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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 500,000
Max Cl/Cd: 102.69 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m23-il-500000-n5.txt
Download as CSV file: xf-m23-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4193   0.11724   0.11410   0.0275   0.6280   0.0079
  -8.750  -0.4133   0.11405   0.11089   0.0261   0.6239   0.0077
  -8.500  -0.4077   0.11067   0.10751   0.0245   0.6196   0.0075
  -8.250  -0.4023   0.10724   0.10407   0.0227   0.6154   0.0075
  -8.000  -0.3972   0.10375   0.10058   0.0209   0.6115   0.0074
  -7.750  -0.3925   0.10021   0.09702   0.0187   0.6079   0.0075
  -7.500  -0.3887   0.09666   0.09349   0.0163   0.6040   0.0075
  -7.250  -0.3825   0.09299   0.08979   0.0135   0.6000   0.0076
  -7.000  -0.3729   0.08885   0.08563   0.0101   0.5963   0.0078
  -6.750  -0.3617   0.08400   0.08075   0.0061   0.5929   0.0083
  -6.500  -0.3460   0.08188   0.07860   0.0042   0.5883   0.0086
  -6.250  -0.3297   0.07906   0.07573   0.0018   0.5841   0.0090
  -6.000  -0.3126   0.07548   0.07209  -0.0012   0.5804   0.0094
  -5.750  -0.2941   0.07159   0.06813  -0.0043   0.5767   0.0096
  -5.500  -0.2739   0.06757   0.06405  -0.0073   0.5727   0.0100
  -5.250  -0.2518   0.06278   0.05914  -0.0107   0.5690   0.0106
  -4.750  -0.2061   0.05750   0.05370  -0.0144   0.5613   0.0121
  -4.500  -0.1817   0.05436   0.05046  -0.0163   0.5573   0.0128
  -4.250  -0.1557   0.05069   0.04664  -0.0183   0.5534   0.0136
  -4.000  -0.1276   0.04643   0.04219  -0.0202   0.5500   0.0150
  -3.750  -0.1036   0.04515   0.04086  -0.0209   0.5457   0.0157
  -3.500  -0.0773   0.04281   0.03839  -0.0219   0.5418   0.0166
  -3.250  -0.0496   0.03994   0.03535  -0.0228   0.5381   0.0175
  -3.000  -0.0182   0.03611   0.03125  -0.0236   0.5349   0.0198
  -2.750   0.0060   0.03509   0.03019  -0.0240   0.5306   0.0205
  -2.500   0.0328   0.03328   0.02825  -0.0244   0.5265   0.0212
  -2.250   0.0605   0.03124   0.02603  -0.0246   0.5229   0.0219
  -2.000   0.0891   0.02924   0.02385  -0.0248   0.5195   0.0232
  -1.750   0.1182   0.02694   0.02134  -0.0247   0.5158   0.0240
  -1.500   0.1472   0.02475   0.01891  -0.0245   0.5119   0.0245
  -1.250   0.1757   0.02281   0.01674  -0.0243   0.5082   0.0248
  -1.000   0.2045   0.01997   0.01354  -0.0238   0.5051   0.0263
  -0.750   0.2328   0.01828   0.01160  -0.0235   0.5016   0.0260
  -0.500   0.2606   0.01654   0.00958  -0.0234   0.4977   0.0263
  -0.250   0.2886   0.01540   0.00822  -0.0234   0.4938   0.0268
   0.000   0.3168   0.01463   0.00729  -0.0235   0.4903   0.0272
   0.250   0.3453   0.01396   0.00651  -0.0236   0.4867   0.0276
   0.500   0.3738   0.01340   0.00583  -0.0238   0.4827   0.0278
   0.750   0.4022   0.01301   0.00535  -0.0239   0.4787   0.0285
   1.000   0.4305   0.01267   0.00494  -0.0241   0.4751   0.0291
   1.250   0.4589   0.01222   0.00442  -0.0242   0.4715   0.0290
   1.500   0.4870   0.01184   0.00398  -0.0243   0.4676   0.0289
   1.750   0.5149   0.01155   0.00363  -0.0243   0.4637   0.0288
   2.000   0.5427   0.01131   0.00336  -0.0244   0.4601   0.0290
   2.250   0.5704   0.01111   0.00315  -0.0244   0.4565   0.0292
   2.500   0.5981   0.01095   0.00299  -0.0245   0.4527   0.0297
   2.750   0.6258   0.01085   0.00287  -0.0246   0.4489   0.0305
   3.000   0.6536   0.01077   0.00280  -0.0248   0.4452   0.0315
   3.250   0.6816   0.01072   0.00276  -0.0249   0.4413   0.0326
   3.500   0.7096   0.01070   0.00274  -0.0251   0.4376   0.0334
   3.750   0.7376   0.01072   0.00276  -0.0254   0.4338   0.0341
   4.000   0.7657   0.01075   0.00280  -0.0256   0.4301   0.0354
   4.250   0.7938   0.01076   0.00283  -0.0259   0.4261   0.0373
   4.500   0.8219   0.01081   0.00289  -0.0261   0.4223   0.0385
