St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: St. CYR 171 (Royer) (stcyr171-il) Reynolds number: 100,000 Max Cl/Cd: 29.99 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stcyr171-il-100000-n5.txt Download as CSV file: xf-stcyr171-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8459 0.08668 0.08054 -0.0249 1.0000 0.0449
-13.500 -0.8873 0.07575 0.06943 -0.0319 1.0000 0.0443
-13.250 -0.9163 0.06829 0.06179 -0.0363 1.0000 0.0443
-13.000 -0.9379 0.06229 0.05562 -0.0397 1.0000 0.0443
-12.750 -0.9556 0.05703 0.05019 -0.0427 1.0000 0.0444
-12.500 -0.9708 0.05257 0.04554 -0.0447 1.0000 0.0447
-12.250 -0.9827 0.04903 0.04181 -0.0451 1.0000 0.0449
-12.000 -0.9913 0.04623 0.03883 -0.0440 1.0000 0.0453
-11.750 -0.9968 0.04396 0.03638 -0.0420 1.0000 0.0456
-11.500 -1.0000 0.04202 0.03424 -0.0394 1.0000 0.0460
-11.250 -0.9990 0.04022 0.03233 -0.0369 1.0000 0.0465
-11.000 -0.9952 0.03858 0.03064 -0.0346 1.0000 0.0472
-10.750 -0.9895 0.03708 0.02908 -0.0324 1.0000 0.0481
-10.500 -0.9818 0.03569 0.02760 -0.0303 1.0000 0.0492
-10.250 -0.9725 0.03436 0.02618 -0.0282 1.0000 0.0506
-10.000 -0.9618 0.03309 0.02479 -0.0261 1.0000 0.0519
-9.750 -0.9502 0.03188 0.02342 -0.0240 1.0000 0.0533
-9.500 -0.9376 0.03074 0.02213 -0.0219 1.0000 0.0545
-9.250 -0.9250 0.02962 0.02096 -0.0198 1.0000 0.0559
-9.000 -0.9113 0.02857 0.01987 -0.0179 1.0000 0.0577
-8.750 -0.8963 0.02761 0.01884 -0.0160 1.0000 0.0601
-8.500 -0.8803 0.02672 0.01786 -0.0141 1.0000 0.0632
-8.250 -0.8640 0.02585 0.01698 -0.0123 1.0000 0.0678
-8.000 -0.8466 0.02507 0.01617 -0.0106 1.0000 0.0758
-7.750 -0.8286 0.02435 0.01551 -0.0091 1.0000 0.0863
-7.500 -0.8093 0.02378 0.01495 -0.0076 1.0000 0.0991
-7.250 -0.7889 0.02331 0.01445 -0.0063 1.0000 0.1110
-7.000 -0.7679 0.02291 0.01393 -0.0050 1.0000 0.1215
-6.750 -0.7468 0.02255 0.01351 -0.0038 1.0000 0.1310
-6.500 -0.7259 0.02219 0.01310 -0.0025 1.0000 0.1389
-6.250 -0.7046 0.02188 0.01274 -0.0013 1.0000 0.1479
-6.000 -0.6837 0.02155 0.01233 0.0001 1.0000 0.1551
-5.750 -0.6634 0.02125 0.01204 0.0015 1.0000 0.1617
-5.500 -0.6422 0.02097 0.01167 0.0028 1.0000 0.1692
-5.250 -0.6220 0.02068 0.01142 0.0043 1.0000 0.1751
-5.000 -0.6016 0.02042 0.01114 0.0058 1.0000 0.1804
-4.750 -0.5809 0.02017 0.01084 0.0072 1.0000 0.1867
-4.500 -0.5607 0.01994 0.01066 0.0086 1.0000 0.1943
-4.250 -0.5398 0.01973 0.01044 0.0099 1.0000 0.2041
-4.000 -0.5198 0.01953 0.01027 0.0114 1.0000 0.2126
-3.750 -0.4994 0.01935 0.01006 0.0128 1.0000 0.2218
-3.500 -0.4802 0.01917 0.00993 0.0144 1.0000 0.2293
-3.250 -0.4607 0.01902 0.00978 0.0159 1.0000 0.2373
-3.000 -0.4411 0.01890 0.00968 0.0174 0.9996 0.2456
-2.750 -0.4023 0.01881 0.00960 0.0150 0.9915 0.2591
-2.500 -0.3653 0.01871 0.00954 0.0130 0.9826 0.2739
-2.250 -0.3299 0.01867 0.00962 0.0114 0.9725 0.2896
-2.000 -0.2941 0.01892 0.01013 0.0099 0.9621 0.3088
-1.750 -0.2566 0.01989 0.01161 0.0087 0.9518 0.3332
-1.500 -0.2161 0.02136 0.01274 0.0066 0.9396 0.4169
-1.250 -0.1779 0.02205 0.01335 0.0050 0.9297 0.4296
-1.000 -0.1403 0.02248 0.01372 0.0034 0.9177 0.4408
-0.750 -0.1020 0.02236 0.01358 0.0018 0.9007 0.4502
