NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 50,000 Max Cl/Cd: 29.91 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212ma-il-50000.txt Download as CSV file: xf-n64212ma-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD A
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3344 0.10021 0.09332 -0.0145 1.0000 0.3162
-8.250 -0.3280 0.09785 0.09104 -0.0131 1.0000 0.3404
-8.000 -0.3343 0.09668 0.08999 -0.0117 1.0000 0.3661
-7.750 -0.3022 0.09285 0.08618 -0.0092 1.0000 0.4006
-7.500 -0.2846 0.09053 0.08392 -0.0067 1.0000 0.4402
-7.250 -0.2659 0.08825 0.08170 -0.0041 1.0000 0.4828
-7.000 -0.2455 0.08566 0.07918 -0.0020 1.0000 0.5242
-6.750 -0.2282 0.08311 0.07670 -0.0002 1.0000 0.5623
-6.500 -0.2397 0.08398 0.07771 0.0043 1.0000 0.5986
-6.250 -0.2022 0.07953 0.07328 0.0042 1.0000 0.6421
-6.000 -0.1658 0.07478 0.06856 0.0032 1.0000 0.6801
-5.750 -0.1631 0.07368 0.06758 0.0060 1.0000 0.7155
-5.500 -0.1600 0.07240 0.06642 0.0082 1.0000 0.7372
-5.250 -0.1562 0.06974 0.06387 0.0089 1.0000 0.7386
-4.250 -0.2517 0.06668 0.06138 0.0247 1.0000 0.6754
-4.000 -0.3513 0.06731 0.06226 0.0328 1.0000 0.6047
-3.750 -0.4199 0.06593 0.06105 0.0378 1.0000 0.5642
-3.500 -0.4344 0.04374 0.03682 -0.0153 1.0000 0.2880
-3.250 -0.3954 0.04185 0.03399 -0.0184 1.0000 0.2320
-3.000 -0.3665 0.04001 0.03159 -0.0190 1.0000 0.2043
-2.750 -0.3403 0.03885 0.02993 -0.0189 1.0000 0.1893
-2.500 -0.3157 0.03747 0.02815 -0.0187 1.0000 0.1796
-2.250 -0.2917 0.03684 0.02712 -0.0181 1.0000 0.1731
-2.000 -0.2694 0.03540 0.02557 -0.0176 1.0000 0.1682
-1.750 -0.2462 0.03445 0.02436 -0.0170 1.0000 0.1627
-1.500 -0.2230 0.03411 0.02364 -0.0162 1.0000 0.1582
-1.250 -0.2013 0.03363 0.02299 -0.0154 1.0000 0.1566
-1.000 -0.1801 0.03302 0.02230 -0.0146 1.0000 0.1572
-0.750 -0.1597 0.03226 0.02159 -0.0137 1.0000 0.1588
-0.500 -0.1397 0.03178 0.02117 -0.0126 1.0000 0.1608
-0.250 -0.1201 0.03151 0.02091 -0.0113 1.0000 0.1622
0.000 -0.1003 0.03135 0.02075 -0.0102 1.0000 0.1643
0.250 -0.0802 0.03128 0.02067 -0.0094 1.0000 0.1680
0.500 -0.0192 0.03192 0.02134 -0.0159 0.9818 0.1819
0.750 0.0367 0.03223 0.02171 -0.0216 0.9628 0.2035
1.000 0.0778 0.03062 0.02258 -0.0231 0.9423 0.7182
1.250 0.1423 0.03098 0.02316 -0.0245 0.9110 1.0000
1.500 0.2287 0.03155 0.02327 -0.0326 0.8756 1.0000
1.750 0.2731 0.03165 0.02320 -0.0347 0.8513 1.0000
2.000 0.3248 0.03167 0.02310 -0.0377 0.8298 1.0000
2.250 0.3815 0.03134 0.02272 -0.0408 0.8082 1.0000
2.500 0.4373 0.03058 0.02195 -0.0431 0.7850 1.0000
2.750 0.4809 0.02964 0.02102 -0.0431 0.7604 1.0000
3.000 0.5220 0.02835 0.01975 -0.0421 0.7326 1.0000
3.250 0.5662 0.02667 0.01811 -0.0409 0.7038 1.0000
3.500 0.6038 0.02488 0.01634 -0.0384 0.6678 1.0000
3.750 0.6363 0.02286 0.01422 -0.0346 0.6105 1.0000
4.000 0.6545 0.02188 0.01271 -0.0296 0.5021 1.0000
4.250 0.6707 0.02251 0.01237 -0.0264 0.4138 1.0000
4.500 0.6916 0.02373 0.01291 -0.0250 0.3733 1.0000
4.750 0.7196 0.02496 0.01376 -0.0249 0.3492 1.0000
5.000 0.7487 0.02608 0.01475 -0.0250 0.3337 1.0000
5.250 0.7796 0.02723 0.01572 -0.0254 0.3235 1.0000
5.500 0.8081 0.02834 0.01685 -0.0256 0.3157 1.0000
5.750 0.8385 0.02954 0.01794 -0.0260 0.3097 1.0000
6.000 0.8665 0.03086 0.01929 -0.0263 0.3053 1.0000
6.250 0.8914 0.03218 0.02079 -0.0261 0.3015 1.0000
6.500 0.9162 0.03359 0.02235 -0.0260 0.2980 1.0000
6.750 0.9407 0.03507 0.02396 -0.0259 0.2947 1.0000
7.000 0.9653 0.03664 0.02560 -0.0259 0.2917 1.0000
7.250 0.9904 0.03840 0.02740 -0.0259 0.2889 1.0000
7.500 1.0092 0.04036 0.02959 -0.0254 0.2868 1.0000
7.750 1.0236 0.04246 0.03206 -0.0246 0.2847 1.0000
8.000 1.0355 0.04479 0.03472 -0.0236 0.2825 1.0000
8.250 1.0447 0.04734 0.03758 -0.0226 0.2801 1.0000
8.500 1.0523 0.05001 0.04051 -0.0216 0.2772 1.0000
8.750 1.0656 0.05236 0.04300 -0.0209 0.2732 1.0000
9.000 1.0894 0.05445 0.04506 -0.0207 0.2670 1.0000
9.250 1.0741 0.05844 0.04946 -0.0187 0.2649 1.0000
9.500 1.0481 0.06342 0.05475 -0.0169 0.2639 1.0000
9.750 1.0102 0.06961 0.06110 -0.0156 0.2652 1.0000
10.000 0.9722 0.07678 0.06834 -0.0158 0.2671 1.0000
10.250 1.0235 0.07419 0.06577 -0.0134 0.2473 1.0000
10.500 0.9839 0.08192 0.07358 -0.0144 0.2484 1.0000
10.750 0.6861 0.13480 0.12624 -0.0562 0.4441 1.0000
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Polar data table (+)
Polar graphs
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