NACA M2 (nacam2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 200,000 Max Cl/Cd: 36.07 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam2-il-200000-n5.txt Download as CSV file: xf-nacam2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7540 0.09741 0.09393 0.0096 1.0000 0.0157
-10.500 -0.7733 0.08735 0.08393 0.0034 1.0000 0.0155
-10.250 -0.9120 0.05151 0.04741 -0.0180 1.0000 0.0135
-10.000 -0.9213 0.04745 0.04308 -0.0170 1.0000 0.0137
-9.750 -0.9162 0.04519 0.04065 -0.0161 1.0000 0.0141
-9.500 -0.9085 0.04293 0.03818 -0.0152 1.0000 0.0145
-9.250 -0.9018 0.03992 0.03485 -0.0141 1.0000 0.0150
-9.000 -0.8930 0.03676 0.03131 -0.0128 1.0000 0.0156
-8.750 -0.8817 0.03364 0.02775 -0.0114 1.0000 0.0165
-8.500 -0.8672 0.03080 0.02445 -0.0101 1.0000 0.0177
-8.250 -0.8487 0.02872 0.02191 -0.0090 1.0000 0.0193
-8.000 -0.8303 0.02664 0.01956 -0.0081 1.0000 0.0205
-7.750 -0.8088 0.02552 0.01833 -0.0075 1.0000 0.0217
-7.500 -0.7865 0.02440 0.01702 -0.0069 1.0000 0.0233
-7.250 -0.7634 0.02341 0.01581 -0.0062 1.0000 0.0258
-7.000 -0.7396 0.02246 0.01460 -0.0056 1.0000 0.0278
-6.750 -0.7169 0.02095 0.01290 -0.0049 1.0000 0.0295
-6.500 -0.6939 0.01993 0.01185 -0.0044 1.0000 0.0320
-6.250 -0.6698 0.01914 0.01098 -0.0038 1.0000 0.0343
-6.000 -0.6456 0.01834 0.01004 -0.0032 1.0000 0.0365
-5.750 -0.6210 0.01773 0.00930 -0.0027 1.0000 0.0385
-5.500 -0.5974 0.01685 0.00835 -0.0020 1.0000 0.0398
-5.250 -0.5746 0.01593 0.00742 -0.0012 1.0000 0.0421
-5.000 -0.5507 0.01534 0.00679 -0.0006 1.0000 0.0446
-4.750 -0.5267 0.01479 0.00618 0.0000 1.0000 0.0465
-4.500 -0.5026 0.01429 0.00562 0.0007 1.0000 0.0483
-4.250 -0.4783 0.01386 0.00512 0.0014 1.0000 0.0501
-4.000 -0.4542 0.01342 0.00463 0.0021 1.0000 0.0528
-3.750 -0.4301 0.01302 0.00424 0.0027 1.0000 0.0573
-3.500 -0.4060 0.01267 0.00389 0.0034 1.0000 0.0650
-3.250 -0.3825 0.01219 0.00357 0.0041 1.0000 0.0921
-3.000 -0.3596 0.01157 0.00325 0.0047 1.0000 0.1578
-2.750 -0.3369 0.01096 0.00301 0.0053 1.0000 0.2408
-2.500 -0.3141 0.01040 0.00283 0.0060 1.0000 0.3295
-2.000 -0.2693 0.00934 0.00262 0.0076 1.0000 0.5325
-1.750 -0.2472 0.00891 0.00263 0.0088 1.0000 0.6317
-1.500 -0.2250 0.00862 0.00269 0.0102 1.0000 0.7153
-1.250 -0.1986 0.00842 0.00281 0.0109 0.9974 0.7970
-1.000 -0.1663 0.00838 0.00299 0.0108 0.9922 0.8749
-0.750 -0.1281 0.00845 0.00311 0.0091 0.9873 0.9183
-0.500 -0.0872 0.00849 0.00313 0.0065 0.9815 0.9366