-0.500 -0.0610 0.02208 0.01325 -0.0003 0.8781 0.4593
-0.250 -0.0239 0.02177 0.01287 -0.0015 0.8509 0.4681
0.000 0.0121 0.02148 0.01248 -0.0027 0.8233 0.4773
0.250 0.0449 0.02100 0.01187 -0.0032 0.7936 0.4879
0.500 0.0751 0.02053 0.01125 -0.0033 0.7631 0.4997
0.750 0.1019 0.01998 0.01058 -0.0029 0.7342 0.5099
1.000 0.1284 0.01956 0.01005 -0.0024 0.7067 0.5177
1.250 0.1542 0.01938 0.00978 -0.0016 0.6760 0.5221
1.500 0.1792 0.01918 0.00950 -0.0008 0.6402 0.5253
1.750 0.2039 0.01906 0.00927 0.0002 0.5974 0.5277
2.000 0.2283 0.01917 0.00915 0.0013 0.5500 0.5292
2.250 0.2517 0.01941 0.00914 0.0025 0.4974 0.5307
2.500 0.2741 0.01950 0.00901 0.0037 0.4271 0.5325
2.750 0.2947 0.01979 0.00890 0.0051 0.3482 0.5342
3.000 0.3166 0.02015 0.00898 0.0062 0.3063 0.5360
3.250 0.3398 0.02048 0.00918 0.0070 0.2805 0.5375
3.500 0.3633 0.02085 0.00943 0.0079 0.2621 0.5388
4.000 0.4113 0.02122 0.00975 0.0094 0.2370 0.5411
4.250 0.4350 0.02149 0.00995 0.0101 0.2285 0.5427
4.500 0.4600 0.02170 0.01022 0.0108 0.2203 0.5445
4.750 0.4843 0.02205 0.01054 0.0114 0.2130 0.5459
5.000 0.5088 0.02244 0.01094 0.0121 0.2058 0.5468
5.250 0.5335 0.02275 0.01130 0.0127 0.1972 0.5471
5.500 0.5575 0.02314 0.01165 0.0134 0.1893 0.5469
5.750 0.5823 0.02340 0.01204 0.0140 0.1807 0.5463
6.000 0.6062 0.02377 0.01243 0.0146 0.1739 0.5457
6.250 0.6307 0.02413 0.01290 0.0152 0.1673 0.5451
6.500 0.6547 0.02444 0.01331 0.0159 0.1599 0.5444
6.750 0.6777 0.02484 0.01374 0.0167 0.1533 0.5438
7.000 0.7014 0.02509 0.01419 0.0175 0.1443 0.5431
7.250 0.7234 0.02540 0.01452 0.0184 0.1358 0.5424
7.500 0.7467 0.02570 0.01502 0.0192 0.1259 0.5417
7.750 0.7686 0.02608 0.01549 0.0201 0.1166 0.5410
8.000 0.7900 0.02649 0.01600 0.0212 0.1056 0.5403
8.250 0.8111 0.02705 0.01665 0.0222 0.0933 0.5396
8.500 0.8308 0.02774 0.01740 0.0235 0.0824 0.5389
8.750 0.8491 0.02848 0.01815 0.0248 0.0747 0.5384
9.000 0.8672 0.02928 0.01905 0.0261 0.0685 0.5378
9.250 0.8835 0.03017 0.01997 0.0276 0.0644 0.5372
9.500 0.9000 0.03110 0.02105 0.0290 0.0610 0.5366
9.750 0.9150 0.03208 0.02215 0.0306 0.0586 0.5360
10.000 0.9283 0.03312 0.02327 0.0324 0.0568 0.5354
10.250 0.9392 0.03431 0.02450 0.0344 0.0553 0.5348
10.500 0.9513 0.03554 0.02595 0.0362 0.0541 0.5341
10.750 0.9617 0.03682 0.02742 0.0382 0.0529 0.5335
11.000 0.9684 0.03813 0.02890 0.0406 0.0515 0.5329
11.250 0.9731 0.03944 0.03035 0.0431 0.0503 0.5323
11.500 0.9768 0.04090 0.03193 0.0454 0.0492 0.5318
11.750 0.9796 0.04248 0.03360 0.0475 0.0481 0.5312
12.000 0.9819 0.04418 0.03541 0.0493 0.0474 0.5307
12.250 0.9834 0.04611 0.03747 0.0508 0.0467 0.5302
12.500 0.9830 0.04838 0.03986 0.0520 0.0462 0.5298
12.750 0.9774 0.05102 0.04275 0.0529 0.0458 0.5293
13.000 0.9687 0.05413 0.04610 0.0532 0.0455 0.5289
13.250 0.9565 0.05784 0.05006 0.0526 0.0451 0.5286
13.500 0.9402 0.06241 0.05486 0.0509 0.0448 0.5283
13.750 0.9198 0.06806 0.06073 0.0480 0.0448 0.5280
14.000 0.8924 0.07548 0.06837 0.0434 0.0449 0.5278
14.250 0.8514 0.08636 0.07945 0.0360 0.0453 0.5279
14.500 0.7664 0.10842 0.10170 0.0218 0.0461 0.5287
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