NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 100,000 Max Cl/Cd: 30.65 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212mb-il-100000.txt Download as CSV file: xf-n64212mb-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5141 0.09639 0.09141 -0.0184 1.0000 0.1594
-9.500 -0.4944 0.09395 0.08895 -0.0165 1.0000 0.1648
-9.250 -0.5931 0.08625 0.08147 -0.0309 1.0000 0.1726
-9.000 -0.4996 0.08623 0.08135 -0.0193 1.0000 0.1792
-8.750 -0.5958 0.07913 0.07441 -0.0308 1.0000 0.1885
-8.500 -0.5063 0.07875 0.07402 -0.0216 1.0000 0.1960
-8.250 -0.5687 0.07212 0.06753 -0.0283 1.0000 0.2070
-7.500 -0.6539 0.04349 0.03657 -0.0316 1.0000 0.0854
-7.250 -0.6437 0.04069 0.03352 -0.0292 1.0000 0.0806
-7.000 -0.6354 0.03791 0.03051 -0.0268 1.0000 0.0785
-6.750 -0.6262 0.03564 0.02795 -0.0243 1.0000 0.0779
-6.500 -0.6150 0.03361 0.02562 -0.0220 1.0000 0.0778
-6.250 -0.6016 0.03163 0.02335 -0.0198 1.0000 0.0773
-6.000 -0.5861 0.02976 0.02119 -0.0179 1.0000 0.0767
-5.750 -0.5691 0.02815 0.01934 -0.0161 1.0000 0.0769
-5.500 -0.5510 0.02676 0.01777 -0.0145 1.0000 0.0777
-5.250 -0.5324 0.02559 0.01646 -0.0130 1.0000 0.0795
-5.000 -0.5134 0.02474 0.01541 -0.0115 1.0000 0.0825
-4.750 -0.4938 0.02342 0.01413 -0.0103 1.0000 0.0855
-4.500 -0.4746 0.02245 0.01325 -0.0090 1.0000 0.0889
-4.250 -0.4554 0.02172 0.01251 -0.0077 1.0000 0.0938
-4.000 -0.4372 0.02084 0.01173 -0.0064 1.0000 0.1005
-3.750 -0.4187 0.02019 0.01113 -0.0052 1.0000 0.1099
-3.500 -0.3950 0.01938 0.01045 -0.0051 0.9984 0.1264
-3.250 -0.3651 0.01647 0.00922 -0.0076 0.9941 0.3563
-3.000 -0.3434 0.01664 0.01052 -0.0048 0.9874 0.6531
-2.750 -0.3135 0.01741 0.01128 -0.0042 0.9811 0.6998
-2.500 -0.2858 0.01806 0.01192 -0.0032 0.9738 0.7314
-2.250 -0.2627 0.01895 0.01287 -0.0003 0.9655 0.7677
-2.000 -0.2406 0.02013 0.01416 0.0044 0.9553 0.8066
-1.750 -0.2047 0.02062 0.01458 0.0052 0.9416 0.8321
-1.500 -0.1490 0.02051 0.01434 0.0012 0.9258 0.8402
-1.250 -0.1074 0.02029 0.01400 -0.0011 0.9122 0.8508
-1.000 -0.0642 0.02016 0.01380 -0.0031 0.9011 0.8579
-0.750 -0.0078 0.01984 0.01338 -0.0077 0.8928 0.8655
-0.500 0.0253 0.01960 0.01311 -0.0080 0.8804 0.8730
-0.250 0.0614 0.01925 0.01271 -0.0090 0.8685 0.8818
0.000 0.1072 0.01876 0.01217 -0.0109 0.8567 0.8878
0.250 0.1422 0.01829 0.01167 -0.0111 0.8426 0.8965
0.500 0.1758 0.01780 0.01116 -0.0110 0.8265 0.9042
0.750 0.2061 0.01724 0.01057 -0.0102 0.8083 0.9136
