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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 100,000
Max Cl/Cd: 53.31 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m23-il-100000-n5.txt
Download as CSV file: xf-m23-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M23 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3642   0.11439   0.10981   0.0127   0.7410   0.0277
  -8.250  -0.3574   0.11118   0.10660   0.0112   0.7346   0.0283
  -8.000  -0.3512   0.10812   0.10349   0.0098   0.7294   0.0291
  -7.750  -0.3439   0.10501   0.10040   0.0078   0.7228   0.0304
  -7.500  -0.3375   0.10209   0.09746   0.0056   0.7172   0.0318
  -7.250  -0.3314   0.09968   0.09502   0.0026   0.7119   0.0333
  -7.000  -0.3186   0.09786   0.09315  -0.0030   0.7058   0.0343
  -6.750  -0.3038   0.09582   0.09102  -0.0081   0.7009   0.0347
  -6.500  -0.2861   0.09328   0.08838  -0.0125   0.6955   0.0349
  -6.250  -0.2672   0.09028   0.08526  -0.0159   0.6899   0.0350
  -6.000  -0.2543   0.08549   0.08043  -0.0173   0.6856   0.0353
  -5.750  -0.2508   0.07950   0.07448  -0.0146   0.6805   0.0365
  -5.500  -0.2383   0.07598   0.07093  -0.0148   0.6750   0.0385
  -5.250  -0.2211   0.07296   0.06780  -0.0164   0.6706   0.0411
  -5.000  -0.1990   0.06999   0.06472  -0.0192   0.6653   0.0440
  -4.750  -0.1573   0.06935   0.06371  -0.0257   0.6598   0.0470
  -4.250  -0.1292   0.06068   0.05496  -0.0259   0.6509   0.0496
  -4.000  -0.1092   0.05793   0.05211  -0.0267   0.6455   0.0536
  -3.750  -0.0660   0.05783   0.05151  -0.0304   0.6411   0.0596
  -3.500  -0.0441   0.05401   0.04755  -0.0313   0.6365   0.0606
  -3.250  -0.0297   0.05015   0.04374  -0.0311   0.6313   0.0626
  -3.000  -0.0072   0.04798   0.04143  -0.0313   0.6270   0.0688
  -2.750   0.0313   0.04719   0.04013  -0.0331   0.6226   0.0743
  -2.500   0.0499   0.04369   0.03665  -0.0332   0.6173   0.0761
  -2.250   0.0732   0.04146   0.03428  -0.0333   0.6129   0.0790
  -2.000   0.1118   0.04213   0.03433  -0.0338   0.6091   0.0885
  -1.500   0.1547   0.03631   0.02850  -0.0343   0.5991   0.0955
  -1.250   0.1893   0.03625   0.02788  -0.0343   0.5954   0.1034
  -1.000   0.2218   0.03198   0.02321  -0.0340   0.5909   0.0590
  -0.750   0.2482   0.03025   0.02134  -0.0341   0.5861   0.0570
  -0.500   0.2762   0.02878   0.01959  -0.0339   0.5822   0.0557
  -0.250   0.3054   0.02761   0.01810  -0.0338   0.5781   0.0577
   0.000   0.3343   0.02644   0.01672  -0.0339   0.5729   0.0570
   0.250   0.3629   0.02531   0.01534  -0.0338   0.5688   0.0557
   0.500   0.3913   0.02427   0.01401  -0.0335   0.5654   0.0546
   0.750   0.4208   0.02343   0.01301  -0.0338   0.5601   0.0539
   1.000   0.4497   0.02266   0.01205  -0.0338   0.5555   0.0535
   1.250   0.4783   0.02196   0.01115  -0.0337   0.5519   0.0534
   1.500   0.5072   0.02145   0.01052  -0.0338   0.5476   0.0539
   1.750   0.5360   0.02105   0.01008  -0.0341   0.5425   0.0548
   2.000   0.5666   0.02070   0.00963  -0.0345   0.5385   0.0574
   2.250   0.5955   0.02041   0.00922  -0.0346   0.5352   0.0617
   2.500   0.6224   0.02036   0.00923  -0.0348   0.5297   0.0649
   2.750   0.6485   0.02026   0.00906  -0.0345   0.5254   0.0676
   3.000   0.6744   0.02017   0.00885  -0.0341   0.5220   0.0715
   3.250   0.7007   0.02024   0.00894  -0.0340   0.5174   0.0786
   3.500   0.7269   0.02032   0.00909  -0.0340   0.5126   0.1041
   4.000   0.8365   0.01926   0.00958  -0.0459   0.5034   1.0000
   4.250   0.8616   0.01961   0.00995  -0.0458   0.4984   1.0000
   4.500   0.8865   0.01983   0.01013  -0.0454   0.4945   1.0000
   4.750   0.9114   0.01997   0.01020  -0.0449   0.4914   1.0000
