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NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M24 AIRFOIL (m24-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.3 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m24-il-1000000.txt
Download as CSV file: xf-m24-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M24 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3273   0.09376   0.09096   0.0000   0.5938   0.0186
  -7.750  -0.3242   0.09028   0.08747  -0.0029   0.5903   0.0193
  -7.500  -0.3264   0.08570   0.08286  -0.0088   0.5876   0.0201
  -7.250  -0.3188   0.08117   0.07826  -0.0134   0.5845   0.0202
  -7.000  -0.3074   0.07725   0.07431  -0.0159   0.5815   0.0202
  -6.750  -0.3006   0.07220   0.06921  -0.0179   0.5784   0.0204
  -6.500  -0.2879   0.06941   0.06639  -0.0184   0.5746   0.0206
  -6.250  -0.2729   0.06689   0.06381  -0.0191   0.5707   0.0207
  -6.000  -0.2568   0.06436   0.06124  -0.0201   0.5672   0.0209
  -5.750  -0.2395   0.06179   0.05862  -0.0211   0.5637   0.0211
  -5.500  -0.2211   0.05919   0.05597  -0.0222   0.5599   0.0215
  -5.250  -0.2017   0.05653   0.05322  -0.0233   0.5563   0.0220
  -5.000  -0.1809   0.05367   0.05026  -0.0243   0.5525   0.0231
  -4.750  -0.1510   0.04884   0.04521  -0.0262   0.5500   0.0242
  -4.500  -0.1294   0.04560   0.04185  -0.0265   0.5466   0.0242
  -4.250  -0.1153   0.04135   0.03747  -0.0262   0.5432   0.0246
  -4.000  -0.0938   0.03958   0.03562  -0.0262   0.5394   0.0248
  -3.750  -0.0712   0.03791   0.03386  -0.0263   0.5357   0.0251
  -3.500  -0.0479   0.03618   0.03206  -0.0262   0.5323   0.0255
  -3.250  -0.0239   0.03445   0.03024  -0.0261   0.5285   0.0261
  -3.000   0.0009   0.03237   0.02802  -0.0259   0.5248   0.0273
  -2.750   0.0242   0.02566   0.02080  -0.0236   0.5222   0.0294
  -2.500   0.0489   0.02471   0.01979  -0.0234   0.5187   0.0297
  -2.250   0.0743   0.02365   0.01865  -0.0233   0.5151   0.0301
  -2.000   0.1001   0.02256   0.01746  -0.0231   0.5112   0.0306
  -1.750   0.1262   0.02124   0.01599  -0.0228   0.5073   0.0314
  -1.500   0.1513   0.01759   0.01173  -0.0210   0.5042   0.0351
  -1.250   0.1780   0.01663   0.01076  -0.0210   0.5011   0.0358
  -1.000   0.2056   0.01602   0.01009  -0.0210   0.4972   0.0365
  -0.750   0.2334   0.01537   0.00933  -0.0210   0.4931   0.0376
  -0.500   0.2619   0.01483   0.00862  -0.0209   0.4889   0.0399
  -0.250   0.2915   0.01145   0.00465  -0.0200   0.4864   0.0301
   0.000   0.3202   0.01104   0.00420  -0.0201   0.4828   0.0301
   0.250   0.3485   0.01071   0.00382  -0.0202   0.4789   0.0302
   0.500   0.3767   0.01050   0.00358  -0.0203   0.4747   0.0309
   0.750   0.4048   0.01026   0.00334  -0.0204   0.4712   0.0313
   1.000   0.4328   0.01003   0.00310  -0.0204   0.4675   0.0317
   1.250   0.4606   0.00985   0.00292  -0.0204   0.4637   0.0324
   1.500   0.4884   0.00975   0.00278  -0.0204   0.4598   0.0331
   1.750   0.5163   0.00965   0.00267  -0.0205   0.4563   0.0338
   2.000   0.5445   0.00956   0.00259  -0.0206   0.4527   0.0343
   2.250   0.5721   0.00944   0.00246  -0.0206   0.4487   0.0351
   2.500   0.5998   0.00939   0.00238  -0.0207   0.4445   0.0366
   2.750   0.6279   0.00936   0.00236  -0.0208   0.4408   0.0388
   3.000   0.6562   0.00933   0.00234  -0.0210   0.4374   0.0413
   3.250   0.6840   0.00927   0.00234  -0.0211   0.4336   0.0600
