NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 50,000 Max Cl/Cd: 16.97 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a415-il-50000-n5.txt Download as CSV file: xf-naca747a415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4251 0.09120 0.08446 -0.0575 1.0000 0.0637
-10.500 -0.4294 0.08653 0.07984 -0.0600 1.0000 0.0632
-10.250 -0.4406 0.08178 0.07514 -0.0625 1.0000 0.0628
-10.000 -0.4554 0.07794 0.07135 -0.0636 1.0000 0.0623
-9.750 -0.4800 0.07556 0.06906 -0.0619 1.0000 0.0619
-9.500 -0.4956 0.07187 0.06529 -0.0631 0.9815 0.0615
-9.250 -0.4977 0.06686 0.06001 -0.0664 0.9633 0.0611
-9.000 -0.4974 0.06221 0.05502 -0.0685 0.9483 0.0609
-8.750 -0.4936 0.05821 0.05063 -0.0694 0.9344 0.0607
-8.500 -0.4901 0.05467 0.04667 -0.0691 0.9205 0.0612
-8.250 -0.4858 0.05166 0.04317 -0.0679 0.9069 0.0621
-8.000 -0.4798 0.04897 0.03994 -0.0662 0.8944 0.0632
-7.750 -0.4683 0.04642 0.03694 -0.0648 0.8839 0.0643
-7.500 -0.4512 0.04420 0.03446 -0.0640 0.8739 0.0654
-7.250 -0.4342 0.04225 0.03225 -0.0629 0.8638 0.0665
-7.000 -0.4130 0.04039 0.03009 -0.0622 0.8558 0.0681
-6.750 -0.3948 0.03890 0.02831 -0.0610 0.8458 0.0707
-6.500 -0.3708 0.03723 0.02619 -0.0603 0.8388 0.0738
-6.250 -0.3478 0.03576 0.02441 -0.0595 0.8297 0.0759
-6.000 -0.3192 0.03433 0.02292 -0.0597 0.8232 0.0793
-5.750 -0.2928 0.03329 0.02173 -0.0594 0.8154 0.0843
-5.500 -0.2601 0.03214 0.02035 -0.0598 0.8087 0.0895
-5.250 -0.2269 0.03110 0.01929 -0.0603 0.8035 0.0968
-4.750 -0.1736 0.02965 0.01766 -0.0597 0.7897 0.1161
-4.500 -0.1525 0.02898 0.01702 -0.0588 0.7834 0.1299
-4.250 -0.1346 0.02836 0.01649 -0.0573 0.7764 0.1505
-4.000 -0.1177 0.02735 0.01580 -0.0558 0.7714 0.1929
-3.750 -0.1134 0.02618 0.01549 -0.0527 0.7642 0.3136
-3.500 -0.0647 0.02661 0.01768 -0.0505 0.7605 0.7451
-3.250 -0.0528 0.02735 0.01816 -0.0462 0.7553 0.8020
-3.000 0.0669 0.02933 0.01960 -0.0561 0.7544 0.9031
-2.750 0.1198 0.02928 0.01923 -0.0607 0.7499 0.9243
-2.500 0.1579 0.02921 0.01894 -0.0633 0.7445 0.9379
-2.250 0.1938 0.02903 0.01853 -0.0655 0.7400 0.9485
-2.000 0.2313 0.02872 0.01800 -0.0678 0.7364 0.9565
-1.750 0.2629 0.02879 0.01794 -0.0698 0.7305 0.9652
-1.500 0.2962 0.02875 0.01775 -0.0718 0.7255 0.9736
-1.250 0.3328 0.02854 0.01740 -0.0743 0.7217 0.9807
-1.000 0.3675 0.02837 0.01708 -0.0762 0.7186 0.9874
-0.750 0.3982 0.02869 0.01737 -0.0785 0.7132 0.9941
-0.500 0.4304 0.02880 0.01741 -0.0806 0.7089 0.9997
-0.250 0.4498 0.02905 0.01759 -0.0799 0.7051 1.0000
0.000 0.4696 0.02920 0.01767 -0.0789 0.7019 1.0000
0.250 0.4821 0.03004 0.01853 -0.0779 0.6961 1.0000
0.500 0.4970 0.03064 0.01912 -0.0768 0.6916 1.0000
0.750 0.5139 0.03109 0.01955 -0.0757 0.6883 1.0000
1.000 0.5327 0.03139 0.01981 -0.0746 0.6854 1.0000
1.250 0.5391 0.03253 0.02099 -0.0727 0.6797 1.0000
1.500 0.5486 0.03339 0.02188 -0.0709 0.6749 1.0000
1.750 0.5631 0.03396 0.02245 -0.0694 0.6714 1.0000
2.000 0.5811 0.03433 0.02281 -0.0681 0.6687 1.0000
2.250 0.5745 0.03598 0.02452 -0.0646 0.6620 1.0000
2.500 0.5791 0.03696 0.02553 -0.0620 0.6570 1.0000