   4.750   0.8499   0.01089   0.00298  -0.0264   0.4187   0.0413
   5.000   0.8777   0.01090   0.00312  -0.0267   0.4149   0.0874
   5.250   0.9022   0.01033   0.00334  -0.0266   0.4109   0.5773
   5.750   1.0140   0.00997   0.00395  -0.0396   0.3833   0.9991
   6.000   1.0454   0.01018   0.00414  -0.0408   0.3709   1.0000
   6.250   1.0709   0.01043   0.00433  -0.0408   0.3527   1.0000
   6.500   1.0959   0.01078   0.00458  -0.0408   0.3312   1.0000
   6.750   1.1198   0.01145   0.00504  -0.0409   0.2877   1.0000
   7.250   1.1447   0.01671   0.00881  -0.0407   0.0176   1.0000
   7.500   1.1653   0.01727   0.00943  -0.0400   0.0142   1.0000
   7.750   1.1856   0.01779   0.01002  -0.0393   0.0128   1.0000
   8.000   1.2048   0.01838   0.01069  -0.0385   0.0117   1.0000
   8.250   1.2225   0.01908   0.01147  -0.0376   0.0107   1.0000
   8.500   1.2378   0.01991   0.01238  -0.0365   0.0099   1.0000
   8.750   1.2480   0.02108   0.01365  -0.0349   0.0092   1.0000
   9.000   1.2569   0.02226   0.01491  -0.0334   0.0087   1.0000
   9.250   1.2617   0.02360   0.01633  -0.0319   0.0083   1.0000
   9.500   1.2629   0.02524   0.01805  -0.0301   0.0079   1.0000
   9.750   1.2662   0.02715   0.02006  -0.0291   0.0076   1.0000
  10.000   1.2697   0.02924   0.02223  -0.0285   0.0073   1.0000
  10.250   1.2725   0.03149   0.02456  -0.0280   0.0070   1.0000
  10.500   1.2746   0.03388   0.02703  -0.0276   0.0068   1.0000
  10.750   1.2753   0.03645   0.02967  -0.0272   0.0066   1.0000
  11.000   1.2742   0.03923   0.03253  -0.0268   0.0064   1.0000
  11.250   1.2707   0.04230   0.03569  -0.0265   0.0062   1.0000
  11.500   1.2639   0.04574   0.03922  -0.0261   0.0061   1.0000
  11.750   1.2562   0.04931   0.04287  -0.0258   0.0060   1.0000
  12.000   1.2559   0.05210   0.04574  -0.0255   0.0059   1.0000
  12.250   1.2565   0.05489   0.04864  -0.0254   0.0057   1.0000
  12.500   1.2576   0.05770   0.05153  -0.0253   0.0055   1.0000
  12.750   1.2587   0.06050   0.05441  -0.0253   0.0053   1.0000
  13.000   1.2596   0.06338   0.05736  -0.0253   0.0051   1.0000
  13.250   1.2609   0.06622   0.06028  -0.0253   0.0049   1.0000
  13.500   1.2617   0.06910   0.06323  -0.0253   0.0048   1.0000
  13.750   1.2632   0.07191   0.06611  -0.0253   0.0046   1.0000
  14.000   1.2652   0.07469   0.06896  -0.0253   0.0045   1.0000
  14.250   1.2676   0.07742   0.07175  -0.0254   0.0044   1.0000
  14.500   1.2698   0.08019   0.07459  -0.0255   0.0043   1.0000
  14.750   1.2722   0.08293   0.07739  -0.0256   0.0042   1.0000
  15.000   1.2745   0.08566   0.08020  -0.0256   0.0041   1.0000
  15.250   1.2765   0.08835   0.08294  -0.0255   0.0040   1.0000
  15.500   1.2787   0.09071   0.08537  -0.0249   0.0039   1.0000
  15.750   1.2816   0.09336   0.08815  -0.0248   0.0038   1.0000
  16.000   1.2842   0.09603   0.09095  -0.0246   0.0038   1.0000
  16.250   1.2860   0.09884   0.09390  -0.0244   0.0037   1.0000
  16.500   1.2865   0.10192   0.09714  -0.0243   0.0036   1.0000
  16.750   1.2850   0.10534   0.10072  -0.0244   0.0035   1.0000
  17.000   1.2820   0.10914   0.10469  -0.0248   0.0035   1.0000
  17.250   1.2772   0.11344   0.10917  -0.0257   0.0034   1.0000
  17.500   1.2712   0.11809   0.11399  -0.0269   0.0033   1.0000
  17.750   1.2641   0.12309   0.11915  -0.0286   0.0032   1.0000
  18.000   1.2561   0.12836   0.12459  -0.0306   0.0031   1.0000
  18.250   1.2474   0.13394   0.13032  -0.0330   0.0031   1.0000
  18.500   1.2385   0.13975   0.13628  -0.0357   0.0030   1.0000
  18.750   1.2281   0.14605   0.14275  -0.0388   0.0030   1.0000
  19.000   1.2169   0.15276   0.14963  -0.0423   0.0030   1.0000
  19.250   1.2057   0.15971   0.15673  -0.0461   0.0029   1.0000
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