NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 50,000 Max Cl/Cd: 24.33 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212mb-il-50000.txt Download as CSV file: xf-n64212mb-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD B
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4065 0.09953 0.09248 0.0039 1.0000 0.3932
-8.500 -0.5464 0.07723 0.07051 -0.0273 1.0000 0.1933
-8.250 -0.5981 0.06841 0.06158 -0.0334 1.0000 0.1685
-8.000 -0.6253 0.06209 0.05491 -0.0349 1.0000 0.1539
-7.750 -0.6351 0.05687 0.04933 -0.0346 1.0000 0.1444
-7.500 -0.6331 0.05307 0.04516 -0.0334 1.0000 0.1380
-7.250 -0.6274 0.04952 0.04137 -0.0319 1.0000 0.1346
-7.000 -0.6219 0.04630 0.03779 -0.0301 1.0000 0.1324
-6.750 -0.6131 0.04350 0.03465 -0.0283 1.0000 0.1317
-6.500 -0.6020 0.04093 0.03173 -0.0264 1.0000 0.1314
-6.250 -0.5887 0.03853 0.02898 -0.0245 1.0000 0.1312
-6.000 -0.5730 0.03630 0.02642 -0.0227 1.0000 0.1312
-5.750 -0.5556 0.03433 0.02419 -0.0209 1.0000 0.1325
-5.500 -0.5376 0.03266 0.02230 -0.0193 1.0000 0.1364
-5.250 -0.5186 0.03126 0.02053 -0.0176 1.0000 0.1408
-5.000 -0.4976 0.02949 0.01887 -0.0161 1.0000 0.1460
-4.750 -0.4769 0.02826 0.01759 -0.0144 1.0000 0.1540
-4.500 -0.4570 0.02701 0.01648 -0.0126 1.0000 0.1649
-4.250 -0.4382 0.02588 0.01543 -0.0105 1.0000 0.1787
-4.000 -0.4217 0.02469 0.01440 -0.0086 1.0000 0.2018
-3.750 -0.4069 0.02284 0.01310 -0.0069 1.0000 0.2539
-3.500 -0.4168 0.02134 0.01418 0.0025 1.0000 0.6345
-3.250 -0.4221 0.02301 0.01592 0.0136 1.0000 0.7227
-3.000 -0.4217 0.02407 0.01693 0.0224 1.0000 0.7708
-2.750 -0.2147 0.02950 0.02148 0.0123 1.0000 0.9283
-2.500 -0.1678 0.02883 0.02057 0.0075 1.0000 0.9459
-2.250 -0.1260 0.02818 0.01972 0.0031 1.0000 0.9601
-2.000 -0.0858 0.02758 0.01897 -0.0012 1.0000 0.9731
-1.750 -0.0435 0.02702 0.01827 -0.0061 1.0000 0.9855
-1.500 -0.0003 0.02651 0.01765 -0.0113 1.0000 0.9974
-1.250 0.0059 0.02638 0.01749 -0.0102 1.0000 1.0000
-1.000 0.0010 0.02628 0.01739 -0.0072 1.0000 1.0000
-0.750 -0.0042 0.02615 0.01725 -0.0042 1.0000 1.0000
-0.500 -0.0098 0.02597 0.01706 -0.0011 1.0000 1.0000
-0.250 -0.0162 0.02574 0.01682 0.0020 1.0000 1.0000
0.000 -0.0234 0.02544 0.01652 0.0052 1.0000 1.0000
0.250 -0.0316 0.02508 0.01615 0.0086 1.0000 1.0000
0.500 0.0133 0.02550 0.01653 0.0031 0.9864 1.0000
0.750 0.1283 0.02638 0.01741 -0.0130 0.9509 1.0000
1.000 0.2324 0.02633 0.01743 -0.0258 0.9165 1.0000
1.250 0.3799 0.02449 0.01582 -0.0423 0.8670 1.0000
1.500 0.4432 0.02236 0.01381 -0.0434 0.8091 1.0000
1.750 0.4600 0.02095 0.01236 -0.0377 0.7336 1.0000
2.000 0.4699 0.02009 0.01106 -0.0313 0.6175 1.0000
2.250 0.4801 0.02024 0.01048 -0.0271 0.5266 1.0000
2.500 0.4929 0.02074 0.01049 -0.0246 0.4799 1.0000
2.750 0.5088 0.02131 0.01073 -0.0229 0.4522 1.0000
3.000 0.5261 0.02190 0.01110 -0.0214 0.4323 1.0000
3.250 0.5441 0.02252 0.01155 -0.0201 0.4164 1.0000
3.500 0.5627 0.02320 0.01211 -0.0188 0.4033 1.0000
3.750 0.5830 0.02397 0.01273 -0.0178 0.3928 1.0000
4.000 0.6026 0.02477 0.01356 -0.0167 0.3841 1.0000
4.250 0.6251 0.02573 0.01441 -0.0160 0.3765 1.0000
4.500 0.6463 0.02670 0.01547 -0.0154 0.3686 1.0000
4.750 0.6713 0.02785 0.01648 -0.0151 0.3613 1.0000
5.000 0.6928 0.02900 0.01788 -0.0147 0.3548 1.0000
5.250 0.7169 0.03029 0.01925 -0.0145 0.3497 1.0000
5.500 0.7428 0.03178 0.02069 -0.0146 0.3449 1.0000
5.750 0.7622 0.03333 0.02259 -0.0142 0.3402 1.0000
6.000 0.7830 0.03495 0.02442 -0.0139 0.3349 1.0000
6.250 0.8062 0.03664 0.02618 -0.0138 0.3304 1.0000
6.500 0.8284 0.03870 0.02834 -0.0137 0.3274 1.0000
6.750 0.8411 0.04110 0.03117 -0.0132 0.3244 1.0000
7.000 0.8522 0.04374 0.03416 -0.0127 0.3209 1.0000
7.250 0.8634 0.04655 0.03723 -0.0124 0.3176 1.0000
7.500 0.8709 0.04987 0.04082 -0.0122 0.3159 1.0000
7.750 0.8825 0.05297 0.04407 -0.0120 0.3131 1.0000
8.000 0.8926 0.05645 0.04769 -0.0118 0.3101 1.0000
8.250 0.8821 0.06160 0.05309 -0.0120 0.3102 1.0000
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Polar data table (+)
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