WORTMANN FX 049-915 AIRFOIL (fx049915-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 049-915 AIRFOIL (fx049915-il) Reynolds number: 200,000 Max Cl/Cd: 49.24 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx049915-il-200000-n5.txt Download as CSV file: xf-fx049915-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 049-915 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1648 0.10712 0.10120 -0.0552 0.5098 0.0188
-10.750 -0.1637 0.10320 0.09728 -0.0569 0.5091 0.0184
-10.500 -0.1683 0.09810 0.09220 -0.0591 0.5086 0.0179
-10.250 -0.1529 0.09755 0.09166 -0.0591 0.5076 0.0197
-10.000 -0.1509 0.09407 0.08822 -0.0605 0.5067 0.0197
-9.750 -0.1550 0.08939 0.08357 -0.0625 0.5061 0.0187
-9.500 -0.1503 0.08674 0.08095 -0.0635 0.5052 0.0194
-9.250 -0.1525 0.08279 0.07705 -0.0652 0.5044 0.0193
-9.000 -0.1556 0.07884 0.07314 -0.0669 0.5037 0.0192
-8.750 -0.1614 0.07463 0.06899 -0.0688 0.5030 0.0191
-8.500 -0.1701 0.07034 0.06475 -0.0710 0.5023 0.0191
-8.250 -0.1891 0.06557 0.06004 -0.0733 0.5019 0.0190
-8.000 -0.2015 0.06079 0.05524 -0.0751 0.5013 0.0191
-7.750 -0.2160 0.05448 0.04881 -0.0767 0.5008 0.0189
-7.500 -0.2216 0.04919 0.04334 -0.0769 0.5002 0.0191
-7.250 -0.2219 0.04441 0.03832 -0.0762 0.4994 0.0196
-7.000 -0.2183 0.04000 0.03359 -0.0749 0.4987 0.0206
-6.750 -0.2183 0.03416 0.02723 -0.0726 0.4980 0.0218
-6.500 -0.2160 0.02824 0.02053 -0.0696 0.4973 0.0229
-6.250 -0.2016 0.02526 0.01705 -0.0678 0.4964 0.0242
-6.000 -0.1781 0.02489 0.01657 -0.0671 0.4953 0.0257
-5.750 -0.1537 0.02463 0.01619 -0.0665 0.4942 0.0273
-5.500 -0.1300 0.02384 0.01518 -0.0658 0.4931 0.0297
-5.250 -0.1070 0.02233 0.01327 -0.0648 0.4922 0.0326
-5.000 -0.0825 0.02160 0.01241 -0.0641 0.4910 0.0352
-4.750 -0.0566 0.02189 0.01271 -0.0638 0.4899 0.0377
-4.500 -0.0309 0.02163 0.01234 -0.0633 0.4888 0.0416
-4.250 -0.0052 0.02098 0.01144 -0.0627 0.4878 0.0463
-4.000 0.0204 0.02115 0.01163 -0.0623 0.4867 0.0491
-3.750 0.0463 0.02104 0.01139 -0.0619 0.4856 0.0534
-3.500 0.0725 0.02089 0.01103 -0.0614 0.4846 0.0574
-3.250 0.0980 0.02053 0.01068 -0.0610 0.4836 0.0607
-3.000 0.1239 0.02035 0.01043 -0.0607 0.4826 0.0644
-2.750 0.1502 0.02018 0.01011 -0.0603 0.4817 0.0684
-2.500 0.1767 0.02006 0.00982 -0.0599 0.4808 0.0707
-2.250 0.2028 0.01955 0.00933 -0.0596 0.4799 0.0724
-2.000 0.2289 0.01926 0.00901 -0.0593 0.4789 0.0741
-1.750 0.2550 0.01903 0.00874 -0.0589 0.4780 0.0758
-1.500 0.2811 0.01888 0.00852 -0.0586 0.4772 0.0781
-1.250 0.3074 0.01882 0.00837 -0.0582 0.4764 0.0806
-1.000 0.3323 0.01862 0.00821 -0.0578 0.4757 0.0825
-0.750 0.3568 0.01851 0.00816 -0.0572 0.4748 0.0839
-0.500 0.3813 0.01845 0.00814 -0.0566 0.4739 0.0858
-0.250 0.4059 0.01845 0.00816 -0.0561 0.4729 0.0880
0.000 0.4307 0.01849 0.00821 -0.0556 0.4719 0.0898
0.250 0.4552 0.01850 0.00826 -0.0550 0.4709 0.0919
0.500 0.4800 0.01857 0.00834 -0.0546 0.4699 0.0946
