NACA 1410 (naca1410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 50,000 Max Cl/Cd: 31.19 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1410-il-50000.txt Download as CSV file: xf-naca1410-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1410
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5190 0.09606 0.08875 0.0124 1.0000 0.3712
-8.000 -0.5138 0.09287 0.08559 0.0130 1.0000 0.3877
-7.750 -0.6636 0.06363 0.05616 -0.0284 1.0000 0.1667
-7.500 -0.6549 0.05879 0.05114 -0.0284 1.0000 0.1638
-7.250 -0.6487 0.05377 0.04587 -0.0285 1.0000 0.1604
-7.000 -0.6436 0.04872 0.04037 -0.0283 1.0000 0.1576
-6.750 -0.6330 0.04499 0.03623 -0.0274 1.0000 0.1602
-6.500 -0.6208 0.04144 0.03215 -0.0264 1.0000 0.1632
-6.250 -0.6054 0.03812 0.02822 -0.0252 1.0000 0.1650
-6.000 -0.5863 0.03523 0.02503 -0.0241 1.0000 0.1682
-5.750 -0.5653 0.03316 0.02282 -0.0230 1.0000 0.1753
-5.500 -0.5446 0.03113 0.02049 -0.0219 1.0000 0.1851
-5.250 -0.5221 0.02923 0.01822 -0.0208 1.0000 0.1956
-5.000 -0.4987 0.02742 0.01639 -0.0197 1.0000 0.2090
-4.750 -0.4761 0.02588 0.01491 -0.0186 1.0000 0.2303
-4.500 -0.4539 0.02443 0.01356 -0.0173 1.0000 0.2622
-4.250 -0.4321 0.02285 0.01222 -0.0160 1.0000 0.3107
-4.000 -0.4116 0.02133 0.01122 -0.0143 1.0000 0.3819
-3.750 -0.3947 0.02040 0.01086 -0.0115 1.0000 0.4712
-3.500 -0.3790 0.01945 0.01046 -0.0079 1.0000 0.5738
-3.250 -0.3655 0.01883 0.01038 -0.0029 1.0000 0.6774
-3.000 -0.3522 0.01862 0.01049 0.0030 1.0000 0.7764
-2.750 -0.3183 0.01900 0.01088 0.0063 1.0000 0.8739
-2.500 -0.1443 0.01990 0.01078 -0.0174 1.0000 0.9741
-2.250 -0.0704 0.01907 0.00959 -0.0285 1.0000 1.0000
-2.000 -0.0733 0.01848 0.00897 -0.0255 1.0000 1.0000
-1.750 -0.0774 0.01804 0.00848 -0.0219 1.0000 1.0000
-1.500 -0.0796 0.01776 0.00813 -0.0181 1.0000 1.0000
-1.250 -0.0780 0.01762 0.00789 -0.0147 1.0000 1.0000
-1.000 -0.0726 0.01759 0.00775 -0.0118 1.0000 1.0000
-0.750 -0.0637 0.01765 0.00769 -0.0094 1.0000 1.0000
-0.500 -0.0521 0.01779 0.00771 -0.0075 1.0000 1.0000
-0.250 -0.0384 0.01799 0.00781 -0.0059 1.0000 1.0000
0.000 -0.0235 0.01825 0.00799 -0.0047 1.0000 1.0000
0.250 -0.0078 0.01858 0.00824 -0.0037 1.0000 1.0000
0.500 0.0083 0.01897 0.00858 -0.0029 1.0000 1.0000
0.750 0.0247 0.01944 0.00900 -0.0023 1.0000 1.0000
1.000 0.0411 0.01998 0.00951 -0.0019 1.0000 1.0000
1.250 0.0575 0.02061 0.01011 -0.0017 1.0000 1.0000
1.500 0.0737 0.02131 0.01081 -0.0016 1.0000 1.0000
1.750 0.0959 0.02215 0.01166 -0.0029 0.9974 1.0000
2.000 0.1652 0.02338 0.01298 -0.0125 0.9751 1.0000
2.250 0.2277 0.02431 0.01403 -0.0204 0.9505 1.0000
2.500 0.2862 0.02502 0.01490 -0.0270 0.9248 1.0000
2.750 0.3508 0.02545 0.01553 -0.0340 0.8998 1.0000
3.000 0.4088 0.02562 0.01594 -0.0391 0.8729 1.0000
3.250 0.4605 0.02555 0.01611 -0.0424 0.8451 1.0000
3.500 0.5079 0.02526 0.01604 -0.0442 0.8164 1.0000
3.750 0.5495 0.02482 0.01580 -0.0442 0.7864 1.0000
4.000 0.5851 0.02434 0.01549 -0.0429 0.7547 1.0000
4.250 0.6168 0.02380 0.01506 -0.0406 0.7209 1.0000
4.500 0.6424 0.02346 0.01478 -0.0374 0.6826 1.0000
4.750 0.6673 0.02306 0.01435 -0.0339 0.6411 1.0000
5.000 0.6883 0.02298 0.01420 -0.0303 0.5934 1.0000
5.250 0.7075 0.02303 0.01410 -0.0266 0.5382 1.0000
5.500 0.7243 0.02322 0.01397 -0.0227 0.4725 1.0000
5.750 0.7375 0.02385 0.01417 -0.0189 0.3939 1.0000
6.000 0.7505 0.02512 0.01489 -0.0156 0.3142 1.0000
6.250 0.7679 0.02693 0.01620 -0.0134 0.2552 1.0000
6.500 0.7889 0.02874 0.01772 -0.0120 0.2181 1.0000
6.750 0.8132 0.03077 0.01975 -0.0110 0.1956 1.0000
7.000 0.8385 0.03299 0.02203 -0.0102 0.1817 1.0000
7.250 0.8626 0.03522 0.02428 -0.0095 0.1705 1.0000
7.500 0.8838 0.03736 0.02669 -0.0084 0.1604 1.0000
7.750 0.9044 0.04029 0.02995 -0.0074 0.1551 1.0000
8.000 0.9199 0.04354 0.03377 -0.0059 0.1517 1.0000
8.250 0.9349 0.04661 0.03720 -0.0045 0.1471 1.0000
8.500 0.9514 0.04983 0.04050 -0.0036 0.1419 1.0000
8.750 0.9555 0.05398 0.04523 -0.0018 0.1407 1.0000
9.000 0.9562 0.05864 0.05037 -0.0003 0.1408 1.0000
9.250 0.9525 0.06359 0.05571 0.0010 0.1412 1.0000
9.500 0.9447 0.06874 0.06118 0.0019 0.1417 1.0000
9.750 0.9350 0.07407 0.06672 0.0024 0.1422 1.0000
10.000 0.9255 0.07954 0.07237 0.0025 0.1430 1.0000
10.250 0.8529 0.09051 0.08353 -0.0025 0.1580 1.0000
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Polar data table (+)
Polar graphs
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