St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: St. CYR 171 (Royer) (stcyr171-il) Reynolds number: 100,000 Max Cl/Cd: 33.35 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr171-il-100000.txt Download as CSV file: xf-stcyr171-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7148 0.08122 0.07559 -0.0298 1.0000 0.0843
-11.000 -0.7569 0.07052 0.06490 -0.0366 1.0000 0.0828
-10.750 -0.8131 0.06089 0.05517 -0.0423 1.0000 0.0810
-10.500 -0.8583 0.05484 0.04889 -0.0410 1.0000 0.0800
-10.250 -0.8859 0.04947 0.04315 -0.0390 1.0000 0.0795
-10.000 -0.8981 0.04529 0.03858 -0.0365 1.0000 0.0798
-9.750 -0.9013 0.04182 0.03473 -0.0339 1.0000 0.0805
-9.500 -0.8983 0.03890 0.03143 -0.0314 1.0000 0.0819
-9.250 -0.8916 0.03639 0.02850 -0.0290 1.0000 0.0838
-9.000 -0.8803 0.03414 0.02598 -0.0269 1.0000 0.0860
-8.750 -0.8631 0.03282 0.02472 -0.0253 1.0000 0.0886
-8.500 -0.8469 0.03137 0.02316 -0.0235 1.0000 0.0916
-8.250 -0.8309 0.02973 0.02127 -0.0215 1.0000 0.0954
-8.000 -0.8143 0.02819 0.01963 -0.0196 1.0000 0.0995
-7.750 -0.7961 0.02739 0.01889 -0.0180 1.0000 0.1058
-7.500 -0.7790 0.02628 0.01771 -0.0160 1.0000 0.1147
-7.250 -0.7618 0.02535 0.01676 -0.0140 1.0000 0.1284
-7.000 -0.7449 0.02472 0.01622 -0.0120 1.0000 0.1474
-6.750 -0.7269 0.02435 0.01583 -0.0102 1.0000 0.1652
-6.500 -0.7079 0.02403 0.01540 -0.0086 1.0000 0.1789
-6.250 -0.6883 0.02387 0.01509 -0.0070 1.0000 0.1908
-6.000 -0.6686 0.02361 0.01491 -0.0056 1.0000 0.2006
-5.750 -0.6486 0.02322 0.01432 -0.0041 1.0000 0.2103
-5.500 -0.6281 0.02276 0.01392 -0.0027 1.0000 0.2180
-5.250 -0.6076 0.02241 0.01333 -0.0012 1.0000 0.2267
-5.000 -0.5872 0.02171 0.01276 0.0001 1.0000 0.2340
-4.750 -0.5665 0.02129 0.01219 0.0015 1.0000 0.2427
-4.500 -0.5464 0.02064 0.01165 0.0029 1.0000 0.2515
-4.250 -0.5262 0.02021 0.01111 0.0044 1.0000 0.2622
-4.000 -0.5073 0.01956 0.01059 0.0060 1.0000 0.2717
-3.750 -0.4884 0.01904 0.01008 0.0077 1.0000 0.2811
-3.500 -0.4710 0.01861 0.00973 0.0097 1.0000 0.2904
-3.250 -0.4544 0.01828 0.00947 0.0118 1.0000 0.2995
-3.000 -0.4378 0.01806 0.00933 0.0138 1.0000 0.3114
-2.750 -0.4224 0.01820 0.00972 0.0162 1.0000 0.3248
-2.500 -0.4062 0.01900 0.01093 0.0186 1.0000 0.3387
-2.250 -0.3886 0.02012 0.01236 0.0208 1.0000 0.3525
-1.750 -0.3496 0.02331 0.01527 0.0240 1.0000 0.4376
-1.500 -0.3348 0.02365 0.01553 0.0260 1.0000 0.4600
-1.250 -0.3218 0.02340 0.01514 0.0280 1.0000 0.4856
-1.000 -0.2872 0.02175 0.01330 0.0255 0.9911 0.5227
-0.750 -0.2498 0.01974 0.01118 0.0225 0.9818 0.5500
-0.500 -0.2103 0.01840 0.00981 0.0193 0.9711 0.5699
-0.250 -0.1609 0.01718 0.00884 0.0146 0.9591 0.5882
0.000 -0.0977 0.01611 0.00831 0.0081 0.9425 0.6072
