0.0938 1.0000
12.750 0.8199 0.07588 0.06696 0.0383 0.0936 1.0000
13.000 0.7356 0.09495 0.08626 0.0265 0.0942 1.0000
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