NACA-M1 AIRFOIL (m1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA-M1 AIRFOIL (m1-il) Reynolds number: 100,000 Max Cl/Cd: 24.86 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m1-il-100000-n5.txt Download as CSV file: xf-m1-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA-M1 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7138 0.08829 0.08355 0.0098 1.0000 0.0221
-8.500 -0.7195 0.08200 0.07731 0.0040 1.0000 0.0218
-8.250 -0.7238 0.07567 0.07093 -0.0008 1.0000 0.0216
-8.000 -0.7256 0.06941 0.06455 -0.0044 1.0000 0.0215
-7.750 -0.7249 0.06334 0.05829 -0.0070 1.0000 0.0216
-7.500 -0.7212 0.05743 0.05210 -0.0086 1.0000 0.0221
-7.250 -0.7144 0.05167 0.04596 -0.0094 1.0000 0.0228
-7.000 -0.7040 0.04630 0.04011 -0.0094 1.0000 0.0235
-6.750 -0.6907 0.04129 0.03454 -0.0090 1.0000 0.0240
-6.500 -0.6740 0.03681 0.02936 -0.0082 1.0000 0.0246
-6.250 -0.6539 0.03327 0.02510 -0.0073 1.0000 0.0256
-6.000 -0.6343 0.03029 0.02186 -0.0070 1.0000 0.0282
-5.750 -0.6112 0.02823 0.01947 -0.0064 1.0000 0.0311
-5.500 -0.5865 0.02574 0.01650 -0.0056 1.0000 0.0338
-5.250 -0.5616 0.02377 0.01415 -0.0050 1.0000 0.0383
-5.000 -0.5368 0.02215 0.01242 -0.0045 1.0000 0.0422
-4.750 -0.5109 0.02111 0.01106 -0.0040 1.0000 0.0480
-4.500 -0.4865 0.01957 0.00950 -0.0034 1.0000 0.0520
-4.250 -0.4615 0.01865 0.00851 -0.0029 1.0000 0.0569
-4.000 -0.4362 0.01788 0.00759 -0.0024 1.0000 0.0613
-3.750 -0.4117 0.01695 0.00656 -0.0017 1.0000 0.0633
-3.500 -0.3870 0.01618 0.00572 -0.0012 1.0000 0.0668
-3.250 -0.3616 0.01557 0.00501 -0.0007 1.0000 0.0727
-3.000 -0.3363 0.01489 0.00435 -0.0002 1.0000 0.0864
-2.750 -0.3123 0.01388 0.00375 0.0003 1.0000 0.1680
-2.500 -0.2904 0.01258 0.00335 0.0008 1.0000 0.3735
-2.250 -0.2705 0.01146 0.00321 0.0025 1.0000 0.5958
-2.000 -0.2518 0.01080 0.00341 0.0062 1.0000 0.8225
-1.750 -0.1821 0.01094 0.00357 -0.0005 1.0000 0.9774
-1.500 -0.1278 0.01089 0.00333 -0.0062 1.0000 1.0000
-1.250 -0.1061 0.01076 0.00309 -0.0053 1.0000 1.0000
-1.000 -0.0846 0.01065 0.00291 -0.0044 1.0000 1.0000
-0.750 -0.0631 0.01058 0.00278 -0.0034 1.0000 1.0000
-0.500 -0.0419 0.01053 0.00269 -0.0023 1.0000 1.0000
-0.250 -0.0209 0.01049 0.00263 -0.0012 1.0000 1.0000
0.000 0.0000 0.01048 0.00261 0.0000 1.0000 1.0000
0.250 0.0209 0.01049 0.00263 0.0012 1.0000 1.0000
0.500 0.0419 0.01053 0.00269 0.0023 1.0000 1.0000
0.750 0.0631 0.01058 0.00278 0.0034 1.0000 1.0000
1.000 0.0846 0.01065 0.00291 0.0044 1.0000 1.0000
1.250 0.1062 0.01076 0.00309 0.0053 1.0000 1.0000
1.500 0.1278 0.01089 0.00333 0.0062 1.0000 1.0000
1.750 0.1821 0.01094 0.00357 0.0005 0.9773 1.0000
2.000 0.2518 0.01080 0.00341 -0.0062 0.8223 1.0000
2.250 0.2705 0.01146 0.00320 -0.0025 0.5947 1.0000
2.500 0.2904 0.01258 0.00335 -0.0008 0.3723 1.0000
2.750 0.3124 0.01388 0.00375 -0.0003 0.1673 1.0000
3.000 0.3363 0.01489 0.00435 0.0002 0.0863 1.0000
3.250 0.3616 0.01557 0.00501 0.0007 0.0726 1.0000
3.500 0.3870 0.01618 0.00572 0.0012 0.0667 1.0000
3.750 0.4118 0.01696 0.00656 0.0017 0.0632 1.0000
4.000 0.4362 0.01788 0.00759 0.0024 0.0613 1.0000
4.250 0.4615 0.01866 0.00851 0.0029 0.0570 1.0000
4.500 0.4865 0.01957 0.00950 0.0034 0.0520 1.0000
4.750 0.5109 0.02111 0.01106 0.0040 0.0480 1.0000
5.000 0.5368 0.02215 0.01242 0.0045 0.0422 1.0000
5.250 0.5616 0.02377 0.01415 0.0050 0.0383 1.0000
5.500 0.5865 0.02574 0.01650 0.0056 0.0338 1.0000
5.750 0.6112 0.02822 0.01947 0.0064 0.0311 1.0000
6.000 0.6343 0.03029 0.02185 0.0069 0.0282 1.0000
6.250 0.6539 0.03326 0.02510 0.0073 0.0256 1.0000
6.500 0.6741 0.03681 0.02936 0.0082 0.0246 1.0000
6.750 0.6907 0.04130 0.03455 0.0090 0.0240 1.0000
7.000 0.7040 0.04630 0.04011 0.0094 0.0235 1.0000
7.250 0.7144 0.05167 0.04596 0.0094 0.0228 1.0000
7.500 0.7213 0.05743 0.05211 0.0086 0.0221 1.0000
7.750 0.7250 0.06335 0.05831 0.0069 0.0216 1.0000
8.000 0.7258 0.06943 0.06457 0.0044 0.0215 1.0000
8.250 0.7240 0.07569 0.07095 0.0007 0.0216 1.0000
8.500 0.7198 0.08203 0.07733 -0.0041 0.0218 1.0000
8.750 0.7141 0.08833 0.08360 -0.0099 0.0221 1.0000
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Polar data table (+)
Polar graphs
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