   5.000   0.9360   0.02046   0.01079  -0.0449   0.4858   1.0000
   5.250   0.9605   0.02078   0.01117  -0.0446   0.4815   1.0000
   5.500   0.9852   0.02098   0.01136  -0.0442   0.4781   1.0000
   5.750   1.0094   0.02138   0.01184  -0.0439   0.4737   1.0000
   6.000   1.0333   0.02184   0.01245  -0.0438   0.4686   1.0000
   6.250   1.0576   0.02213   0.01279  -0.0434   0.4649   1.0000
   6.500   1.0824   0.02230   0.01299  -0.0428   0.4619   1.0000
   6.750   1.1046   0.02301   0.01394  -0.0428   0.4558   1.0000
   7.000   1.1295   0.02275   0.01368  -0.0419   0.4479   1.0000
   7.250   1.1523   0.02259   0.01361  -0.0411   0.4341   1.0000
   7.500   1.1745   0.02267   0.01382  -0.0405   0.4211   1.0000
   7.750   1.1964   0.02288   0.01418  -0.0399   0.4092   1.0000
   8.000   1.2175   0.02284   0.01421  -0.0390   0.3896   1.0000
   8.250   1.2358   0.02324   0.01471  -0.0381   0.3639   1.0000
   8.500   1.2523   0.02384   0.01535  -0.0371   0.3345   1.0000
   8.750   1.2579   0.02528   0.01645  -0.0354   0.2694   1.0000
   9.000   1.2386   0.02877   0.01925  -0.0325   0.1785   1.0000
   9.250   1.2139   0.03263   0.02280  -0.0300   0.1298   1.0000
   9.500   1.1902   0.03699   0.02691  -0.0284   0.0851   1.0000
   9.750   1.1683   0.04165   0.03134  -0.0274   0.0497   1.0000
  10.000   1.1560   0.04556   0.03520  -0.0268   0.0359   1.0000
  10.250   1.1499   0.04894   0.03863  -0.0264   0.0313   1.0000
  10.500   1.1444   0.05232   0.04208  -0.0260   0.0290   1.0000
  10.750   1.1412   0.05552   0.04543  -0.0258   0.0276   1.0000
  11.000   1.1376   0.05883   0.04889  -0.0256   0.0265   1.0000
  11.250   1.1335   0.06226   0.05250  -0.0255   0.0256   1.0000
  11.500   1.1288   0.06584   0.05623  -0.0255   0.0246   1.0000
  11.750   1.1239   0.06960   0.06012  -0.0257   0.0236   1.0000
  12.000   1.1179   0.07356   0.06421  -0.0260   0.0227   1.0000
  12.250   1.1111   0.07772   0.06850  -0.0264   0.0218   1.0000
  12.500   1.1053   0.08176   0.07264  -0.0268   0.0211   1.0000
  12.750   1.1040   0.08521   0.07623  -0.0270   0.0207   1.0000
  13.000   1.1036   0.08845   0.07960  -0.0271   0.0203   1.0000
  13.250   1.1058   0.09119   0.08246  -0.0270   0.0199   1.0000
  13.500   1.1124   0.09299   0.08436  -0.0262   0.0195   1.0000
  13.750   1.1244   0.09365   0.08509  -0.0246   0.0190   1.0000
  14.000   1.1397   0.09373   0.08525  -0.0226   0.0181   1.0000
  14.250   1.1540   0.09415   0.08573  -0.0208   0.0170   1.0000
  14.500   1.1680   0.09478   0.08641  -0.0191   0.0160   1.0000
  14.750   1.1841   0.09522   0.08693  -0.0169   0.0156   1.0000
  15.000   1.1984   0.09624   0.08808  -0.0151   0.0152   1.0000
  15.250   1.2094   0.09801   0.09001  -0.0138   0.0150   1.0000
  15.500   1.2169   0.10048   0.09266  -0.0130   0.0148   1.0000
  15.750   1.2202   0.10367   0.09606  -0.0129   0.0147   1.0000
  16.000   1.2200   0.10745   0.10010  -0.0133   0.0147   1.0000
  16.250   1.2167   0.11174   0.10462  -0.0143   0.0147   1.0000
  16.500   1.2111   0.11642   0.10953  -0.0157   0.0146   1.0000
  16.750   1.2037   0.12149   0.11481  -0.0176   0.0146   1.0000
  17.000   1.1949   0.12693   0.12046  -0.0199   0.0145   1.0000
  17.250   1.1851   0.13272   0.12646  -0.0227   0.0145   1.0000
  17.500   1.1744   0.13889   0.13284  -0.0259   0.0144   1.0000
  17.750   1.1630   0.14548   0.13962  -0.0296   0.0145   1.0000
  18.000   1.1508   0.15257   0.14691  -0.0339   0.0145   1.0000
  18.250   1.1376   0.16037   0.15491  -0.0387   0.0147   1.0000
  18.500   1.1226   0.16933   0.16407  -0.0445   0.0149   1.0000
  18.750   1.0994   0.18213   0.17705  -0.0528   0.0156   1.0000
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