NACA M4 AIRFOIL (m4-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M4 AIRFOIL (m4-il) Reynolds number: 100,000 Max Cl/Cd: 45.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m4-il-100000.txt Download as CSV file: xf-m4-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M4 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6064 0.10912 0.10453 0.0271 1.0000 0.0631
-8.250 -0.6090 0.10606 0.10153 0.0215 1.0000 0.0648
-8.000 -0.6116 0.10306 0.09855 0.0137 1.0000 0.0655
-7.750 -0.6079 0.10008 0.09547 0.0059 1.0000 0.0659
-7.500 -0.5986 0.09265 0.08820 0.0137 1.0000 0.0684
-7.250 -0.5898 0.08872 0.08427 0.0136 1.0000 0.0711
-7.000 -0.5810 0.08471 0.08024 0.0108 1.0000 0.0745
-6.750 -0.5667 0.08165 0.07693 0.0007 1.0000 0.0793
-6.500 -0.5574 0.07587 0.07115 -0.0005 1.0000 0.0810
-6.250 -0.5466 0.07168 0.06705 0.0016 1.0000 0.0843
-6.000 -0.5297 0.06807 0.06330 -0.0011 1.0000 0.0912
-5.750 -0.5136 0.06348 0.05855 -0.0039 1.0000 0.0961
-5.500 -0.4913 0.06159 0.05621 -0.0070 1.0000 0.1083
-5.250 -0.4801 0.05625 0.05116 -0.0051 1.0000 0.1134
-5.000 -0.4593 0.05271 0.04739 -0.0068 1.0000 0.1248
-4.750 -0.4382 0.04961 0.04407 -0.0078 1.0000 0.1381
-4.500 -0.4177 0.04647 0.04079 -0.0081 1.0000 0.1524
-4.250 -0.3978 0.04323 0.03752 -0.0080 1.0000 0.1681
-4.000 -0.3778 0.04061 0.03480 -0.0080 1.0000 0.1957
-3.000 -0.2522 0.02864 0.02079 -0.0094 1.0000 0.1359
-2.750 -0.2201 0.02470 0.01629 -0.0089 1.0000 0.1057
-2.500 -0.1918 0.02235 0.01366 -0.0087 1.0000 0.0995
-2.250 -0.1637 0.02071 0.01158 -0.0082 1.0000 0.0961
-2.000 -0.1414 0.01967 0.01054 -0.0078 1.0000 0.1006
-1.750 -0.1243 0.01885 0.00961 -0.0063 1.0000 0.1015
-1.500 -0.1076 0.01816 0.00882 -0.0050 1.0000 0.1014
-1.250 -0.0717 0.01725 0.00783 -0.0070 0.9939 0.1031
-1.000 -0.0212 0.01627 0.00677 -0.0115 0.9828 0.1078
-0.750 0.0261 0.01526 0.00593 -0.0156 0.9705 0.1193
-0.500 0.1056 0.01177 0.00524 -0.0248 0.9747 1.0000
-0.250 0.1557 0.01180 0.00484 -0.0293 0.9554 1.0000
0.000 0.1928 0.01193 0.00478 -0.0311 0.9319 1.0000
0.250 0.2203 0.01213 0.00483 -0.0307 0.9092 1.0000
0.500 0.2428 0.01235 0.00494 -0.0292 0.8881 1.0000
0.750 0.2640 0.01258 0.00507 -0.0275 0.8686 1.0000
1.000 0.2852 0.01281 0.00522 -0.0258 0.8500 1.0000
1.250 0.3064 0.01303 0.00536 -0.0240 0.8327 1.0000
1.500 0.3278 0.01326 0.00551 -0.0223 0.8165 1.0000
1.750 0.3496 0.01348 0.00569 -0.0207 0.8009 1.0000
2.000 0.3728 0.01371 0.00590 -0.0195 0.7844 1.0000
2.250 0.3960 0.01395 0.00612 -0.0184 0.7685 1.0000
2.500 0.4194 0.01419 0.00635 -0.0172 0.7529 1.0000
2.750 0.4430 0.01444 0.00661 -0.0161 0.7376 1.0000
3.000 0.4669 0.01470 0.00691 -0.0150 0.7223 1.0000
3.250 0.4908 0.01495 0.00719 -0.0140 0.7070 1.0000
3.500 0.5147 0.01518 0.00746 -0.0128 0.6912 1.0000
3.750 0.5381 0.01536 0.00766 -0.0114 0.6746 1.0000
4.000 0.5619 0.01549 0.00790 -0.0101 0.6538 1.0000
4.250 0.5840 0.01538 0.00777 -0.0080 0.6283 1.0000
4.500 0.6063 0.01515 0.00754 -0.0058 0.5956 1.0000
4.750 0.6287 0.01487 0.00723 -0.0038 0.5563 1.0000
5.000 0.6522 0.01473 0.00712 -0.0022 0.5101 1.0000
5.250 0.6745 0.01481 0.00705 -0.0005 0.4117 1.0000
5.500 0.6884 0.01842 0.00864 0.0003 0.1111 1.0000
5.750 0.7099 0.02010 0.01017 0.0010 0.0882 1.0000
6.000 0.7307 0.02180 0.01177 0.0021 0.0774 1.0000
6.250 0.7541 0.02332 0.01336 0.0032 0.0710 1.0000
6.500 0.7763 0.02559 0.01548 0.0041 0.0638 1.0000
6.750 0.8018 0.02744 0.01759 0.0051 0.0613 1.0000
7.000 0.8271 0.02983 0.02026 0.0061 0.0600 1.0000
7.250 0.8511 0.03239 0.02319 0.0071 0.0583 1.0000
7.500 0.8733 0.03485 0.02589 0.0078 0.0551 1.0000
7.750 0.8936 0.03857 0.03028 0.0090 0.0567 1.0000
8.000 0.9107 0.04318 0.03548 0.0100 0.0603 1.0000
8.250 0.9246 0.04872 0.04185 0.0114 0.0700 1.0000
8.500 0.8729 0.04511 0.03940 0.0153 0.0865 1.0000
9.250 0.8124 0.09562 0.09079 -0.0176 0.1779 1.0000
9.750 0.8049 0.10467 0.09975 -0.0206 0.1628 1.0000
10.750 0.6638 0.11500 0.11017 -0.0111 0.1559 1.0000
11.000 0.6434 0.11942 0.11454 -0.0142 0.1496 1.0000
11.250 0.8153 0.13117 0.12615 -0.0242 0.1293 1.0000
11.500 0.7929 0.13601 0.13089 -0.0311 0.1228 1.0000
11.750 0.8138 0.13921 0.13415 -0.0277 0.1176 1.0000
12.000 0.6584 0.13512 0.13027 -0.0139 0.1293 1.0000
12.250 0.6317 0.13799 0.13307 -0.0181 0.1243 1.0000
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Polar data table (+)
Polar graphs
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