St. CYR 172 (Royer) (stcyr172-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: St. CYR 172 (Royer) (stcyr172-il) Reynolds number: 500,000 Max Cl/Cd: 61.7 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stcyr172-il-500000-n5.txt Download as CSV file: xf-stcyr172-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.1585 0.08664 0.08206 -0.0275 1.0000 0.0274
-17.750 -1.1664 0.08211 0.07747 -0.0295 1.0000 0.0277
-17.500 -1.1744 0.07765 0.07295 -0.0314 1.0000 0.0279
-17.250 -1.1829 0.07314 0.06837 -0.0334 1.0000 0.0281
-17.000 -1.1912 0.06874 0.06389 -0.0353 1.0000 0.0283
-16.750 -1.1992 0.06441 0.05947 -0.0372 1.0000 0.0285
-16.500 -1.2050 0.06036 0.05534 -0.0389 1.0000 0.0288
-16.250 -1.2117 0.05627 0.05115 -0.0406 1.0000 0.0290
-16.000 -1.2165 0.05241 0.04721 -0.0422 1.0000 0.0292
-15.750 -1.2180 0.04899 0.04369 -0.0437 1.0000 0.0296
-15.500 -1.2201 0.04562 0.04023 -0.0449 1.0000 0.0299
-15.250 -1.2205 0.04258 0.03708 -0.0460 1.0000 0.0302
-15.000 -1.2202 0.03978 0.03418 -0.0467 1.0000 0.0306
-14.750 -1.2177 0.03735 0.03166 -0.0471 1.0000 0.0309
-14.500 -1.2150 0.03510 0.02931 -0.0471 1.0000 0.0313
-14.250 -1.2104 0.03319 0.02729 -0.0469 1.0000 0.0317
-14.000 -1.2057 0.03145 0.02545 -0.0463 1.0000 0.0319
-13.750 -1.2036 0.02966 0.02359 -0.0452 1.0000 0.0322
-13.500 -1.2011 0.02808 0.02195 -0.0437 1.0000 0.0326
-13.250 -1.1960 0.02680 0.02062 -0.0421 1.0000 0.0330
-13.000 -1.1896 0.02570 0.01946 -0.0402 1.0000 0.0334
-12.750 -1.1815 0.02478 0.01849 -0.0382 1.0000 0.0338
-12.500 -1.1730 0.02395 0.01760 -0.0361 1.0000 0.0343
-12.250 -1.1642 0.02320 0.01680 -0.0337 1.0000 0.0348
-12.000 -1.1557 0.02252 0.01606 -0.0311 1.0000 0.0352
-11.750 -1.1473 0.02189 0.01537 -0.0282 1.0000 0.0356
-11.500 -1.1393 0.02133 0.01476 -0.0250 1.0000 0.0360
-11.250 -1.1307 0.02084 0.01421 -0.0218 1.0000 0.0365
-11.000 -1.1192 0.02036 0.01367 -0.0191 1.0000 0.0369
-10.750 -1.1077 0.01977 0.01304 -0.0164 1.0000 0.0375
-10.500 -1.0962 0.01915 0.01240 -0.0138 1.0000 0.0381
-10.250 -1.0827 0.01863 0.01185 -0.0113 1.0000 0.0387
-10.000 -1.0680 0.01816 0.01135 -0.0091 1.0000 0.0393
-9.750 -1.0524 0.01773 0.01089 -0.0069 1.0000 0.0400
-9.500 -1.0365 0.01731 0.01044 -0.0048 1.0000 0.0407
-9.250 -1.0201 0.01692 0.01001 -0.0027 1.0000 0.0414
-9.000 -1.0034 0.01656 0.00961 -0.0006 1.0000 0.0422
-8.750 -0.9865 0.01623 0.00925 0.0014 1.0000 0.0429
-8.500 -0.9718 0.01580 0.00880 0.0038 1.0000 0.0440
-8.250 -0.9484 0.01536 0.00836 0.0045 0.9991 0.0452
-8.000 -0.9167 0.01495 0.00793 0.0034 0.9967 0.0466
-7.750 -0.8834 0.01458 0.00754 0.0021 0.9938 0.0482
-7.500 -0.8509 0.01423 0.00715 0.0010 0.9900 0.0496