-0.250 -0.0441 0.00850 0.00314 0.0033 0.9742 0.9504
0.000 0.0000 0.00851 0.00313 0.0000 0.9631 0.9631
0.250 0.0441 0.00850 0.00314 -0.0033 0.9504 0.9742
0.500 0.0871 0.00848 0.00313 -0.0065 0.9367 0.9814
0.750 0.1281 0.00845 0.00311 -0.0091 0.9183 0.9873
1.000 0.1663 0.00838 0.00299 -0.0108 0.8747 0.9922
1.250 0.1986 0.00842 0.00281 -0.0109 0.7975 0.9974
1.500 0.2249 0.00862 0.00269 -0.0101 0.7155 1.0000
1.750 0.2471 0.00891 0.00263 -0.0088 0.6315 1.0000
2.000 0.2692 0.00934 0.00262 -0.0076 0.5325 1.0000
2.250 0.2918 0.00979 0.00269 -0.0067 0.4392 1.0000
2.500 0.3140 0.01040 0.00283 -0.0060 0.3296 1.0000
2.750 0.3368 0.01095 0.00301 -0.0053 0.2410 1.0000
3.000 0.3596 0.01156 0.00325 -0.0047 0.1582 1.0000
3.250 0.3824 0.01219 0.00357 -0.0041 0.0923 1.0000
3.500 0.4059 0.01267 0.00389 -0.0034 0.0651 1.0000
3.750 0.4301 0.01302 0.00424 -0.0027 0.0573 1.0000
4.000 0.4542 0.01342 0.00463 -0.0021 0.0528 1.0000
4.250 0.4783 0.01386 0.00512 -0.0014 0.0501 1.0000
4.500 0.5025 0.01429 0.00562 -0.0007 0.0483 1.0000
4.750 0.5266 0.01478 0.00618 0.0000 0.0465 1.0000
5.000 0.5507 0.01534 0.00679 0.0006 0.0446 1.0000
5.250 0.5746 0.01593 0.00742 0.0012 0.0421 1.0000
5.500 0.5974 0.01685 0.00835 0.0020 0.0398 1.0000
5.750 0.6210 0.01773 0.00930 0.0027 0.0385 1.0000
6.000 0.6456 0.01835 0.01004 0.0032 0.0365 1.0000
6.250 0.6698 0.01914 0.01098 0.0038 0.0343 1.0000
6.500 0.6938 0.01993 0.01186 0.0044 0.0320 1.0000
6.750 0.7169 0.02094 0.01290 0.0049 0.0295 1.0000
7.000 0.7396 0.02246 0.01460 0.0056 0.0278 1.0000
7.250 0.7634 0.02341 0.01581 0.0062 0.0258 1.0000
7.500 0.7865 0.02441 0.01703 0.0069 0.0233 1.0000
7.750 0.8088 0.02552 0.01833 0.0075 0.0217 1.0000
8.000 0.8303 0.02664 0.01956 0.0081 0.0205 1.0000
8.250 0.8487 0.02873 0.02191 0.0090 0.0193 1.0000
8.500 0.8673 0.03080 0.02446 0.0101 0.0177 1.0000
8.750 0.8818 0.03364 0.02776 0.0114 0.0165 1.0000
9.000 0.8931 0.03677 0.03132 0.0128 0.0156 1.0000
9.250 0.9018 0.03992 0.03485 0.0140 0.0150 1.0000
9.500 0.9088 0.04290 0.03814 0.0152 0.0145 1.0000
9.750 0.9170 0.04508 0.04053 0.0161 0.0141 1.0000
10.000 0.9222 0.04733 0.04295 0.0170 0.0137 1.0000
10.250 0.9123 0.05150 0.04739 0.0180 0.0135 1.0000
10.500 0.7737 0.08749 0.08407 -0.0036 0.0155 1.0000
10.750 0.7545 0.09753 0.09405 -0.0098 0.0157 1.0000
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Polar data table (+)
Polar graphs
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