NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M22 AIRFOIL (m22-il) Reynolds number: 1,000,000 Max Cl/Cd: 115 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m22-il-1000000.txt Download as CSV file: xf-m22-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M22 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4583 0.10591 0.10352 0.0353 0.6390 0.0076
-7.500 -0.4529 0.10286 0.10046 0.0335 0.6338 0.0077
-7.000 -0.4356 0.09661 0.09418 0.0287 0.6238 0.0080
-6.750 -0.4232 0.09333 0.09087 0.0258 0.6185 0.0082
-6.500 -0.4093 0.08996 0.08745 0.0229 0.6137 0.0085
-6.250 -0.3940 0.08651 0.08397 0.0198 0.6086 0.0089
-6.000 -0.3765 0.08284 0.08026 0.0166 0.6036 0.0099
-5.750 -0.3512 0.07894 0.07630 0.0116 0.5991 0.0104
-5.500 -0.3282 0.07498 0.07228 0.0076 0.5943 0.0105
-5.250 -0.3053 0.07113 0.06836 0.0043 0.5894 0.0105
-5.000 -0.2913 0.06649 0.06367 0.0026 0.5851 0.0109
-4.750 -0.2703 0.06379 0.06093 0.0008 0.5800 0.0112
-4.500 -0.2470 0.06116 0.05822 -0.0012 0.5748 0.0118
-4.250 -0.2213 0.05829 0.05526 -0.0035 0.5702 0.0133
-4.000 -0.1853 0.05513 0.05198 -0.0068 0.5657 0.0142
-3.750 -0.1553 0.05162 0.04834 -0.0091 0.5612 0.0143
-3.500 -0.1260 0.04806 0.04465 -0.0108 0.5569 0.0144
-3.250 -0.1058 0.04368 0.04020 -0.0119 0.5528 0.0149
-3.000 -0.0817 0.04186 0.03831 -0.0126 0.5480 0.0154
-2.750 -0.0552 0.04008 0.03642 -0.0135 0.5433 0.0167
-2.500 -0.0169 0.03826 0.03443 -0.0145 0.5393 0.0190
-2.250 0.0128 0.03560 0.03163 -0.0150 0.5350 0.0191
-1.750 0.0672 0.02863 0.02430 -0.0158 0.5275 0.0200
-1.500 0.0925 0.02747 0.02308 -0.0162 0.5231 0.0207
-1.250 0.1197 0.02626 0.02177 -0.0165 0.5187 0.0221
-1.000 0.1520 0.02544 0.02079 -0.0164 0.5146 0.0254
-0.750 0.1818 0.02404 0.01927 -0.0164 0.5109 0.0258
-0.500 0.2110 0.02237 0.01745 -0.0162 0.5067 0.0259
-0.250 0.2402 0.02048 0.01536 -0.0160 0.5028 0.0260
1.000 0.3807 0.01348 0.00757 -0.0162 0.4836 0.0311
1.250 0.4094 0.01285 0.00684 -0.0162 0.4796 0.0333
1.500 0.4384 0.01318 0.00711 -0.0163 0.4755 0.0355
1.750 0.4671 0.01254 0.00632 -0.0163 0.4716 0.0357
2.500 0.5518 0.01057 0.00413 -0.0168 0.4592 0.0471
2.750 0.5804 0.01037 0.00391 -0.0169 0.4556 0.0477
3.250 0.6356 0.00910 0.00255 -0.0166 0.4475 0.0341
3.500 0.6634 0.00892 0.00235 -0.0167 0.4433 0.0333
3.750 0.6914 0.00878 0.00222 -0.0168 0.4392 0.0329
4.000 0.7196 0.00872 0.00213 -0.0170 0.4327 0.0331
4.250 0.7478 0.00867 0.00208 -0.0172 0.4250 0.0342
4.500 0.7761 0.00870 0.00208 -0.0175 0.4169 0.0363
4.750 0.8044 0.00872 0.00208 -0.0177 0.4066 0.0394
5.000 0.8327 0.00881 0.00214 -0.0181 0.3919 0.0435
5.250 0.8606 0.00888 0.00231 -0.0185 0.3719 0.1380
5.500 0.8993 0.00782 0.00275 -0.0217 0.3248 0.9952
5.750 0.9578 0.01166 0.00507 -0.0323 0.0186 1.0000
6.000 0.9830 0.01202 0.00550 -0.0321 0.0149 1.0000
6.250 1.0080 0.01238 0.00590 -0.0320 0.0141 1.0000
6.500 1.0328 0.01277 0.00634 -0.0318 0.0133 1.0000
6.750 1.0572 0.01325 0.00687 -0.0316 0.0121 1.0000
7.000 1.0811 0.01379 0.00745 -0.0314 0.0109 1.0000
7.250 1.1040 0.01457 0.00830 -0.0312 0.0101 1.0000
7.500 1.1238 0.01600 0.00989 -0.0310 0.0094 1.0000
7.750 1.1421 0.01728 0.01127 -0.0306 0.0090 1.0000
8.000 1.1631 0.01788 0.01192 -0.0300 0.0086 1.0000
8.250 1.1810 0.01885 0.01296 -0.0293 0.0082 1.0000
8.500 1.1950 0.02014 0.01433 -0.0283 0.0079 1.0000
8.750 1.2070 0.02147 0.01574 -0.0271 0.0076 1.0000
9.000 1.2188 0.02270 0.01702 -0.0261 0.0072 1.0000
9.250 1.2286 0.02425 0.01863 -0.0257 0.0069 1.0000
9.500 1.2294 0.02612 0.02055 -0.0241 0.0068 1.0000
9.750 1.2343 0.02793 0.02243 -0.0228 0.0067 1.0000
10.000 1.2411 0.02965 0.02419 -0.0216 0.0066 1.0000
10.250 1.2496 0.03125 0.02584 -0.0204 0.0065 1.0000
10.500 1.2588 0.03279 0.02742 -0.0192 0.0063 1.0000
10.750 1.2685 0.03431 0.02897 -0.0179 0.0061 1.0000
11.000 1.2816 0.03571 0.03038 -0.0153 0.0059 1.0000
11.500 1.3104 0.03993 0.03491 -0.0108 0.0053 1.0000
17.000 0.8574 0.14013 0.13848 -0.0212 0.0071 1.0000
17.250 0.8326 0.14836 0.14680 -0.0258 0.0074 1.0000
17.500 0.8079 0.15742 0.15593 -0.0306 0.0077 1.0000
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Polar data table (+)
Polar graphs
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