St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: St. CYR 172 (Royer) (stcyr172-il) Reynolds number: 50,000 Max Cl/Cd: 22.82 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr172-il-50000.txt Download as CSV file: xf-stcyr172-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5669 0.10705 0.09859 -0.0092 1.0000 0.2141
-10.500 -0.7007 0.08028 0.07208 -0.0284 1.0000 0.1867
-10.250 -0.7473 0.07085 0.06267 -0.0321 1.0000 0.1846
-10.000 -0.8015 0.06363 0.05541 -0.0311 1.0000 0.1818
-9.750 -0.8445 0.05809 0.04969 -0.0279 1.0000 0.1812
-9.500 -0.8717 0.05356 0.04489 -0.0244 1.0000 0.1828
-9.250 -0.8934 0.04942 0.04035 -0.0205 1.0000 0.1856
-9.000 -0.8841 0.04725 0.03817 -0.0184 1.0000 0.1922
-8.750 -0.8822 0.04475 0.03547 -0.0155 1.0000 0.1998
-8.500 -0.8738 0.04264 0.03329 -0.0130 1.0000 0.2090
-8.250 -0.8721 0.04031 0.03071 -0.0096 1.0000 0.2209
-8.000 -0.8591 0.03902 0.02948 -0.0071 1.0000 0.2376
-7.750 -0.8409 0.03848 0.02916 -0.0047 1.0000 0.2590
-7.500 -0.8296 0.03772 0.02838 -0.0016 1.0000 0.2819
-7.250 -0.8206 0.03682 0.02735 0.0016 1.0000 0.3024
-7.000 -0.8005 0.03668 0.02734 0.0038 1.0000 0.3216
-6.750 -0.7859 0.03604 0.02664 0.0063 1.0000 0.3383
-6.500 -0.7711 0.03550 0.02607 0.0089 1.0000 0.3552
-6.250 -0.7517 0.03548 0.02617 0.0112 1.0000 0.3746
-6.000 -0.7337 0.03524 0.02602 0.0136 1.0000 0.3935
-5.750 -0.7228 0.03422 0.02488 0.0163 1.0000 0.4089
-5.500 -0.7025 0.03341 0.02412 0.0181 1.0000 0.4217
-5.250 -0.6878 0.03215 0.02278 0.0201 1.0000 0.4328
-5.000 -0.6776 0.03073 0.02114 0.0225 1.0000 0.4451
-4.750 -0.6572 0.02977 0.02025 0.0241 1.0000 0.4565
-4.500 -0.6412 0.02868 0.01909 0.0260 1.0000 0.4696
-4.250 -0.6254 0.02767 0.01803 0.0280 1.0000 0.4847
-4.000 -0.6090 0.02676 0.01708 0.0299 1.0000 0.5011
-3.750 -0.5916 0.02593 0.01626 0.0318 1.0000 0.5185
-3.500 -0.5732 0.02523 0.01561 0.0337 1.0000 0.5374
-3.250 -0.5546 0.02463 0.01511 0.0356 1.0000 0.5577
-3.000 -0.5362 0.02410 0.01466 0.0376 1.0000 0.5793
-2.750 -0.5187 0.02359 0.01420 0.0396 1.0000 0.6025
-2.500 -0.5012 0.02313 0.01382 0.0416 1.0000 0.6271
-2.250 -0.4816 0.02280 0.01362 0.0434 1.0000 0.6527
-2.000 -0.4639 0.02244 0.01335 0.0453 1.0000 0.6813
-1.750 -0.4432 0.02224 0.01331 0.0470 1.0000 0.7119
-1.500 -0.4228 0.02217 0.01343 0.0490 1.0000 0.7451
-1.250 -0.4007 0.02229 0.01373 0.0507 1.0000 0.7833
-1.000 -0.3702 0.02271 0.01432 0.0511 1.0000 0.8278
-0.750 -0.3132 0.02356 0.01526 0.0468 1.0000 0.8796