   3.500   0.7112   0.00920   0.00244  -0.0212   0.4297   0.1334
   3.750   0.7385   0.00916   0.00254  -0.0213   0.4258   0.2118
   4.000   0.7432   0.00746   0.00267  -0.0166   0.4232   0.9372
   4.250   0.7749   0.00767   0.00291  -0.0173   0.4191   0.9661
   4.500   0.8185   0.00800   0.00320  -0.0208   0.4145   0.9763
   4.750   0.8577   0.00827   0.00343  -0.0235   0.4103   0.9811
   5.000   0.9233   0.00860   0.00375  -0.0319   0.4061   0.9854
   5.250   0.9635   0.00875   0.00388  -0.0349   0.4019   0.9870
   5.500   1.0081   0.00897   0.00407  -0.0389   0.3972   0.9898
   5.750   1.0608   0.00917   0.00427  -0.0446   0.3932   0.9946
   6.000   1.0939   0.00924   0.00434  -0.0461   0.3892   0.9952
   6.250   1.1238   0.00935   0.00443  -0.0470   0.3841   0.9956
   6.500   1.1535   0.00947   0.00454  -0.0478   0.3789   0.9961
   6.750   1.1833   0.00955   0.00463  -0.0486   0.3730   0.9966
   7.000   1.2127   0.00972   0.00477  -0.0494   0.3670   0.9971
   7.250   1.2426   0.00982   0.00488  -0.0503   0.3611   0.9976
   7.500   1.2723   0.00997   0.00502  -0.0512   0.3542   0.9982
   7.750   1.3020   0.01014   0.00519  -0.0521   0.3472   0.9988
   8.000   1.3313   0.01032   0.00536  -0.0530   0.3394   0.9993
   8.250   1.3602   0.01052   0.00555  -0.0538   0.3310   0.9997
   8.750   1.4110   0.01109   0.00605  -0.0542   0.3077   1.0000
   9.000   1.4335   0.01149   0.00638  -0.0538   0.2916   1.0000
   9.250   1.4536   0.01210   0.00686  -0.0533   0.2649   1.0000
   9.500   1.4577   0.01411   0.00836  -0.0510   0.1887   1.0000
   9.750   1.4390   0.01702   0.01076  -0.0456   0.1078   1.0000
  10.000   1.4163   0.01903   0.01262  -0.0390   0.0764   1.0000
  10.250   1.3895   0.02042   0.01405  -0.0314   0.0698   1.0000
  10.500   1.3646   0.02279   0.01637  -0.0258   0.0515   1.0000
  10.750   1.3412   0.02588   0.01937  -0.0217   0.0291   1.0000
  11.000   1.3341   0.02826   0.02176  -0.0195   0.0225   1.0000
  11.250   1.3344   0.03023   0.02377  -0.0181   0.0203   1.0000
  11.500   1.3348   0.03235   0.02595  -0.0169   0.0191   1.0000
  11.750   1.3342   0.03469   0.02834  -0.0159   0.0179   1.0000
  12.000   1.3350   0.03697   0.03068  -0.0151   0.0172   1.0000
  12.250   1.3370   0.03919   0.03296  -0.0145   0.0167   1.0000
  12.500   1.3378   0.04156   0.03540  -0.0139   0.0162   1.0000
  12.750   1.3379   0.04409   0.03800  -0.0134   0.0157   1.0000
  13.000   1.3369   0.04683   0.04080  -0.0131   0.0152   1.0000
  13.250   1.3347   0.04980   0.04383  -0.0128   0.0148   1.0000
  13.500   1.3291   0.05320   0.04731  -0.0126   0.0143   1.0000
  13.750   1.3244   0.05658   0.05077  -0.0124   0.0139   1.0000
  14.000   1.3257   0.05931   0.05357  -0.0124   0.0137   1.0000
  14.250   1.3253   0.06228   0.05660  -0.0124   0.0135   1.0000
  14.500   1.3237   0.06542   0.05982  -0.0125   0.0132   1.0000
  14.750   1.3226   0.06854   0.06301  -0.0126   0.0129   1.0000
  15.000   1.3205   0.07184   0.06637  -0.0129   0.0127   1.0000
  15.250   1.3178   0.07524   0.06983  -0.0131   0.0124   1.0000
  15.500   1.3157   0.07857   0.07322  -0.0134   0.0122   1.0000
  15.750   1.3121   0.08218   0.07691  -0.0138   0.0120   1.0000
  16.000   1.3080   0.08587   0.08066  -0.0142   0.0118   1.0000
  16.250   1.3025   0.08976   0.08461  -0.0147   0.0116   1.0000
  16.500   1.2942   0.09411   0.08904  -0.0154   0.0113   1.0000
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