NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 50,000 Max Cl/Cd: 28.13 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212ma-il-50000-n5.txt Download as CSV file: xf-n64212ma-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3909 0.10180 0.09477 -0.0298 1.0000 0.1588
-8.750 -0.3691 0.09836 0.09133 -0.0277 1.0000 0.1647
-8.500 -0.3986 0.09658 0.08974 -0.0318 1.0000 0.1743
-8.250 -0.3812 0.09235 0.08557 -0.0300 1.0000 0.1792
-8.000 -0.3710 0.08948 0.08275 -0.0290 1.0000 0.1853
-7.500 -0.3854 0.08410 0.07766 -0.0282 1.0000 0.2027
-7.250 -0.3996 0.08192 0.07563 -0.0271 1.0000 0.2089
-7.000 -0.4164 0.07968 0.07357 -0.0251 1.0000 0.2224
-6.500 -0.4918 0.06707 0.05991 -0.0321 1.0000 0.0886
-6.000 -0.4632 0.05946 0.05190 -0.0341 0.9899 0.0785
-5.750 -0.4373 0.05588 0.04806 -0.0369 0.9814 0.0779
-5.500 -0.4122 0.05264 0.04453 -0.0391 0.9726 0.0773
-5.250 -0.3833 0.04942 0.04099 -0.0415 0.9653 0.0756
-5.000 -0.3569 0.04650 0.03764 -0.0429 0.9565 0.0734
-4.750 -0.3247 0.04379 0.03424 -0.0447 0.9496 0.0712
-4.500 -0.2975 0.04167 0.03181 -0.0455 0.9412 0.0708
-4.250 -0.2639 0.03959 0.02948 -0.0474 0.9355 0.0718
-4.000 -0.2377 0.03802 0.02779 -0.0479 0.9274 0.0733
-3.750 -0.2053 0.03644 0.02597 -0.0490 0.9208 0.0745
-3.500 -0.1674 0.03483 0.02407 -0.0509 0.9162 0.0746
-3.250 -0.1433 0.03371 0.02275 -0.0503 0.9076 0.0749
-3.000 -0.1096 0.03253 0.02138 -0.0512 0.9017 0.0755
-2.750 -0.0720 0.03148 0.02015 -0.0526 0.8972 0.0776
-2.500 -0.0479 0.03086 0.01939 -0.0516 0.8888 0.0797
-2.250 -0.0178 0.03004 0.01868 -0.0518 0.8826 0.0820
-2.000 0.0163 0.02935 0.01799 -0.0523 0.8780 0.0839
-1.750 0.0418 0.02890 0.01750 -0.0515 0.8708 0.0859
-1.500 0.0677 0.02852 0.01703 -0.0508 0.8624 0.0888
-1.250 0.1014 0.02782 0.01642 -0.0517 0.8560 0.0941
-1.000 0.1216 0.02756 0.01610 -0.0504 0.8460 0.0985
-0.750 0.1502 0.02702 0.01557 -0.0504 0.8373 0.1037
-0.500 0.1811 0.02652 0.01505 -0.0508 0.8294 0.1135
-0.250 0.2027 0.02622 0.01479 -0.0499 0.8185 0.1264
0.250 0.2343 0.02389 0.01496 -0.0440 0.7999 0.7152
0.500 0.2485 0.02385 0.01515 -0.0378 0.7897 0.8283
0.750 0.2697 0.02382 0.01517 -0.0334 0.7757 0.9020
1.000 0.3859 0.02273 0.01383 -0.0445 0.7524 0.9719
1.250 0.4240 0.02223 0.01319 -0.0457 0.7340 0.9811
1.500 0.4622 0.02173 0.01256 -0.0469 0.7134 0.9910
1.750 0.4921 0.02137 0.01211 -0.0470 0.6923 1.0000
2.000 0.5047 0.02117 0.01182 -0.0441 0.6734 1.0000
2.250 0.5155 0.02107 0.01167 -0.0410 0.6538 1.0000
