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NACA M18 (nacam18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M18 (nacam18-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.09 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacam18-il-1000000.txt
Download as CSV file: xf-nacam18-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4460   0.09200   0.08988  -0.0149   0.7976   0.0234
  -8.750  -0.4485   0.08689   0.08472  -0.0189   0.7843   0.0234
  -8.500  -0.4650   0.08013   0.07793  -0.0239   0.7720   0.0238
  -8.250  -0.4661   0.07695   0.07468  -0.0253   0.7586   0.0239
  -8.000  -0.4606   0.07390   0.07156  -0.0269   0.7456   0.0240
  -7.750  -0.4532   0.07085   0.06845  -0.0285   0.7335   0.0242
  -7.500  -0.4443   0.06783   0.06534  -0.0300   0.7224   0.0245
  -7.250  -0.3634   0.05561   0.05315  -0.0338   0.6888   0.0256
  -7.000  -0.3641   0.05067   0.04812  -0.0356   0.6820   0.0264
  -6.750  -0.4127   0.05592   0.05309  -0.0351   0.6938   0.0273
  -6.500  -0.4268   0.04004   0.03666  -0.0367   0.6900   0.0285
  -6.250  -0.4083   0.03871   0.03523  -0.0362   0.6812   0.0287
  -6.000  -0.3890   0.03725   0.03367  -0.0358   0.6736   0.0289
  -5.750  -0.3689   0.03578   0.03209  -0.0353   0.6662   0.0293
  -5.500  -0.3481   0.03435   0.03053  -0.0349   0.6596   0.0298
  -5.250  -0.3581   0.02006   0.01478  -0.0292   0.6567   0.0274
  -5.000  -0.3352   0.01836   0.01277  -0.0283   0.6504   0.0274
  -4.750  -0.3092   0.01769   0.01192  -0.0279   0.6447   0.0277
  -4.500  -0.2839   0.01667   0.01066  -0.0273   0.6392   0.0281
  -4.250  -0.2584   0.01537   0.00916  -0.0268   0.6336   0.0282
  -4.000  -0.2322   0.01426   0.00790  -0.0265   0.6284   0.0284
  -3.750  -0.2052   0.01342   0.00697  -0.0263   0.6234   0.0286
  -3.500  -0.1779   0.01278   0.00626  -0.0261   0.6183   0.0288
  -3.250  -0.1505   0.01229   0.00569  -0.0259   0.6131   0.0291
  -3.000  -0.1228   0.01182   0.00520  -0.0258   0.6086   0.0294
  -2.750  -0.0952   0.01144   0.00478  -0.0257   0.6036   0.0297
  -2.500  -0.0676   0.01112   0.00441  -0.0255   0.5988   0.0301
  -2.250  -0.0398   0.01081   0.00408  -0.0254   0.5943   0.0305
  -2.000  -0.0120   0.01055   0.00381  -0.0254   0.5893   0.0312
  -1.750   0.0157   0.01031   0.00352  -0.0252   0.5843   0.0318
  -1.500   0.0434   0.01009   0.00327  -0.0251   0.5796   0.0323
  -1.250   0.0714   0.00987   0.00304  -0.0251   0.5749   0.0327
  -1.000   0.0994   0.00970   0.00285  -0.0251   0.5696   0.0331
  -0.750   0.1267   0.00949   0.00258  -0.0249   0.5644   0.0336
  -0.500   0.1543   0.00922   0.00231  -0.0248   0.5598   0.0346
  -0.250   0.1823   0.00907   0.00215  -0.0248   0.5543   0.0357
   0.000   0.2102   0.00898   0.00203  -0.0248   0.5486   0.0370
   0.250   0.2386   0.00887   0.00193  -0.0249   0.5436   0.0385
   0.500   0.2667   0.00877   0.00182  -0.0250   0.5378   0.0409
   0.750   0.2947   0.00870   0.00174  -0.0250   0.5319   0.0456
   1.000   0.3224   0.00851   0.00169  -0.0250   0.5261   0.0784
   1.250   0.3497   0.00835   0.00168  -0.0250   0.5199   0.1324
   1.500   0.3771   0.00820   0.00168  -0.0251   0.5138   0.1903
   1.750   0.4027   0.00784   0.00169  -0.0249   0.5074   0.3343
   2.000   0.4087   0.00612   0.00173  -0.0203   0.5016   0.9185
   2.250   0.4386   0.00625   0.00190  -0.0205   0.4949   0.9573
   2.500   0.4696   0.00644   0.00204  -0.0210   0.4875   0.9710
   2.750   0.5141   0.00665   0.00222  -0.0247   0.4803   0.9763
   3.000   0.5515   0.00686   0.00237  -0.0268   0.4730   0.9822
   3.250   0.6098   0.00712   0.00258  -0.0337   0.4654   0.9858
   3.500   0.6553   0.00729   0.00270  -0.0377   0.4584   0.9887
   3.750   0.6967   0.00746   0.00283  -0.0409   0.4519   0.9926
   4.000   0.7373   0.00755   0.00290  -0.0439   0.4450   0.9947
   4.250   0.7708   0.00764   0.00295  -0.0455   0.4376   0.9955
