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NACA M18 (nacam18-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 (nacam18-il)
Reynolds number: 500,000
Max Cl/Cd: 99.25 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam18-il-500000-n5.txt
Download as CSV file: xf-nacam18-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4439   0.08810   0.08515  -0.0156   0.7531   0.0212
  -8.500  -0.4470   0.08335   0.08038  -0.0194   0.7421   0.0213
  -8.250  -0.4545   0.07808   0.07505  -0.0243   0.7317   0.0214
  -7.750  -0.4606   0.06767   0.06446  -0.0310   0.7128   0.0220
  -7.250  -0.5279   0.03108   0.02632  -0.0362   0.7062   0.0241
  -7.000  -0.5120   0.02860   0.02354  -0.0351   0.6972   0.0243
  -6.750  -0.4936   0.02658   0.02123  -0.0341   0.6882   0.0245
  -6.500  -0.4735   0.02483   0.01921  -0.0332   0.6801   0.0247
  -6.250  -0.4519   0.02334   0.01745  -0.0324   0.6719   0.0250
  -6.000  -0.4293   0.02198   0.01584  -0.0316   0.6650   0.0252
  -5.750  -0.4056   0.02080   0.01443  -0.0310   0.6578   0.0254
  -5.500  -0.3812   0.01975   0.01315  -0.0304   0.6515   0.0257
  -5.250  -0.3561   0.01879   0.01200  -0.0299   0.6452   0.0259
  -5.000  -0.3304   0.01794   0.01096  -0.0295   0.6391   0.0262
  -4.750  -0.3041   0.01725   0.01012  -0.0291   0.6337   0.0266
  -4.500  -0.2775   0.01661   0.00934  -0.0289   0.6279   0.0270
  -4.250  -0.2507   0.01598   0.00855  -0.0286   0.6224   0.0273
  -4.000  -0.2236   0.01539   0.00783  -0.0283   0.6176   0.0276
  -3.750  -0.1963   0.01485   0.00720  -0.0281   0.6124   0.0278
  -3.500  -0.1690   0.01440   0.00664  -0.0279   0.6071   0.0281
  -3.250  -0.1416   0.01400   0.00615  -0.0278   0.6023   0.0283
  -3.000  -0.1139   0.01363   0.00572  -0.0277   0.5975   0.0285
  -2.750  -0.0863   0.01330   0.00533  -0.0275   0.5924   0.0287
  -2.500  -0.0596   0.01280   0.00476  -0.0273   0.5875   0.0291
  -2.250  -0.0324   0.01240   0.00435  -0.0271   0.5827   0.0296
  -2.000  -0.0050   0.01210   0.00404  -0.0270   0.5778   0.0300
  -1.750   0.0223   0.01186   0.00377  -0.0268   0.5729   0.0305
  -1.500   0.0499   0.01165   0.00354  -0.0267   0.5681   0.0311
  -1.250   0.0775   0.01146   0.00334  -0.0267   0.5627   0.0319
  -1.000   0.1052   0.01130   0.00316  -0.0266   0.5577   0.0327
  -0.750   0.1328   0.01114   0.00297  -0.0265   0.5530   0.0334
  -0.500   0.1606   0.01099   0.00281  -0.0265   0.5474   0.0340
  -0.250   0.1884   0.01088   0.00267  -0.0265   0.5417   0.0346
   0.000   0.2159   0.01074   0.00251  -0.0264   0.5367   0.0359
   0.250   0.2438   0.01062   0.00241  -0.0264   0.5311   0.0375
   0.500   0.2716   0.01055   0.00231  -0.0264   0.5251   0.0396
   0.750   0.2995   0.01048   0.00224  -0.0265   0.5195   0.0431
   1.000   0.3270   0.01036   0.00220  -0.0265   0.5134   0.0595
   1.250   0.3542   0.01025   0.00218  -0.0265   0.5075   0.0917
   1.500   0.3816   0.01013   0.00218  -0.0265   0.5013   0.1294
   1.750   0.4088   0.01002   0.00219  -0.0265   0.4950   0.1768
   2.000   0.4350   0.00981   0.00221  -0.0264   0.4890   0.2660
   2.250   0.4446   0.00798   0.00232  -0.0227   0.4833   0.9041
   2.500   0.4845   0.00819   0.00253  -0.0251   0.4763   0.9473
   2.750   0.5233   0.00841   0.00272  -0.0274   0.4688   0.9656
   3.250   0.6143   0.00891   0.00310  -0.0352   0.4531   0.9842
   3.500   0.6606   0.00908   0.00321  -0.0394   0.4455   0.9878
   3.750   0.6951   0.00917   0.00328  -0.0412   0.4391   0.9900
   4.000   0.7250   0.00926   0.00335  -0.0419   0.4331   0.9913
   4.250   0.7546   0.00938   0.00343  -0.0426   0.4278   0.9926
