NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 500,000 Max Cl/Cd: 75.21 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a410-il-500000-n5.txt Download as CSV file: xf-naca64a410-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4712 0.08381 0.08156 -0.0424 1.0000 0.0072
-9.500 -0.4812 0.07757 0.07536 -0.0459 1.0000 0.0072
-9.000 -0.5624 0.03048 0.02708 -0.0858 0.9654 0.0073
-8.750 -0.5495 0.02629 0.02241 -0.0866 0.9585 0.0076
-8.500 -0.5243 0.02579 0.02185 -0.0871 0.9542 0.0079
-8.250 -0.4989 0.02508 0.02101 -0.0876 0.9506 0.0082
-8.000 -0.4785 0.02327 0.01893 -0.0874 0.9448 0.0087
-7.750 -0.4583 0.02073 0.01596 -0.0871 0.9394 0.0093
-7.500 -0.4362 0.01864 0.01348 -0.0868 0.9348 0.0099
-7.250 -0.4129 0.01734 0.01190 -0.0864 0.9292 0.0103
-7.000 -0.3895 0.01595 0.01028 -0.0860 0.9244 0.0108
-6.750 -0.3643 0.01526 0.00949 -0.0858 0.9202 0.0113
-6.500 -0.3387 0.01479 0.00894 -0.0857 0.9153 0.0119
-6.250 -0.3128 0.01434 0.00840 -0.0855 0.9108 0.0128
-6.000 -0.2867 0.01377 0.00770 -0.0853 0.9069 0.0136
-5.750 -0.2611 0.01317 0.00699 -0.0851 0.9018 0.0142
-5.500 -0.2358 0.01245 0.00615 -0.0848 0.8970 0.0148
-5.250 -0.2102 0.01182 0.00545 -0.0845 0.8928 0.0158
-5.000 -0.1837 0.01150 0.00511 -0.0844 0.8876 0.0169
-4.750 -0.1571 0.01118 0.00473 -0.0843 0.8825 0.0181
-4.500 -0.1307 0.01080 0.00426 -0.0841 0.8769 0.0190
-4.250 -0.1044 0.01046 0.00386 -0.0838 0.8690 0.0198
-4.000 -0.0781 0.01006 0.00337 -0.0836 0.8616 0.0211
-3.750 -0.0515 0.00978 0.00308 -0.0834 0.8537 0.0235
-3.500 -0.0242 0.00958 0.00281 -0.0833 0.8478 0.0261
-3.250 0.0029 0.00935 0.00255 -0.0833 0.8406 0.0293
-3.000 0.0301 0.00915 0.00233 -0.0832 0.8338 0.0349
-2.750 0.0574 0.00898 0.00214 -0.0831 0.8258 0.0411
-2.500 0.0847 0.00882 0.00194 -0.0830 0.8177 0.0487
-2.250 0.1117 0.00858 0.00176 -0.0830 0.8084 0.0684
-2.000 0.1391 0.00846 0.00169 -0.0830 0.7990 0.1075
-1.750 0.1661 0.00834 0.00155 -0.0828 0.7867 0.1207
-1.500 0.1931 0.00827 0.00142 -0.0827 0.7724 0.1289
-1.250 0.2200 0.00818 0.00132 -0.0826 0.7597 0.1443
-1.000 0.2449 0.00754 0.00119 -0.0825 0.7469 0.3248
-0.750 0.2699 0.00711 0.00115 -0.0822 0.7338 0.4725
-0.500 0.2960 0.00696 0.00117 -0.0820 0.7210 0.5463
-0.250 0.3225 0.00690 0.00120 -0.0817 0.7094 0.5912
0.000 0.3493 0.00689 0.00123 -0.0815 0.6980 0.6219
0.250 0.3760 0.00689 0.00127 -0.0813 0.6864 0.6490
0.750 0.4301 0.00697 0.00134 -0.0810 0.6622 0.6784
1.000 0.4570 0.00702 0.00139 -0.0809 0.6480 0.6920
1.500 0.5099 0.00719 0.00151 -0.0803 0.6161 0.7203
1.750 0.5356 0.00732 0.00159 -0.0800 0.5914 0.7339
2.000 0.5603 0.00753 0.00170 -0.0794 0.5566 0.7487
2.250 0.5844 0.00777 0.00183 -0.0787 0.5154 0.7664
2.500 0.6067 0.00819 0.00200 -0.0778 0.4495 0.7811
2.750 0.6255 0.00900 0.00235 -0.0765 0.3338 0.7960
