NACA M7 AIRFOIL (m7-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M7 AIRFOIL (m7-il) Reynolds number: 100,000 Max Cl/Cd: 50.32 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m7-il-100000.txt Download as CSV file: xf-m7-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M7 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5544 0.11698 0.11304 0.0403 1.0000 0.0393
-8.000 -0.5513 0.11468 0.11081 0.0355 1.0000 0.0398
-7.750 -0.5475 0.11256 0.10873 0.0303 1.0000 0.0401
-7.500 -0.5373 0.11035 0.10651 0.0245 1.0000 0.0404
-7.250 -0.5232 0.10784 0.10397 0.0193 1.0000 0.0405
-7.000 -0.5156 0.09961 0.09587 0.0207 1.0000 0.0413
-6.750 -0.5054 0.09354 0.08987 0.0223 1.0000 0.0428
-6.500 -0.4911 0.08931 0.08567 0.0198 1.0000 0.0444
-6.250 -0.4735 0.08530 0.08167 0.0159 1.0000 0.0464
-6.000 -0.4522 0.08137 0.07773 0.0110 1.0000 0.0487
-5.750 -0.4225 0.07829 0.07455 0.0040 1.0000 0.0518
-5.500 -0.3780 0.07840 0.07424 -0.0056 0.9496 0.0533
-5.250 -0.3714 0.07176 0.06766 -0.0048 0.9245 0.0542
-5.000 -0.3658 0.06755 0.06343 -0.0027 0.9041 0.0559
-4.750 -0.3541 0.06468 0.06047 -0.0018 0.8872 0.0584
-4.500 -0.3375 0.06215 0.05780 -0.0019 0.8724 0.0618
-4.250 -0.2989 0.06397 0.05900 -0.0045 0.8580 0.0667
-4.000 -0.2923 0.05738 0.05258 -0.0036 0.8462 0.0684
-3.750 -0.2778 0.05403 0.04921 -0.0029 0.8343 0.0720
-3.500 -0.2426 0.05457 0.04918 -0.0040 0.8228 0.0804
-3.250 -0.2342 0.04918 0.04397 -0.0028 0.8133 0.0839
-3.000 -0.2084 0.04769 0.04213 -0.0027 0.8032 0.0951
-2.750 -0.1843 0.04594 0.04015 -0.0026 0.7927 0.1080
-2.500 -0.1671 0.04260 0.03683 -0.0018 0.7837 0.1164
-2.250 -0.1445 0.04034 0.03439 -0.0011 0.7749 0.1274
-2.000 -0.1193 0.03830 0.03216 -0.0009 0.7652 0.1415
-1.750 -0.0934 0.03714 0.03065 -0.0002 0.7572 0.1626
-1.500 -0.0711 0.03445 0.02790 0.0002 0.7482 0.1796
-1.250 -0.0476 0.03249 0.02581 0.0008 0.7397 0.2093
-1.000 -0.0272 0.03053 0.02374 0.0020 0.7321 0.2552
-0.750 -0.0042 0.02836 0.02150 0.0025 0.7233 0.3055
-0.500 0.0202 0.02661 0.01957 0.0038 0.7167 0.3337
-0.250 0.0873 0.02601 0.01753 0.0038 0.7081 0.0886
0.000 0.1166 0.02453 0.01558 0.0054 0.7020 0.0772
0.250 0.1490 0.02305 0.01376 0.0055 0.6929 0.0692
0.500 0.1776 0.02234 0.01278 0.0064 0.6862 0.0668
0.750 0.2075 0.02124 0.01162 0.0064 0.6777 0.0676
1.000 0.2364 0.02039 0.01080 0.0067 0.6705 0.0734
1.250 0.2644 0.01988 0.01023 0.0070 0.6627 0.0873
1.500 0.2907 0.01951 0.00997 0.0077 0.6553 0.1386
1.750 0.3949 0.01789 0.00984 -0.0070 0.6458 1.0000
2.000 0.4226 0.01823 0.01009 -0.0074 0.6367 1.0000
