NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA M22 AIRFOIL (m22-il) Reynolds number: 200,000 Max Cl/Cd: 74.9 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m22-il-200000.txt Download as CSV file: xf-m22-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M22 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.3035 0.02488 0.01759 -0.0243 0.5873 0.0948
0.500 0.3331 0.02400 0.01653 -0.0245 0.5820 0.1052
0.750 0.3621 0.02332 0.01567 -0.0245 0.5768 0.1179
1.000 0.3895 0.02253 0.01469 -0.0244 0.5729 0.1315
1.250 0.4172 0.02151 0.01366 -0.0248 0.5676 0.1463
2.000 0.5095 0.01869 0.01004 -0.0236 0.5538 0.0871
2.250 0.5392 0.01774 0.00893 -0.0234 0.5489 0.0735
2.500 0.5670 0.01701 0.00810 -0.0232 0.5450 0.0699
2.750 0.5951 0.01656 0.00761 -0.0231 0.5400 0.0673
3.000 0.6225 0.01619 0.00725 -0.0230 0.5348 0.0664
3.250 0.6492 0.01592 0.00694 -0.0227 0.5308 0.0672
3.500 0.6764 0.01580 0.00690 -0.0227 0.5262 0.0698
3.750 0.7034 0.01572 0.00684 -0.0226 0.5209 0.0744
4.000 0.7300 0.01563 0.00672 -0.0223 0.5168 0.0885
4.250 0.8034 0.01432 0.00707 -0.0325 0.5101 1.0000
4.500 0.8295 0.01450 0.00724 -0.0323 0.5054 1.0000
4.750 0.8551 0.01468 0.00733 -0.0318 0.5017 1.0000
5.000 0.8815 0.01495 0.00769 -0.0319 0.4963 1.0000
5.250 0.9066 0.01478 0.00741 -0.0312 0.4877 1.0000
5.500 0.9317 0.01435 0.00691 -0.0304 0.4725 1.0000
5.750 0.9578 0.01431 0.00699 -0.0303 0.4619 1.0000
6.000 0.9837 0.01427 0.00701 -0.0300 0.4510 1.0000
6.250 1.0093 0.01388 0.00660 -0.0295 0.4244 1.0000
6.500 1.0351 0.01382 0.00651 -0.0293 0.3906 1.0000
6.750 1.0596 0.01442 0.00681 -0.0294 0.3118 1.0000
7.000 1.0675 0.01928 0.01000 -0.0311 0.0396 1.0000
7.250 1.0877 0.02040 0.01123 -0.0307 0.0323 1.0000
7.500 1.1075 0.02142 0.01244 -0.0302 0.0307 1.0000
7.750 1.1247 0.02268 0.01391 -0.0295 0.0295 1.0000
8.000 1.1380 0.02423 0.01566 -0.0288 0.0288 1.0000
8.250 1.1466 0.02609 0.01771 -0.0279 0.0282 1.0000
8.500 1.1507 0.02830 0.02004 -0.0273 0.0271 1.0000
8.750 1.1480 0.03071 0.02252 -0.0262 0.0261 1.0000
9.000 1.1456 0.03318 0.02505 -0.0249 0.0253 1.0000
9.250 1.1461 0.03551 0.02743 -0.0236 0.0250 1.0000
9.500 1.1496 0.03755 0.02951 -0.0220 0.0249 1.0000
9.750 1.1576 0.03916 0.03115 -0.0200 0.0250 1.0000
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Polar data table (+)
Polar graphs
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