-0.500 -0.2007 0.02498 0.01663 0.0322 1.0000 0.9259
-0.250 -0.0759 0.02580 0.01740 0.0136 1.0000 0.9697
0.000 -0.0001 0.02570 0.01728 0.0000 1.0000 1.0000
0.250 0.0765 0.02580 0.01740 -0.0137 0.9695 1.0000
0.500 0.2015 0.02496 0.01661 -0.0323 0.9257 1.0000
0.750 0.3132 0.02356 0.01526 -0.0468 0.8797 1.0000
1.000 0.3704 0.02270 0.01431 -0.0511 0.8276 1.0000
1.250 0.4006 0.02229 0.01374 -0.0507 0.7831 1.0000
1.500 0.4228 0.02216 0.01342 -0.0490 0.7452 1.0000
1.750 0.4431 0.02224 0.01331 -0.0471 0.7120 1.0000
2.000 0.4638 0.02244 0.01335 -0.0453 0.6815 1.0000
2.250 0.4816 0.02280 0.01362 -0.0434 0.6529 1.0000
2.500 0.5012 0.02314 0.01383 -0.0416 0.6273 1.0000
2.750 0.5187 0.02359 0.01420 -0.0396 0.6026 1.0000
3.000 0.5362 0.02409 0.01466 -0.0376 0.5793 1.0000
3.250 0.5546 0.02463 0.01511 -0.0356 0.5577 1.0000
3.500 0.5732 0.02523 0.01561 -0.0337 0.5374 1.0000
3.750 0.5916 0.02593 0.01626 -0.0318 0.5186 1.0000
4.000 0.6089 0.02676 0.01709 -0.0299 0.5012 1.0000
4.250 0.6254 0.02767 0.01803 -0.0280 0.4847 1.0000
4.500 0.6412 0.02868 0.01909 -0.0260 0.4696 1.0000
4.750 0.6572 0.02977 0.02024 -0.0240 0.4564 1.0000
5.000 0.6775 0.03072 0.02114 -0.0225 0.4451 1.0000
5.250 0.6877 0.03215 0.02279 -0.0201 0.4329 1.0000
5.500 0.7025 0.03341 0.02412 -0.0181 0.4217 1.0000
5.750 0.7226 0.03423 0.02489 -0.0163 0.4090 1.0000
6.000 0.7338 0.03523 0.02600 -0.0136 0.3935 1.0000
6.250 0.7516 0.03548 0.02617 -0.0112 0.3746 1.0000
6.500 0.7708 0.03553 0.02611 -0.0088 0.3554 1.0000
6.750 0.7858 0.03605 0.02666 -0.0063 0.3384 1.0000
7.000 0.8005 0.03667 0.02733 -0.0038 0.3215 1.0000
7.250 0.8203 0.03684 0.02738 -0.0016 0.3025 1.0000
7.500 0.8297 0.03771 0.02837 0.0016 0.2820 1.0000
7.750 0.8408 0.03849 0.02916 0.0047 0.2590 1.0000
8.000 0.8592 0.03900 0.02946 0.0071 0.2376 1.0000
8.250 0.8713 0.04037 0.03080 0.0097 0.2211 1.0000
8.500 0.8738 0.04264 0.03328 0.0130 0.2090 1.0000
8.750 0.8824 0.04474 0.03546 0.0155 0.1998 1.0000
9.000 0.8840 0.04727 0.03819 0.0184 0.1923 1.0000
9.250 0.8937 0.04942 0.04034 0.0205 0.1857 1.0000
9.500 0.8720 0.05354 0.04487 0.0244 0.1828 1.0000
9.750 0.8447 0.05810 0.04971 0.0279 0.1812 1.0000
10.000 0.8019 0.06368 0.05546 0.0311 0.1820 1.0000
10.250 0.7476 0.07087 0.06269 0.0320 0.1846 1.0000
10.500 0.7010 0.08031 0.07211 0.0283 0.1867 1.0000
10.750 0.6053 0.10147 0.09309 0.0142 0.2021 1.0000
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Polar data table (+)
Polar graphs
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