NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 100,000 Max Cl/Cd: 49.08 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a210-il-100000.txt Download as CSV file: xf-naca64a210-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5446 0.12864 0.12345 -0.0069 1.0000 0.0863
-11.000 -0.5536 0.12520 0.12008 -0.0118 1.0000 0.0894
-10.750 -0.5705 0.12171 0.11671 -0.0187 1.0000 0.0903
-10.500 -0.5446 0.11636 0.11128 -0.0132 1.0000 0.0935
-10.250 -0.5366 0.11292 0.10784 -0.0131 1.0000 0.0973
-10.000 -0.5400 0.10904 0.10401 -0.0162 1.0000 0.1018
-9.750 -0.5644 0.10456 0.09966 -0.0253 1.0000 0.1040
-9.500 -0.5429 0.10031 0.09538 -0.0204 1.0000 0.1075
-9.250 -0.5366 0.09710 0.09219 -0.0206 1.0000 0.1139
-9.000 -0.5566 0.09197 0.08717 -0.0284 1.0000 0.1173
-8.750 -0.4327 0.07992 0.07533 -0.0289 1.0000 0.1411
-8.500 -0.4667 0.07465 0.07020 -0.0347 1.0000 0.1457
-8.250 -0.4483 0.07105 0.06658 -0.0314 1.0000 0.1518
-8.000 -0.5590 0.07564 0.07102 -0.0334 1.0000 0.1395
-7.750 -0.5874 0.07115 0.06635 -0.0393 1.0000 0.1459
-7.500 -0.5676 0.06775 0.06311 -0.0361 1.0000 0.1545
-7.250 -0.5779 0.06383 0.05912 -0.0370 1.0000 0.1641
-7.000 -0.5861 0.06093 0.05609 -0.0365 1.0000 0.1767
-6.750 -0.5858 0.05831 0.05341 -0.0348 1.0000 0.1906
-6.500 -0.5802 0.05551 0.05064 -0.0326 1.0000 0.2054
-6.250 -0.5724 0.05290 0.04810 -0.0300 1.0000 0.2213
-5.750 -0.5431 0.03626 0.02861 -0.0295 1.0000 0.0757
-5.500 -0.5268 0.03283 0.02496 -0.0281 1.0000 0.0732
-5.250 -0.5086 0.03051 0.02222 -0.0265 1.0000 0.0735
-5.000 -0.4883 0.02819 0.01953 -0.0251 1.0000 0.0728
-4.750 -0.4661 0.02607 0.01706 -0.0238 1.0000 0.0719
-4.500 -0.4429 0.02432 0.01502 -0.0227 1.0000 0.0725
-4.250 -0.4194 0.02299 0.01345 -0.0217 1.0000 0.0750
-4.000 -0.3960 0.02147 0.01187 -0.0210 1.0000 0.0802
-3.750 -0.3724 0.02033 0.01074 -0.0203 1.0000 0.0853
-3.500 -0.3487 0.01924 0.00963 -0.0195 1.0000 0.0921
-3.250 -0.3264 0.01825 0.00878 -0.0189 1.0000 0.1074
-3.000 -0.3030 0.01714 0.00786 -0.0185 1.0000 0.1383
-2.750 -0.2876 0.01424 0.00773 -0.0158 1.0000 0.6884
-2.500 -0.2747 0.01441 0.00802 -0.0118 1.0000 0.7677
-2.250 -0.2623 0.01452 0.00817 -0.0078 1.0000 0.8177
-2.000 -0.2522 0.01461 0.00831 -0.0033 1.0000 0.8663
-1.750 -0.2386 0.01483 0.00860 0.0014 1.0000 0.9340
-1.250 -0.1254 0.01540 0.00873 -0.0114 1.0000 1.0000
-1.000 -0.0848 0.01547 0.00864 -0.0162 0.9910 1.0000
-0.750 -0.0417 0.01565 0.00864 -0.0211 0.9824 1.0000
-0.500 -0.0019 0.01582 0.00867 -0.0251 0.9728 1.0000
-0.250 0.0375 0.01604 0.00877 -0.0288 0.9637 1.0000
0.000 0.0826 0.01631 0.00893 -0.0332 0.9565 1.0000
0.250 0.1173 0.01654 0.00910 -0.0356 0.9464 1.0000
0.500 0.1598 0.01680 0.00931 -0.0393 0.9392 1.0000
0.750 0.1960 0.01704 0.00952 -0.0417 0.9299 1.0000
1.000 0.2311 0.01731 0.00977 -0.0438 0.9209 1.0000
1.250 0.2743 0.01751 0.01000 -0.0474 0.9139 1.0000
1.500 0.3046 0.01780 0.01030 -0.0484 0.9038 1.0000
1.750 0.3518 0.01792 0.01049 -0.0525 0.8983 1.0000
2.000 0.3781 0.01823 0.01086 -0.0526 0.8872 1.0000
2.250 0.4096 0.01847 0.01118 -0.0536 0.8777 1.0000
2.500 0.4498 0.01851 0.01132 -0.0559 0.8703 1.0000
2.750 0.4768 0.01872 0.01163 -0.0558 0.8586 1.0000
3.000 0.5072 0.01881 0.01186 -0.0560 0.8472 1.0000
3.250 0.5408 0.01865 0.01184 -0.0563 0.8355 1.0000
3.500 0.5762 0.01777 0.01111 -0.0554 0.8162 1.0000
3.750 0.6085 0.01628 0.00972 -0.0524 0.7871 1.0000
4.000 0.6350 0.01531 0.00881 -0.0493 0.7569 1.0000
4.250 0.6580 0.01471 0.00826 -0.0464 0.7219 1.0000
4.500 0.6787 0.01429 0.00785 -0.0431 0.6733 1.0000
4.750 0.6935 0.01413 0.00743 -0.0386 0.5645 1.0000
5.000 0.6796 0.01751 0.00821 -0.0312 0.1621 1.0000
5.250 0.6903 0.01950 0.00972 -0.0284 0.1104 1.0000
5.500 0.7070 0.02091 0.01102 -0.0265 0.0923 1.0000
5.750 0.7267 0.02253 0.01253 -0.0249 0.0832 1.0000
6.000 0.7498 0.02432 0.01414 -0.0242 0.0745 1.0000
6.250 0.7767 0.02590 0.01589 -0.0236 0.0698 1.0000
6.500 0.8048 0.02783 0.01796 -0.0231 0.0669 1.0000
6.750 0.8325 0.03006 0.02036 -0.0226 0.0653 1.0000
7.000 0.8574 0.03254 0.02296 -0.0222 0.0626 1.0000
7.250 0.8794 0.03604 0.02674 -0.0214 0.0607 1.0000
7.500 0.9008 0.03984 0.03090 -0.0204 0.0611 1.0000
7.750 0.9191 0.04139 0.03325 -0.0176 0.0641 1.0000
8.000 0.9311 0.04647 0.03903 -0.0151 0.0706 1.0000
10.250 0.8873 0.09965 0.09503 -0.0080 0.1418 1.0000
10.500 0.6299 0.10643 0.10187 -0.0161 0.1639 1.0000
10.750 0.6393 0.10974 0.10520 -0.0151 0.1582 1.0000
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Polar data table (+)
Polar graphs
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