0.250 -0.0385 0.01547 0.00822 0.0031 0.9240 0.6293
0.500 0.0153 0.01508 0.00805 -0.0008 0.9068 0.6589
0.750 0.0658 0.01480 0.00778 -0.0044 0.8905 0.6863
1.000 0.1108 0.01450 0.00753 -0.0068 0.8732 0.7057
1.250 0.1541 0.01417 0.00727 -0.0088 0.8536 0.7168
1.500 0.1945 0.01389 0.00702 -0.0102 0.8308 0.7257
1.750 0.2308 0.01366 0.00683 -0.0107 0.8044 0.7343
2.000 0.2634 0.01352 0.00669 -0.0106 0.7739 0.7427
2.250 0.2929 0.01345 0.00661 -0.0099 0.7385 0.7507
2.500 0.3206 0.01343 0.00655 -0.0087 0.6973 0.7605
2.750 0.3446 0.01342 0.00652 -0.0070 0.6409 0.7728
3.000 0.3673 0.01357 0.00641 -0.0048 0.5476 0.7880
3.250 0.3907 0.01428 0.00658 -0.0033 0.4265 0.8080
3.500 0.4254 0.01509 0.00698 -0.0046 0.3602 0.8420
3.750 0.4639 0.01593 0.00755 -0.0068 0.3282 0.8797
4.000 0.5032 0.01670 0.00821 -0.0091 0.3061 0.9147
4.250 0.5396 0.01748 0.00888 -0.0108 0.2908 0.9422
4.500 0.5717 0.01829 0.00956 -0.0117 0.2796 0.9635
4.750 0.6023 0.01899 0.01035 -0.0122 0.2694 0.9780
5.000 0.6311 0.01983 0.01104 -0.0125 0.2590 0.9864
5.250 0.6581 0.02036 0.01168 -0.0125 0.2476 0.9947
5.500 0.6857 0.02112 0.01243 -0.0126 0.2377 1.0000
5.750 0.7075 0.02166 0.01300 -0.0114 0.2283 1.0000
6.000 0.7291 0.02234 0.01371 -0.0103 0.2191 1.0000
6.250 0.7501 0.02280 0.01415 -0.0091 0.2087 1.0000
6.500 0.7701 0.02337 0.01487 -0.0077 0.1986 1.0000
6.750 0.7918 0.02397 0.01536 -0.0066 0.1892 1.0000
7.000 0.8101 0.02444 0.01608 -0.0049 0.1779 1.0000
7.250 0.8282 0.02493 0.01661 -0.0032 0.1645 1.0000
7.500 0.8443 0.02532 0.01707 -0.0011 0.1475 1.0000
7.750 0.8595 0.02595 0.01772 0.0012 0.1295 1.0000
8.000 0.8765 0.02699 0.01875 0.0031 0.1168 1.0000
8.250 0.8953 0.02789 0.01952 0.0046 0.1086 1.0000
8.500 0.9122 0.02939 0.02132 0.0065 0.1019 1.0000
8.750 0.9306 0.03029 0.02220 0.0080 0.0966 1.0000
9.000 0.9480 0.03195 0.02394 0.0095 0.0927 1.0000
9.250 0.9622 0.03393 0.02627 0.0115 0.0896 1.0000
9.500 0.9757 0.03587 0.02845 0.0135 0.0870 1.0000
9.750 0.9899 0.03751 0.03024 0.0152 0.0847 1.0000
10.000 1.0071 0.03923 0.03190 0.0163 0.0822 1.0000
10.250 1.0100 0.04198 0.03504 0.0191 0.0808 1.0000
10.500 1.0065 0.04504 0.03856 0.0222 0.0797 1.0000
10.750 0.9974 0.04856 0.04250 0.0254 0.0791 1.0000
11.000 0.9816 0.05237 0.04666 0.0286 0.0789 1.0000
11.250 0.9574 0.05616 0.05072 0.0322 0.0790 1.0000
11.500 0.9272 0.06039 0.05517 0.0347 0.0794 1.0000
11.750 0.8920 0.06592 0.06090 0.0344 0.0800 1.0000
12.000 0.8550 0.07317 0.06830 0.0310 0.0808 1.0000
12.250 0.8228 0.08173 0.07693 0.0261 0.0816 1.0000
12.500 0.7095 0.11496 0.11015 0.0053 0.0941 1.0000
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Polar data table (+)
Polar graphs
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