2.750 0.5938 0.03745 0.02604 -0.0603 0.6537 1.0000
3.250 0.5827 0.04013 0.02878 -0.0526 0.6416 1.0000
3.500 0.5946 0.04067 0.02935 -0.0505 0.6376 1.0000
3.750 0.6149 0.04092 0.02964 -0.0493 0.6350 1.0000
4.000 0.5718 0.04338 0.03210 -0.0413 0.6245 1.0000
4.250 0.5847 0.04385 0.03261 -0.0392 0.6207 1.0000
4.500 0.6071 0.04404 0.03284 -0.0382 0.6179 1.0000
4.750 0.5527 0.04622 0.03497 -0.0284 0.6067 1.0000
5.000 0.5736 0.04650 0.03530 -0.0272 0.6031 1.0000
5.250 0.5485 0.04810 0.03687 -0.0214 0.5941 1.0000
5.500 0.5616 0.04870 0.03751 -0.0196 0.5888 1.0000
5.750 0.5900 0.04886 0.03775 -0.0193 0.5855 1.0000
6.000 0.5725 0.05073 0.03962 -0.0154 0.5748 1.0000
6.250 0.5986 0.05103 0.04001 -0.0150 0.5704 1.0000
6.500 0.5954 0.05263 0.04164 -0.0127 0.5606 1.0000
6.750 0.6195 0.05301 0.04212 -0.0122 0.5550 1.0000
7.000 0.6238 0.05438 0.04356 -0.0107 0.5456 1.0000
7.250 0.6477 0.05473 0.04403 -0.0101 0.5391 1.0000
7.500 0.6533 0.05607 0.04545 -0.0088 0.5288 1.0000
7.750 0.6810 0.05614 0.04568 -0.0084 0.5224 1.0000
8.000 0.6849 0.05760 0.04722 -0.0070 0.5108 1.0000
8.250 0.7184 0.05716 0.04697 -0.0067 0.5052 1.0000
8.500 0.7206 0.05874 0.04864 -0.0053 0.4922 1.0000
9.000 0.7634 0.05903 0.04928 -0.0036 0.4735 1.0000
9.250 0.7695 0.06024 0.05063 -0.0024 0.4596 1.0000
9.500 0.7800 0.06100 0.05153 -0.0012 0.4458 1.0000
9.750 0.7939 0.06130 0.05201 0.0000 0.4314 1.0000
10.000 0.8096 0.06125 0.05214 0.0014 0.4159 1.0000
10.250 0.8277 0.06080 0.05189 0.0028 0.3998 1.0000
10.500 0.8490 0.05983 0.05114 0.0043 0.3833 1.0000
10.750 0.8610 0.05977 0.05124 0.0058 0.3615 1.0000
11.000 0.8809 0.05835 0.04992 0.0078 0.3301 1.0000
11.250 0.9030 0.05678 0.04820 0.0100 0.2832 1.0000
11.500 0.9154 0.05690 0.04798 0.0118 0.2345 1.0000
11.750 0.9146 0.05901 0.04970 0.0129 0.1943 1.0000
12.000 0.9104 0.06189 0.05229 0.0135 0.1637 1.0000
12.250 0.9062 0.06498 0.05513 0.0139 0.1401 1.0000
12.500 0.9038 0.06803 0.05800 0.0142 0.1216 1.0000
12.750 0.9038 0.07093 0.06076 0.0144 0.1077 1.0000
13.000 0.9056 0.07366 0.06336 0.0145 0.0973 1.0000
13.250 0.9111 0.07604 0.06577 0.0148 0.0884 1.0000
13.500 0.9184 0.07824 0.06800 0.0151 0.0814 1.0000
13.750 0.9270 0.08029 0.07006 0.0154 0.0759 1.0000
14.000 0.9382 0.08216 0.07202 0.0159 0.0711 1.0000
14.250 0.9487 0.08419 0.07417 0.0161 0.0666 1.0000
14.500 0.9633 0.08561 0.07554 0.0167 0.0632 1.0000
14.750 0.9737 0.08805 0.07832 0.0168 0.0603 1.0000
15.000 0.9819 0.09066 0.08113 0.0167 0.0575 1.0000
15.250 0.9920 0.09290 0.08342 0.0166 0.0551 1.0000
15.500 1.0004 0.09567 0.08635 0.0164 0.0536 1.0000
15.750 0.9970 0.10025 0.09127 0.0152 0.0526 1.0000
16.000 0.9895 0.10549 0.09683 0.0134 0.0519 1.0000
16.250 0.9779 0.11149 0.10311 0.0109 0.0514 1.0000
16.500 0.9613 0.11858 0.11046 0.0075 0.0511 1.0000
16.750 0.9397 0.12710 0.11920 0.0030 0.0511 1.0000
17.000 0.9116 0.13788 0.13020 -0.0031 0.0516 1.0000
17.250 0.8798 0.15104 0.14350 -0.0107 0.0522 1.0000
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