2.500 0.5265 0.02100 0.01153 -0.0379 0.6320 1.0000
2.750 0.5372 0.02098 0.01145 -0.0348 0.6050 1.0000
3.000 0.5518 0.02096 0.01133 -0.0323 0.5727 1.0000
3.250 0.5688 0.02100 0.01123 -0.0301 0.5315 1.0000
3.500 0.5880 0.02107 0.01104 -0.0282 0.4665 1.0000
3.750 0.6047 0.02150 0.01070 -0.0257 0.3758 1.0000
4.000 0.6184 0.02241 0.01107 -0.0238 0.3227 1.0000
4.250 0.6332 0.02338 0.01165 -0.0222 0.2903 1.0000
4.500 0.6497 0.02431 0.01229 -0.0209 0.2696 1.0000
4.750 0.6684 0.02514 0.01296 -0.0199 0.2541 1.0000
5.000 0.6883 0.02597 0.01365 -0.0190 0.2423 1.0000
5.250 0.7095 0.02677 0.01433 -0.0183 0.2329 1.0000
5.500 0.7327 0.02754 0.01501 -0.0177 0.2257 1.0000
5.750 0.7576 0.02828 0.01572 -0.0174 0.2194 1.0000
6.000 0.7838 0.02905 0.01642 -0.0173 0.2146 1.0000
6.250 0.8123 0.02982 0.01714 -0.0174 0.2107 1.0000
6.500 0.8412 0.03059 0.01798 -0.0176 0.2070 1.0000
6.750 0.8700 0.03142 0.01883 -0.0177 0.2038 1.0000
7.000 0.8986 0.03228 0.01974 -0.0179 0.2009 1.0000
7.250 0.9271 0.03319 0.02062 -0.0182 0.1982 1.0000
7.500 0.9555 0.03418 0.02157 -0.0184 0.1956 1.0000
7.750 0.9800 0.03521 0.02282 -0.0182 0.1926 1.0000
8.000 1.0042 0.03629 0.02406 -0.0180 0.1896 1.0000
8.250 1.0281 0.03739 0.02528 -0.0179 0.1869 1.0000
8.500 1.0521 0.03849 0.02645 -0.0177 0.1840 1.0000
8.750 1.0777 0.03957 0.02749 -0.0177 0.1810 1.0000
9.000 1.0935 0.04092 0.02918 -0.0167 0.1774 1.0000
9.250 1.1100 0.04212 0.03059 -0.0159 0.1730 1.0000
9.500 1.1311 0.04296 0.03139 -0.0154 0.1683 1.0000
9.750 1.1424 0.04435 0.03308 -0.0141 0.1636 1.0000
10.000 1.1551 0.04548 0.03438 -0.0129 0.1586 1.0000
10.250 1.1706 0.04644 0.03538 -0.0120 0.1539 1.0000
10.500 1.1751 0.04801 0.03727 -0.0102 0.1490 1.0000
10.750 1.1896 0.04868 0.03792 -0.0091 0.1441 1.0000
11.000 1.1857 0.05056 0.04015 -0.0068 0.1393 1.0000
11.250 1.1972 0.05124 0.04078 -0.0055 0.1350 1.0000
11.500 1.1873 0.05375 0.04365 -0.0032 0.1310 1.0000
11.750 1.1956 0.05482 0.04473 -0.0021 0.1271 1.0000
12.000 1.1830 0.05792 0.04814 -0.0007 0.1235 1.0000
12.250 1.1885 0.05939 0.04965 0.0001 0.1195 1.0000
12.500 1.1718 0.06335 0.05389 0.0005 0.1164 1.0000
12.750 1.1726 0.06565 0.05625 0.0008 0.1129 1.0000
13.000 1.1522 0.07063 0.06147 0.0001 0.1103 1.0000
13.250 1.1220 0.07738 0.06848 -0.0020 0.1082 1.0000
13.500 1.1246 0.08011 0.07121 -0.0025 0.1051 1.0000
13.750 1.0414 0.09693 0.08841 -0.0118 0.1048 1.0000
14.000 0.9317 0.12592 0.11752 -0.0296 0.1002 1.0000
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