-7.250 -0.8190 0.01379 0.00671 0.0000 0.9857 0.0519
-7.000 -0.7860 0.01339 0.00631 -0.0012 0.9822 0.0550
-6.750 -0.7586 0.01305 0.00596 -0.0012 0.9759 0.0582
-6.500 -0.7282 0.01260 0.00555 -0.0019 0.9709 0.0651
-6.250 -0.7049 0.01188 0.00506 -0.0013 0.9627 0.0983
-6.000 -0.6745 0.01142 0.00475 -0.0019 0.9572 0.1259
-5.750 -0.6444 0.01115 0.00452 -0.0023 0.9498 0.1375
-5.500 -0.6088 0.01089 0.00428 -0.0039 0.9441 0.1476
-5.250 -0.5701 0.01058 0.00402 -0.0062 0.9367 0.1589
-5.000 -0.5268 0.01031 0.00377 -0.0095 0.9294 0.1680
-4.750 -0.4879 0.01006 0.00355 -0.0118 0.9218 0.1765
-4.500 -0.4486 0.00981 0.00332 -0.0142 0.9128 0.1867
-4.250 -0.4153 0.00961 0.00314 -0.0153 0.9015 0.1984
-4.000 -0.3849 0.00941 0.00298 -0.0158 0.8903 0.2135
-3.750 -0.3569 0.00922 0.00284 -0.0157 0.8766 0.2307
-3.500 -0.3308 0.00907 0.00271 -0.0152 0.8612 0.2475
-3.250 -0.3058 0.00892 0.00261 -0.0144 0.8430 0.2654
-3.000 -0.2812 0.00880 0.00249 -0.0135 0.8137 0.2833
-2.750 -0.2582 0.00877 0.00236 -0.0121 0.7643 0.3009
-2.500 -0.2361 0.00880 0.00227 -0.0107 0.7240 0.3159
-2.250 -0.2128 0.00885 0.00221 -0.0095 0.6919 0.3279
-2.000 -0.1897 0.00888 0.00216 -0.0083 0.6584 0.3376
-1.750 -0.1667 0.00897 0.00212 -0.0070 0.6180 0.3464
-1.500 -0.1453 0.00910 0.00207 -0.0055 0.5639 0.3553
-1.250 -0.1226 0.00924 0.00204 -0.0042 0.5160 0.3637
-1.000 -0.0995 0.00933 0.00202 -0.0031 0.4812 0.3730
-0.750 -0.0753 0.00942 0.00201 -0.0022 0.4548 0.3826
-0.500 -0.0509 0.00945 0.00200 -0.0014 0.4344 0.3926
-0.250 -0.0254 0.00948 0.00199 -0.0007 0.4212 0.4015
0.000 0.0000 0.00946 0.00199 0.0000 0.4114 0.4113
0.250 0.0254 0.00948 0.00199 0.0007 0.4015 0.4211
0.500 0.0509 0.00945 0.00200 0.0014 0.3923 0.4343
1.000 0.0994 0.00933 0.00202 0.0031 0.3727 0.4813
1.250 0.1226 0.00924 0.00204 0.0042 0.3637 0.5158
1.500 0.1451 0.00909 0.00207 0.0055 0.3554 0.5657
1.750 0.1668 0.00898 0.00212 0.0070 0.3464 0.6177
2.000 0.1899 0.00889 0.00216 0.0082 0.3377 0.6571
2.250 0.2129 0.00885 0.00221 0.0094 0.3279 0.6914
2.500 0.2361 0.00880 0.00227 0.0107 0.3165 0.7243
2.750 0.2582 0.00877 0.00236 0.0121 0.3006 0.7641
3.000 0.2812 0.00880 0.00249 0.0135 0.2826 0.8125
3.250 0.3056 0.00893 0.00261 0.0144 0.2639 0.8428
3.500 0.3307 0.00907 0.00271 0.0152 0.2472 0.8614
3.750 0.3567 0.00923 0.00284 0.0157 0.2300 0.8773
4.000 0.3849 0.00941 0.00298 0.0158 0.2137 0.8904
4.250 0.4152 0.00961 0.00314 0.0153 0.1981 0.9015
4.500 0.4486 0.00982 0.00332 0.0142 0.1865 0.9128
4.750 0.4878 0.01006 0.00355 0.0118 0.1766 0.9217
5.000 0.5268 0.01031 0.00377 0.0095 0.1678 0.9294
5.250 0.5698 0.01057 0.00402 0.0063 0.1592 0.9366
5.500 0.6088 0.01088 0.00428 0.0039 0.1476 0.9441
