NACA 4424 (naca4424-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 4424 (naca4424-il) Reynolds number: 50,000 Max Cl/Cd: 8.79 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4424-il-50000-n5.txt Download as CSV file: xf-naca4424-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4424
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3297 0.13073 0.12215 -0.0526 0.9839 0.1568
-12.250 -0.3237 0.12619 0.11756 -0.0565 0.9796 0.1604
-12.000 -0.3529 0.11705 0.10838 -0.0616 0.9741 0.1651
-11.750 -0.3251 0.11617 0.10748 -0.0632 0.9686 0.1675
-11.500 -0.3121 0.11310 0.10438 -0.0658 0.9635 0.1710
-11.250 -0.3758 0.09968 0.09088 -0.0722 0.9568 0.1782
-11.000 -0.3379 0.10011 0.09131 -0.0735 0.9519 0.1804
-10.750 -0.5981 0.06709 0.05764 -0.0846 0.9380 0.1912
-10.500 -0.5130 0.07074 0.06151 -0.0863 0.9354 0.1948
-10.250 -0.5525 0.06604 0.05668 -0.0849 0.9237 0.1977
-10.000 -0.6018 0.06144 0.05183 -0.0817 0.9130 0.2005
-9.750 -0.6451 0.05831 0.04841 -0.0759 0.9019 0.2032
-9.500 -0.6871 0.05577 0.04553 -0.0686 0.8894 0.2059
-9.250 -0.6596 0.05527 0.04511 -0.0690 0.8828 0.2097
-9.000 -0.6336 0.05434 0.04415 -0.0696 0.8780 0.2143
-8.750 -0.6533 0.05319 0.04286 -0.0634 0.8651 0.2173
-8.500 -0.6559 0.05098 0.04025 -0.0607 0.8582 0.2227
-8.250 -0.6462 0.05087 0.04027 -0.0579 0.8481 0.2257
-8.000 -0.6273 0.05025 0.03965 -0.0568 0.8408 0.2303
-7.750 -0.6105 0.04884 0.03799 -0.0560 0.8357 0.2367
-7.500 -0.6235 0.04812 0.03711 -0.0501 0.8231 0.2403
-7.250 -0.5928 0.04774 0.03683 -0.0506 0.8175 0.2453
-7.000 -0.5781 0.04708 0.03609 -0.0488 0.8105 0.2509
-6.750 -0.5808 0.04633 0.03511 -0.0445 0.8000 0.2563
-6.500 -0.5504 0.04573 0.03457 -0.0449 0.7949 0.2622
-6.250 -0.5442 0.04554 0.03436 -0.0416 0.7855 0.2670
-6.000 -0.5328 0.04491 0.03355 -0.0392 0.7775 0.2738
-5.750 -0.5035 0.04421 0.03283 -0.0394 0.7729 0.2808
-5.500 -0.5014 0.04426 0.03289 -0.0355 0.7624 0.2855
-5.250 -0.4843 0.04374 0.03224 -0.0339 0.7555 0.2933
-5.000 -0.4544 0.04307 0.03153 -0.0341 0.7512 0.3013
-4.750 -0.4546 0.04330 0.03178 -0.0299 0.7403 0.3063
-4.500 -0.4352 0.04286 0.03122 -0.0285 0.7337 0.3148
-4.250 -0.4041 0.04224 0.03059 -0.0288 0.7297 0.3235
-4.000 -0.4049 0.04262 0.03098 -0.0246 0.7189 0.3290
-3.750 -0.3862 0.04230 0.03054 -0.0231 0.7123 0.3384
-3.500 -0.3549 0.04179 0.03007 -0.0234 0.7083 0.3478
-3.250 -0.3525 0.04216 0.03045 -0.0197 0.6984 0.3548
-3.000 -0.3380 0.04206 0.03019 -0.0178 0.6912 0.3647
-2.750 -0.3063 0.04165 0.02991 -0.0180 0.6871 0.3747
-2.500 -0.2733 0.04105 0.02918 -0.0183 0.6841 0.3881
-2.250 -0.2858 0.04212 0.03033 -0.0131 0.6707 0.3933
-2.000 -0.2581 0.04185 0.03008 -0.0128 0.6661 0.4056