3.000 0.6432 0.00996 0.00281 -0.0750 0.2076 0.8142
3.250 0.6634 0.01050 0.00315 -0.0738 0.1347 0.8440
3.500 0.6963 0.01055 0.00337 -0.0749 0.1227 0.9884
3.750 0.7223 0.01080 0.00360 -0.0748 0.1157 1.0000
4.000 0.7477 0.01105 0.00383 -0.0745 0.1082 1.0000
4.250 0.7726 0.01136 0.00409 -0.0741 0.0967 1.0000
4.500 0.7979 0.01161 0.00428 -0.0738 0.0688 1.0000
4.750 0.8210 0.01209 0.00462 -0.0732 0.0481 1.0000
5.000 0.8450 0.01247 0.00499 -0.0727 0.0401 1.0000
5.250 0.8697 0.01277 0.00532 -0.0722 0.0349 1.0000
5.500 0.8935 0.01316 0.00569 -0.0717 0.0285 1.0000
5.750 0.9171 0.01355 0.00607 -0.0711 0.0230 1.0000
6.000 0.9406 0.01395 0.00649 -0.0705 0.0196 1.0000
6.250 0.9637 0.01437 0.00692 -0.0699 0.0175 1.0000
6.500 0.9860 0.01488 0.00744 -0.0691 0.0160 1.0000
6.750 1.0074 0.01546 0.00809 -0.0681 0.0150 1.0000
7.000 1.0293 0.01597 0.00866 -0.0672 0.0145 1.0000
7.250 1.0504 0.01654 0.00929 -0.0663 0.0140 1.0000
7.500 1.0709 0.01714 0.00996 -0.0652 0.0135 1.0000
7.750 1.0908 0.01779 0.01067 -0.0641 0.0131 1.0000
8.000 1.1100 0.01848 0.01142 -0.0629 0.0126 1.0000
8.250 1.1291 0.01915 0.01216 -0.0617 0.0122 1.0000
8.500 1.1476 0.01985 0.01291 -0.0604 0.0117 1.0000
8.750 1.1633 0.02074 0.01386 -0.0587 0.0112 1.0000
9.000 1.1755 0.02194 0.01515 -0.0565 0.0108 1.0000
9.250 1.1891 0.02308 0.01639 -0.0545 0.0106 1.0000
9.500 1.2046 0.02401 0.01742 -0.0529 0.0104 1.0000
9.750 1.2197 0.02498 0.01852 -0.0512 0.0102 1.0000
10.000 1.2347 0.02595 0.01960 -0.0496 0.0099 1.0000
10.250 1.2490 0.02695 0.02072 -0.0480 0.0096 1.0000
10.500 1.2627 0.02798 0.02187 -0.0464 0.0092 1.0000
10.750 1.2752 0.02914 0.02315 -0.0447 0.0089 1.0000
11.000 1.2867 0.03036 0.02449 -0.0429 0.0087 1.0000
11.250 1.2973 0.03162 0.02587 -0.0412 0.0084 1.0000
11.500 1.3070 0.03293 0.02729 -0.0394 0.0082 1.0000
11.750 1.3153 0.03433 0.02881 -0.0377 0.0080 1.0000
12.000 1.3222 0.03588 0.03049 -0.0360 0.0078 1.0000
12.250 1.3260 0.03780 0.03255 -0.0341 0.0076 1.0000
12.500 1.3211 0.04090 0.03587 -0.0318 0.0073 1.0000
12.750 1.3245 0.04284 0.03800 -0.0303 0.0072 1.0000
13.000 1.3263 0.04503 0.04038 -0.0289 0.0071 1.0000
13.250 1.3255 0.04756 0.04312 -0.0276 0.0069 1.0000
13.500 1.3213 0.05061 0.04637 -0.0265 0.0067 1.0000
13.750 1.3153 0.05395 0.04993 -0.0258 0.0066 1.0000
14.000 1.3064 0.05780 0.05399 -0.0254 0.0064 1.0000
14.250 1.2942 0.06229 0.05869 -0.0255 0.0063 1.0000
14.500 1.2796 0.06733 0.06395 -0.0263 0.0062 1.0000
14.750 1.2628 0.07309 0.06991 -0.0278 0.0062 1.0000
15.000 1.2435 0.07973 0.07675 -0.0302 0.0061 1.0000
15.250 1.2212 0.08746 0.08469 -0.0336 0.0061 1.0000
15.500 1.1946 0.09686 0.09430 -0.0385 0.0062 1.0000
15.750 1.1631 0.10840 0.10605 -0.0452 0.0062 1.0000
16.000 1.1197 0.12496 0.12282 -0.0553 0.0064 1.0000
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