1.000 0.2397 0.01666 0.00997 -0.0099 0.7830 0.9215
1.250 0.2697 0.01603 0.00929 -0.0089 0.7532 0.9316
1.500 0.3046 0.01539 0.00855 -0.0086 0.6986 0.9401
1.750 0.3326 0.01513 0.00761 -0.0070 0.5257 0.9493
2.000 0.3579 0.01624 0.00751 -0.0070 0.3782 0.9598
2.250 0.4005 0.01697 0.00779 -0.0104 0.3448 0.9676
2.500 0.4437 0.01748 0.00807 -0.0138 0.3255 0.9758
2.750 0.4865 0.01798 0.00836 -0.0172 0.3123 0.9845
3.000 0.5319 0.01842 0.00872 -0.0211 0.3016 0.9931
3.250 0.5717 0.01901 0.00910 -0.0242 0.2932 1.0000
3.500 0.5872 0.01928 0.00945 -0.0227 0.2875 1.0000
3.750 0.6028 0.01967 0.00982 -0.0211 0.2822 1.0000
4.000 0.6189 0.02022 0.01026 -0.0197 0.2781 1.0000
4.250 0.6343 0.02077 0.01083 -0.0181 0.2746 1.0000
4.500 0.6496 0.02126 0.01139 -0.0163 0.2709 1.0000
4.750 0.6672 0.02184 0.01201 -0.0149 0.2670 1.0000
5.000 0.6891 0.02254 0.01267 -0.0143 0.2628 1.0000
5.250 0.7138 0.02352 0.01359 -0.0142 0.2589 1.0000
5.500 0.7382 0.02424 0.01450 -0.0139 0.2554 1.0000
5.750 0.7637 0.02512 0.01551 -0.0138 0.2520 1.0000
6.000 0.7897 0.02604 0.01650 -0.0139 0.2485 1.0000
6.250 0.8158 0.02708 0.01752 -0.0140 0.2449 1.0000
6.500 0.8406 0.02836 0.01893 -0.0139 0.2415 1.0000
6.750 0.8639 0.02950 0.02035 -0.0136 0.2384 1.0000
7.000 0.8872 0.03072 0.02179 -0.0133 0.2350 1.0000
7.250 0.9115 0.03186 0.02303 -0.0132 0.2311 1.0000
7.500 0.9372 0.03322 0.02435 -0.0133 0.2274 1.0000
7.750 0.9565 0.03496 0.02639 -0.0128 0.2240 1.0000
8.000 0.9739 0.03655 0.02834 -0.0120 0.2195 1.0000
8.250 0.9950 0.03790 0.02985 -0.0116 0.2149 1.0000
8.500 1.0222 0.03915 0.03095 -0.0118 0.2105 1.0000
8.750 1.0316 0.04146 0.03375 -0.0105 0.2060 1.0000
9.000 1.0438 0.04344 0.03605 -0.0094 0.2007 1.0000
9.250 1.0742 0.04388 0.03632 -0.0097 0.1952 1.0000
9.500 1.0789 0.04671 0.03954 -0.0083 0.1902 1.0000
9.750 1.0816 0.04924 0.04244 -0.0067 0.1844 1.0000
10.000 1.1243 0.04848 0.04131 -0.0076 0.1781 1.0000
10.250 1.1060 0.05277 0.04623 -0.0049 0.1733 1.0000
10.500 1.1005 0.05573 0.04949 -0.0031 0.1680 1.0000
10.750 1.1496 0.05407 0.04750 -0.0039 0.1609 1.0000
11.000 1.1071 0.06000 0.05401 -0.0006 0.1580 1.0000
11.250 1.0562 0.06625 0.06053 0.0020 0.1573 1.0000
11.500 0.9818 0.07673 0.07116 -0.0001 0.1594 1.0000
11.750 0.9043 0.09319 0.08766 -0.0092 0.1612 1.0000
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Polar data table (+)
Polar graphs
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