-1.750 -0.2237 0.04133 0.02956 -0.0134 0.6630 0.4195
-1.500 -0.2329 0.04246 0.03075 -0.0088 0.6509 0.4270
-1.250 -0.2082 0.04235 0.03061 -0.0082 0.6456 0.4413
-1.000 -0.1748 0.04197 0.03028 -0.0087 0.6421 0.4574
-0.750 -0.1742 0.04291 0.03127 -0.0055 0.6323 0.4682
-0.500 -0.1571 0.04319 0.03159 -0.0042 0.6255 0.4839
-0.250 -0.1267 0.04295 0.03144 -0.0042 0.6215 0.5028
0.000 -0.0915 0.04249 0.03106 -0.0047 0.6188 0.5249
0.500 -0.0823 0.04429 0.03299 0.0006 0.6012 0.5614
0.750 -0.0502 0.04392 0.03272 0.0007 0.5981 0.5894
1.250 -0.0379 0.04593 0.03501 0.0052 0.5813 0.6381
1.500 -0.0050 0.04571 0.03493 0.0050 0.5777 0.6758
1.750 0.0402 0.04529 0.03471 0.0032 0.5752 0.7194
2.250 0.0937 0.04818 0.03802 -0.0004 0.5580 0.8033
2.500 0.1783 0.04835 0.03830 -0.0095 0.5553 0.8512
2.750 0.2615 0.04821 0.03814 -0.0179 0.5534 0.8872
3.250 0.3236 0.05241 0.04237 -0.0244 0.5352 0.9416
3.500 0.3835 0.05219 0.04204 -0.0291 0.5329 0.9714
3.750 0.4556 0.05181 0.04154 -0.0358 0.5313 0.9951
4.250 0.4253 0.05614 0.04574 -0.0290 0.5119 1.0000
4.500 0.4514 0.05543 0.04488 -0.0280 0.5098 1.0000
5.000 0.4231 0.06020 0.04954 -0.0212 0.4907 1.0000
5.500 0.4061 0.06481 0.05404 -0.0161 0.4729 1.0000
5.750 0.4312 0.06463 0.05377 -0.0152 0.4699 1.0000
6.250 0.4191 0.06939 0.05845 -0.0110 0.4525 1.0000
6.500 0.4450 0.06923 0.05822 -0.0102 0.4495 1.0000
7.000 0.4343 0.07435 0.06328 -0.0068 0.4326 1.0000
7.250 0.4609 0.07418 0.06305 -0.0060 0.4296 1.0000
7.750 0.4525 0.07943 0.06827 -0.0033 0.4129 1.0000
8.000 0.4786 0.07935 0.06813 -0.0026 0.4100 1.0000
8.500 0.4717 0.08478 0.07355 -0.0004 0.3936 1.0000
8.750 0.4976 0.08475 0.07347 0.0002 0.3908 1.0000
9.000 0.4723 0.08976 0.07853 0.0013 0.3789 1.0000
9.250 0.4906 0.09048 0.07922 0.0019 0.3746 1.0000
9.500 0.5166 0.09044 0.07913 0.0025 0.3720 1.0000
9.750 0.4904 0.09580 0.08455 0.0032 0.3601 1.0000
10.000 0.5094 0.09648 0.08520 0.0037 0.3561 1.0000
10.250 0.5365 0.09626 0.08495 0.0044 0.3535 1.0000
10.500 0.5083 0.10212 0.09086 0.0046 0.3416 1.0000
10.750 0.5281 0.10271 0.09143 0.0051 0.3379 1.0000
11.000 0.5495 0.10314 0.09183 0.0057 0.3347 1.0000
11.250 0.5254 0.10879 0.09755 0.0055 0.3237 1.0000
11.500 0.5460 0.10925 0.09799 0.0060 0.3201 1.0000
12.000 0.5420 0.11571 0.10450 0.0059 0.3062 1.0000
12.250 0.5625 0.11620 0.10497 0.0064 0.3028 1.0000
12.750 0.5583 0.12284 0.11167 0.0059 0.2892 1.0000
13.000 0.5790 0.12329 0.11211 0.0063 0.2860 1.0000
13.500 0.5736 0.13028 0.11916 0.0054 0.2728 1.0000
13.750 0.5946 0.13064 0.11951 0.0058 0.2697 1.0000
14.250 0.5893 0.13778 0.12671 0.0045 0.2569 1.0000
14.500 0.6097 0.13821 0.12713 0.0049 0.2539 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 4424 (naca4424-il)