   4.500   0.8024   0.00769   0.00298  -0.0466   0.4306   0.9962
   4.750   0.8336   0.00779   0.00304  -0.0477   0.4235   0.9970
   5.000   0.8649   0.00784   0.00309  -0.0488   0.4175   0.9977
   5.250   0.8962   0.00793   0.00316  -0.0499   0.4109   0.9985
   5.500   0.9276   0.00802   0.00324  -0.0510   0.4051   0.9993
   5.750   0.9592   0.00810   0.00333  -0.0522   0.3989   0.9999
   6.000   0.9854   0.00823   0.00343  -0.0523   0.3916   1.0000
   6.250   1.0112   0.00829   0.00350  -0.0522   0.3852   1.0000
   6.500   1.0365   0.00845   0.00362  -0.0521   0.3761   1.0000
   6.750   1.0621   0.00854   0.00372  -0.0521   0.3675   1.0000
   7.000   1.0870   0.00869   0.00385  -0.0519   0.3580   1.0000
   7.250   1.1113   0.00889   0.00400  -0.0517   0.3431   1.0000
   7.500   1.1351   0.00910   0.00416  -0.0513   0.3285   1.0000
   7.750   1.1585   0.00935   0.00435  -0.0510   0.3130   1.0000
   8.000   1.1814   0.00962   0.00457  -0.0505   0.2962   1.0000
   8.250   1.2035   0.00994   0.00483  -0.0499   0.2780   1.0000
   8.500   1.2244   0.01036   0.00514  -0.0492   0.2570   1.0000
   8.750   1.2448   0.01078   0.00548  -0.0484   0.2365   1.0000
   9.000   1.2629   0.01136   0.00592  -0.0472   0.2101   1.0000
   9.250   1.2765   0.01222   0.00653  -0.0454   0.1679   1.0000
   9.500   1.2830   0.01347   0.00746  -0.0424   0.1172   1.0000
   9.750   1.2938   0.01429   0.00814  -0.0400   0.0928   1.0000
  10.000   1.2957   0.01550   0.00910  -0.0362   0.0546   1.0000
  10.250   1.2991   0.01647   0.00996  -0.0326   0.0360   1.0000
  10.500   1.3046   0.01723   0.01069  -0.0293   0.0280   1.0000
  10.750   1.3087   0.01788   0.01134  -0.0257   0.0248   1.0000
  11.000   1.3096   0.01857   0.01206  -0.0217   0.0228   1.0000
  11.250   1.3166   0.01939   0.01291  -0.0193   0.0213   1.0000
  11.500   1.3233   0.02047   0.01402  -0.0174   0.0198   1.0000
  11.750   1.3324   0.02158   0.01519  -0.0161   0.0188   1.0000
  12.000   1.3429   0.02271   0.01637  -0.0152   0.0180   1.0000
  12.250   1.3524   0.02401   0.01773  -0.0144   0.0173   1.0000
  12.500   1.3599   0.02555   0.01931  -0.0136   0.0166   1.0000
  12.750   1.3632   0.02757   0.02139  -0.0129   0.0159   1.0000
  13.000   1.3688   0.02944   0.02335  -0.0123   0.0155   1.0000
  13.250   1.3764   0.03119   0.02516  -0.0120   0.0152   1.0000
  13.500   1.3824   0.03313   0.02717  -0.0118   0.0148   1.0000
  13.750   1.3873   0.03520   0.02930  -0.0115   0.0144   1.0000
  14.000   1.3913   0.03739   0.03156  -0.0113   0.0140   1.0000
  14.250   1.3939   0.03975   0.03398  -0.0112   0.0137   1.0000
  14.500   1.3935   0.04243   0.03673  -0.0110   0.0134   1.0000
  14.750   1.3892   0.04558   0.03996  -0.0108   0.0130   1.0000
  15.000   1.3802   0.04932   0.04379  -0.0107   0.0127   1.0000
  15.250   1.3761   0.05266   0.04722  -0.0108   0.0126   1.0000
  15.500   1.3769   0.05551   0.05015  -0.0111   0.0124   1.0000
  15.750   1.3767   0.05850   0.05322  -0.0114   0.0123   1.0000
  16.000   1.3755   0.06167   0.05647  -0.0118   0.0121   1.0000
  16.250   1.3740   0.06494   0.05981  -0.0123   0.0119   1.0000
  16.500   1.3717   0.06834   0.06330  -0.0128   0.0117   1.0000
  16.750   1.3691   0.07183   0.06687  -0.0134   0.0115   1.0000
  17.000   1.3659   0.07546   0.07057  -0.0141   0.0114   1.0000
  17.250   1.3625   0.07916   0.07434  -0.0148   0.0112   1.0000
  17.500   1.3592   0.08286   0.07811  -0.0156   0.0110   1.0000
  17.750   1.3555   0.08662   0.08194  -0.0165   0.0109   1.0000
  18.000   1.3510   0.09058   0.08597  -0.0174   0.0108   1.0000
  18.250   1.3460   0.09464   0.09010  -0.0185   0.0106   1.0000
  18.500   1.3405   0.09875   0.09427  -0.0195   0.0105   1.0000
  18.750   1.3334   0.10312   0.09871  -0.0207   0.0103   1.0000
  19.000   1.3247   0.10769   0.10335  -0.0219   0.0101   1.0000
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