0.750 0.5051 0.01865 0.00842 -0.0541 0.4688 0.0975
1.000 0.5300 0.01870 0.00850 -0.0537 0.4676 0.1023
1.250 0.5551 0.01877 0.00859 -0.0532 0.4665 0.1097
1.500 0.5796 0.01878 0.00870 -0.0527 0.4656 0.1294
2.000 0.7422 0.01717 0.00929 -0.0759 0.4637 1.0000
2.250 0.7654 0.01741 0.00948 -0.0752 0.4630 1.0000
2.500 0.7888 0.01765 0.00968 -0.0745 0.4623 1.0000
2.750 0.8124 0.01790 0.00988 -0.0738 0.4616 1.0000
3.000 0.8363 0.01814 0.01008 -0.0732 0.4609 1.0000
3.250 0.8604 0.01840 0.01030 -0.0727 0.4602 1.0000
3.500 0.8813 0.01880 0.01076 -0.0717 0.4590 1.0000
3.750 0.9015 0.01928 0.01131 -0.0706 0.4577 1.0000
4.000 0.9218 0.01976 0.01187 -0.0696 0.4565 1.0000
4.250 0.9421 0.02026 0.01243 -0.0686 0.4552 1.0000
4.500 0.9628 0.02072 0.01295 -0.0677 0.4538 1.0000
4.750 0.9840 0.02112 0.01340 -0.0668 0.4523 1.0000
5.000 1.0055 0.02151 0.01383 -0.0660 0.4511 1.0000
5.250 1.0271 0.02192 0.01428 -0.0652 0.4500 1.0000
5.500 1.0491 0.02231 0.01471 -0.0645 0.4490 1.0000
5.750 1.0719 0.02261 0.01504 -0.0639 0.4480 1.0000
6.000 1.0953 0.02288 0.01534 -0.0633 0.4471 1.0000
6.250 1.1191 0.02314 0.01562 -0.0628 0.4463 1.0000
6.500 1.1428 0.02343 0.01594 -0.0624 0.4455 1.0000
6.750 1.1671 0.02370 0.01624 -0.0620 0.4448 1.0000
7.000 1.1759 0.02485 0.01761 -0.0598 0.4421 1.0000
7.250 1.1837 0.02603 0.01897 -0.0575 0.4389 1.0000
7.500 1.1992 0.02667 0.01971 -0.0561 0.4365 1.0000
7.750 1.2187 0.02704 0.02015 -0.0551 0.4347 1.0000
8.000 1.2404 0.02727 0.02046 -0.0544 0.4333 1.0000
8.250 1.2635 0.02743 0.02067 -0.0539 0.4321 1.0000
8.500 1.2878 0.02754 0.02083 -0.0535 0.4311 1.0000
8.750 1.3140 0.02754 0.02088 -0.0533 0.4302 1.0000
9.000 1.3071 0.02939 0.02295 -0.0495 0.4265 1.0000
9.250 1.1590 0.04050 0.03430 -0.0373 0.4105 1.0000
9.500 1.1940 0.03923 0.03309 -0.0367 0.4112 1.0000
9.750 1.2332 0.03770 0.03162 -0.0364 0.4118 1.0000
10.000 1.2829 0.03537 0.02937 -0.0366 0.4120 1.0000
10.250 1.0796 0.05847 0.05244 -0.0356 0.3758 1.0000
10.500 1.1009 0.05861 0.05265 -0.0352 0.3743 1.0000
10.750 1.1277 0.05805 0.05217 -0.0348 0.3732 1.0000
11.000 1.1579 0.05705 0.05126 -0.0344 0.3723 1.0000
12.500 1.1822 0.06827 0.06284 -0.0329 0.3233 1.0000
12.750 1.2022 0.06834 0.06294 -0.0326 0.3123 1.0000
13.000 1.2292 0.06755 0.06214 -0.0323 0.2989 1.0000
13.250 1.2767 0.06404 0.05847 -0.0316 0.2770 1.0000
13.500 1.2934 0.06415 0.05835 -0.0309 0.2490 1.0000
13.750 1.2907 0.06680 0.06086 -0.0306 0.2246 1.0000
14.000 1.2805 0.07045 0.06435 -0.0303 0.1977 1.0000
14.250 1.2665 0.07471 0.06842 -0.0303 0.1714 1.0000
14.500 1.2509 0.07930 0.07281 -0.0304 0.1454 1.0000
14.750 1.2362 0.08391 0.07725 -0.0306 0.1229 1.0000
15.000 1.2273 0.08790 0.08114 -0.0309 0.1060 1.0000
15.250 1.2193 0.09186 0.08501 -0.0312 0.0902 1.0000
15.500 1.2114 0.09585 0.08889 -0.0316 0.0705 1.0000
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