5.750 0.6446 0.01115 0.00452 0.0023 0.1375 0.9500
6.000 0.6748 0.01143 0.00476 0.0019 0.1255 0.9573
6.250 0.7049 0.01189 0.00506 0.0012 0.0975 0.9630
6.500 0.7284 0.01261 0.00556 0.0018 0.0646 0.9711
6.750 0.7587 0.01304 0.00596 0.0012 0.0583 0.9759
7.000 0.7860 0.01339 0.00632 0.0013 0.0550 0.9822
7.250 0.8191 0.01379 0.00671 0.0000 0.0519 0.9857
7.500 0.8512 0.01424 0.00715 -0.0011 0.0496 0.9901
7.750 0.8835 0.01458 0.00754 -0.0021 0.0482 0.9938
8.000 0.9166 0.01495 0.00793 -0.0034 0.0467 0.9967
8.250 0.9484 0.01537 0.00836 -0.0045 0.0452 0.9991
8.500 0.9715 0.01581 0.00881 -0.0038 0.0439 1.0000
8.750 0.9864 0.01624 0.00925 -0.0014 0.0429 1.0000
9.000 1.0034 0.01656 0.00961 0.0006 0.0422 1.0000
9.250 1.0201 0.01692 0.01001 0.0027 0.0414 1.0000
9.500 1.0364 0.01731 0.01044 0.0048 0.0407 1.0000
9.750 1.0524 0.01772 0.01089 0.0069 0.0400 1.0000
10.000 1.0679 0.01816 0.01135 0.0091 0.0394 1.0000
10.250 1.0826 0.01864 0.01185 0.0113 0.0387 1.0000
10.500 1.0961 0.01916 0.01241 0.0138 0.0381 1.0000
10.750 1.1080 0.01976 0.01303 0.0164 0.0375 1.0000
11.000 1.1191 0.02037 0.01368 0.0191 0.0369 1.0000
11.250 1.1302 0.02087 0.01424 0.0219 0.0366 1.0000
11.500 1.1394 0.02134 0.01477 0.0250 0.0360 1.0000
11.750 1.1475 0.02190 0.01538 0.0281 0.0356 1.0000
12.000 1.1560 0.02252 0.01606 0.0310 0.0352 1.0000
12.250 1.1648 0.02319 0.01679 0.0336 0.0347 1.0000
12.500 1.1733 0.02395 0.01761 0.0360 0.0343 1.0000
12.750 1.1820 0.02478 0.01849 0.0382 0.0339 1.0000
13.000 1.1896 0.02573 0.01950 0.0402 0.0334 1.0000
13.250 1.1967 0.02679 0.02061 0.0420 0.0330 1.0000
13.500 1.2022 0.02805 0.02192 0.0436 0.0326 1.0000
13.750 1.2044 0.02966 0.02359 0.0451 0.0322 1.0000
14.000 1.2083 0.03130 0.02530 0.0461 0.0318 1.0000
14.250 1.2133 0.03301 0.02712 0.0467 0.0315 1.0000
14.500 1.2176 0.03494 0.02914 0.0470 0.0312 1.0000
14.750 1.2199 0.03723 0.03153 0.0469 0.0309 1.0000
15.000 1.2215 0.03974 0.03415 0.0465 0.0306 1.0000
15.250 1.2216 0.04257 0.03707 0.0458 0.0303 1.0000
15.500 1.2219 0.04556 0.04016 0.0448 0.0299 1.0000
15.750 1.2212 0.04877 0.04346 0.0435 0.0296 1.0000
16.000 1.2178 0.05240 0.04719 0.0420 0.0293 1.0000
16.250 1.2134 0.05622 0.05111 0.0404 0.0291 1.0000
16.500 1.2076 0.06021 0.05520 0.0388 0.0289 1.0000
16.750 1.2014 0.06429 0.05936 0.0370 0.0287 1.0000
17.000 1.1935 0.06861 0.06377 0.0352 0.0284 1.0000
17.250 1.1857 0.07297 0.06820 0.0332 0.0282 1.0000
17.500 1.1775 0.07747 0.07277 0.0312 0.0280 1.0000
17.750 1.1694 0.08198 0.07733 0.0292 0.0277 1.0000
18.000 1.1614 0.08653 0.08195 0.0272 0.0274 1.0000
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Polar data table (+)
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