St. CYR 234 (Bartel 17-IC) (stcyr234-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: St. CYR 234 (Bartel 17-IC) (stcyr234-il) Reynolds number: 50,000 Max Cl/Cd: 27.97 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stcyr234-il-50000.txt Download as CSV file: xf-stcyr234-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: St. CYR 234 (Bartel 17-IC)
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3389 0.12940 0.12237 -0.0058 1.0000 0.2989
-11.500 -0.3512 0.12884 0.12186 -0.0042 1.0000 0.3061
-11.250 -0.4107 0.13260 0.12576 -0.0022 1.0000 0.3100
-11.000 -0.3651 0.12530 0.11841 -0.0012 1.0000 0.3147
-10.750 -0.3593 0.12320 0.11634 0.0005 1.0000 0.3209
-10.500 -0.3841 0.12339 0.11660 0.0024 1.0000 0.3287
-10.250 -0.4197 0.12342 0.11673 0.0045 1.0000 0.3319
-10.000 -0.3835 0.11844 0.11172 0.0054 1.0000 0.3369
-9.750 -0.3840 0.11680 0.11009 0.0072 1.0000 0.3445
-9.500 -0.4430 0.11870 0.11211 0.0109 1.0000 0.3511
-9.250 -0.4112 0.11371 0.10712 0.0112 1.0000 0.3560
-9.000 -0.4035 0.11151 0.10493 0.0128 1.0000 0.3632
-8.750 -0.4604 0.11259 0.10612 0.0176 1.0000 0.3714
-8.500 -0.4505 0.10899 0.10254 0.0187 1.0000 0.3756
-8.250 -0.4329 0.10628 0.09983 0.0198 1.0000 0.3824
-8.000 -0.4962 0.10685 0.10051 0.0222 1.0000 0.3936
-7.750 -0.4642 0.10274 0.09640 0.0249 1.0000 0.3982
-7.500 -0.4671 0.10103 0.09471 0.0270 1.0000 0.4094
-7.000 -0.4964 0.09758 0.09133 0.0290 1.0000 0.4352
-6.750 -0.4763 0.09432 0.08812 0.0325 1.0000 0.4405
-6.500 -0.4866 0.09255 0.08637 0.0337 1.0000 0.4572
-6.250 -0.4740 0.09019 0.08405 0.0365 1.0000 0.4657
-6.000 -0.4755 0.08813 0.08202 0.0385 1.0000 0.4816
-5.750 -0.4059 0.06736 0.05977 -0.0162 1.0000 0.2889
-5.500 -0.3918 0.06522 0.05768 -0.0153 1.0000 0.2853
-5.250 -0.3559 0.05888 0.05057 -0.0248 1.0000 0.2686
-5.000 -0.3359 0.05680 0.04831 -0.0258 1.0000 0.2680
-4.750 -0.3142 0.05482 0.04603 -0.0274 1.0000 0.2687
-4.500 -0.2937 0.05324 0.04422 -0.0282 1.0000 0.2701
-4.250 -0.2767 0.05237 0.04335 -0.0277 1.0000 0.2724
-4.000 -0.2581 0.05153 0.04242 -0.0277 1.0000 0.2745
-3.750 -0.2392 0.05084 0.04159 -0.0278 1.0000 0.2773
-3.500 -0.2202 0.05030 0.04088 -0.0279 1.0000 0.2814
-3.250 -0.2002 0.04988 0.04017 -0.0283 1.0000 0.2875
-3.000 -0.1834 0.04975 0.04002 -0.0279 1.0000 0.2937
-2.750 -0.1673 0.04991 0.04018 -0.0275 1.0000 0.3008
-2.500 -0.1479 0.05003 0.03999 -0.0278 1.0000 0.3102
-2.250 -0.1124 0.05178 0.04185 -0.0305 0.9920 0.3230
-2.000 -0.0760 0.05343 0.04347 -0.0335 0.9799 0.3411
-1.750 -0.0418 0.05494 0.04496 -0.0362 0.9655 0.3618
-1.500 -0.0023 0.05682 0.04682 -0.0395 0.9478 0.3898
-1.250 0.1193 0.05791 0.04819 -0.0510 0.8431 0.4634
-1.000 0.1746 0.05813 0.04852 -0.0534 0.8055 0.5143
-0.750 0.2242 0.05811 0.04855 -0.0555 0.7794 0.5670
-0.500 0.2790 0.05754 0.04813 -0.0590 0.7581 0.6329
-0.250 0.3356 0.05625 0.04809 -0.0629 0.7389 0.7990
0.000 0.3918 0.05653 0.04799 -0.0684 0.7187 1.0000
0.250 0.4261 0.05696 0.04815 -0.0694 0.6998 1.0000
0.500 0.4563 0.05738 0.04839 -0.0696 0.6811 1.0000
0.750 0.4860 0.05773 0.04860 -0.0696 0.6626 1.0000
1.000 0.5159 0.05797 0.04873 -0.0695 0.6442 1.0000
1.250 0.5471 0.05804 0.04871 -0.0693 0.6260 1.0000
1.500 0.5804 0.05791 0.04849 -0.0691 0.6087 1.0000
1.750 0.6372 0.05625 0.04676 -0.0703 0.5973 1.0000
2.000 0.6585 0.05656 0.04702 -0.0691 0.5788 1.0000
2.250 0.6785 0.05700 0.04742 -0.0679 0.5609 1.0000
2.750 0.7610 0.05435 0.04467 -0.0674 0.5374 1.0000
3.250 0.7733 0.05816 0.04846 -0.0643 0.5054 1.0000
3.500 0.8573 0.05227 0.04250 -0.0652 0.5018 1.0000
3.750 0.8418 0.05644 0.04667 -0.0629 0.4858 1.0000
4.000 0.9859 0.04599 0.03609 -0.0680 0.4826 1.0000
4.250 0.9335 0.05260 0.04276 -0.0627 0.4672 1.0000
4.500 0.8543 0.06418 0.05442 -0.0593 0.4505 1.0000
4.750 1.1156 0.04376 0.03358 -0.0707 0.4408 1.0000
5.000 1.1917 0.04260 0.03218 -0.0761 0.4236 1.0000
5.250 1.1451 0.04648 0.03629 -0.0679 0.4164 1.0000
5.500 1.2082 0.04602 0.03565 -0.0717 0.4011 1.0000
5.750 1.1778 0.04938 0.03919 -0.0657 0.3933 1.0000
6.000 1.2208 0.04983 0.03955 -0.0673 0.3801 1.0000
6.250 1.1539 0.05558 0.04556 -0.0589 0.3756 1.0000
6.500 1.0888 0.06320 0.05337 -0.0534 0.3696 1.0000
6.750 1.2972 0.05363 0.04321 -0.0671 0.3442 1.0000
7.000 1.2242 0.05902 0.04893 -0.0576 0.3423 1.0000
7.250 1.0359 0.07844 0.06877 -0.0488 0.3441 1.0000
7.500 0.7443 0.12456 0.11509 -0.0601 0.3517 1.0000
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Polar data table (+)
Polar graphs
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