2.250 0.4459 0.01839 0.01006 -0.0062 0.6309 1.0000
2.500 0.4738 0.01878 0.01043 -0.0067 0.6216 1.0000
2.750 0.4971 0.01895 0.01046 -0.0055 0.6161 1.0000
3.000 0.5247 0.01939 0.01093 -0.0061 0.6067 1.0000
3.250 0.5488 0.01962 0.01111 -0.0052 0.6007 1.0000
3.500 0.5743 0.01989 0.01139 -0.0049 0.5910 1.0000
3.750 0.5975 0.01983 0.01128 -0.0036 0.5789 1.0000
4.000 0.6197 0.01956 0.01094 -0.0018 0.5659 1.0000
4.250 0.6427 0.01942 0.01074 -0.0003 0.5546 1.0000
4.500 0.6667 0.01949 0.01085 0.0007 0.5466 1.0000
4.750 0.6921 0.01974 0.01119 0.0009 0.5365 1.0000
5.000 0.7157 0.01960 0.01105 0.0022 0.5247 1.0000
5.250 0.7391 0.01939 0.01083 0.0036 0.5126 1.0000
5.500 0.7627 0.01922 0.01065 0.0050 0.5024 1.0000
5.750 0.7872 0.01914 0.01072 0.0058 0.4891 1.0000
6.000 0.8112 0.01880 0.01043 0.0071 0.4726 1.0000
6.250 0.8353 0.01828 0.00999 0.0083 0.4484 1.0000
6.500 0.8595 0.01779 0.00954 0.0094 0.4180 1.0000
6.750 0.8846 0.01758 0.00946 0.0100 0.3667 1.0000
7.000 0.9065 0.01907 0.01003 0.0094 0.1867 1.0000
7.250 0.9257 0.02169 0.01202 0.0084 0.1138 1.0000
7.500 0.9464 0.02314 0.01349 0.0085 0.1032 1.0000
7.750 0.9661 0.02445 0.01489 0.0089 0.0982 1.0000
8.000 0.9848 0.02567 0.01625 0.0097 0.0947 1.0000
8.250 1.0027 0.02692 0.01752 0.0108 0.0923 1.0000
8.500 1.0208 0.02825 0.01880 0.0122 0.0905 1.0000
8.750 1.0408 0.02986 0.02030 0.0138 0.0887 1.0000
9.000 1.0619 0.03113 0.02177 0.0149 0.0862 1.0000
9.250 1.0838 0.03273 0.02358 0.0160 0.0844 1.0000
9.500 1.1062 0.03467 0.02572 0.0172 0.0830 1.0000
9.750 1.1266 0.03679 0.02800 0.0181 0.0797 1.0000
10.000 1.1461 0.04056 0.03180 0.0187 0.0757 1.0000
10.250 1.1581 0.04251 0.03438 0.0200 0.0718 1.0000
10.500 1.1707 0.04547 0.03769 0.0210 0.0678 1.0000
10.750 1.1810 0.05085 0.04314 0.0214 0.0631 1.0000
11.000 1.1784 0.05342 0.04638 0.0230 0.0610 1.0000
11.250 1.1738 0.05760 0.05103 0.0242 0.0604 1.0000
11.500 1.1639 0.06191 0.05571 0.0252 0.0603 1.0000
11.750 1.1489 0.06604 0.06014 0.0259 0.0604 1.0000
12.000 1.1299 0.07009 0.06439 0.0262 0.0608 1.0000
12.250 1.1107 0.07477 0.06925 0.0252 0.0613 1.0000
12.500 1.0917 0.08008 0.07471 0.0235 0.0618 1.0000
12.750 1.0738 0.08600 0.08075 0.0214 0.0624 1.0000
13.000 1.0617 0.09298 0.08779 0.0197 0.0632 1.0000
13.250 0.8835 0.09206 0.08727 0.0218 0.0744 1.0000
13.500 0.8643 0.09906 0.09431 0.0197 0.0755 1.0000
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Polar data table (+)
Polar graphs
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