   4.500   0.7841   0.00947   0.00351  -0.0432   0.4221   0.9938
   4.750   0.8148   0.00957   0.00360  -0.0442   0.4157   0.9945
   5.000   0.8453   0.00968   0.00369  -0.0451   0.4086   0.9953
   5.250   0.8755   0.00980   0.00379  -0.0460   0.4008   0.9961
   5.500   0.9057   0.00993   0.00391  -0.0470   0.3942   0.9970
   5.750   0.9361   0.01005   0.00404  -0.0479   0.3871   0.9980
   6.000   0.9663   0.01021   0.00419  -0.0489   0.3806   0.9989
   6.250   0.9964   0.01034   0.00434  -0.0498   0.3743   0.9998
   6.500   1.0221   0.01051   0.00451  -0.0498   0.3677   1.0000
   6.750   1.0464   0.01065   0.00467  -0.0495   0.3605   1.0000
   7.000   1.0700   0.01085   0.00485  -0.0490   0.3524   1.0000
   7.250   1.0937   0.01102   0.00505  -0.0486   0.3438   1.0000
   7.500   1.1165   0.01126   0.00527  -0.0481   0.3327   1.0000
   7.750   1.1387   0.01154   0.00551  -0.0475   0.3193   1.0000
   8.000   1.1595   0.01191   0.00581  -0.0467   0.2969   1.0000
   8.250   1.1782   0.01243   0.00619  -0.0456   0.2699   1.0000
   8.500   1.1968   0.01293   0.00659  -0.0445   0.2480   1.0000
   8.750   1.2143   0.01347   0.00703  -0.0432   0.2265   1.0000
   9.000   1.2293   0.01415   0.00758  -0.0416   0.1997   1.0000
   9.250   1.2404   0.01503   0.00826  -0.0394   0.1617   1.0000
   9.500   1.2456   0.01617   0.00916  -0.0363   0.1229   1.0000
   9.750   1.2539   0.01702   0.00992  -0.0335   0.1047   1.0000
  10.000   1.2619   0.01780   0.01064  -0.0308   0.0867   1.0000
  10.250   1.2586   0.01900   0.01166  -0.0264   0.0594   1.0000
  10.500   1.2542   0.01999   0.01262  -0.0218   0.0474   1.0000
  10.750   1.2561   0.02111   0.01372  -0.0189   0.0385   1.0000
  11.000   1.2609   0.02235   0.01496  -0.0169   0.0319   1.0000
  11.250   1.2671   0.02368   0.01631  -0.0154   0.0271   1.0000
  11.500   1.2744   0.02508   0.01774  -0.0143   0.0237   1.0000
  11.750   1.2820   0.02656   0.01926  -0.0134   0.0214   1.0000
  12.000   1.2893   0.02815   0.02091  -0.0127   0.0197   1.0000
  12.250   1.2949   0.02996   0.02277  -0.0121   0.0183   1.0000
  12.500   1.3021   0.03170   0.02458  -0.0116   0.0175   1.0000
  12.750   1.3083   0.03358   0.02654  -0.0113   0.0167   1.0000
  13.000   1.3130   0.03563   0.02865  -0.0109   0.0160   1.0000
  13.250   1.3163   0.03788   0.03097  -0.0107   0.0154   1.0000
  13.500   1.3178   0.04034   0.03350  -0.0104   0.0149   1.0000
  13.750   1.3179   0.04297   0.03620  -0.0102   0.0144   1.0000
  14.000   1.3204   0.04539   0.03872  -0.0101   0.0140   1.0000
  14.250   1.3215   0.04796   0.04137  -0.0100   0.0136   1.0000
  14.500   1.3222   0.05066   0.04416  -0.0100   0.0132   1.0000
  14.750   1.3223   0.05351   0.04708  -0.0102   0.0129   1.0000
  15.000   1.3218   0.05648   0.05014  -0.0104   0.0125   1.0000
  15.250   1.3203   0.05964   0.05338  -0.0107   0.0122   1.0000
  15.500   1.3179   0.06298   0.05681  -0.0111   0.0120   1.0000
  15.750   1.3144   0.06653   0.06043  -0.0116   0.0117   1.0000
  16.000   1.3093   0.07033   0.06432  -0.0122   0.0115   1.0000
  16.250   1.3031   0.07437   0.06844  -0.0129   0.0113   1.0000
  16.500   1.3012   0.07789   0.07205  -0.0136   0.0111   1.0000
  16.750   1.2988   0.08149   0.07575  -0.0144   0.0110   1.0000
  17.000   1.2961   0.08517   0.07951  -0.0152   0.0108   1.0000
  17.250   1.2929   0.08896   0.08340  -0.0161   0.0106   1.0000
  17.500   1.2894   0.09284   0.08737  -0.0170   0.0105   1.0000
  17.750   1.2863   0.09668   0.09129  -0.0180   0.0103   1.0000
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