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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.86 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m20-il-1000000.txt
Download as CSV file: xf-m20-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M20 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3968   0.11336   0.11099   0.0103   0.7063   0.0115
  -8.750  -0.3915   0.10991   0.10751   0.0084   0.7003   0.0116
  -8.500  -0.3878   0.10568   0.10327   0.0074   0.6942   0.0117
  -8.250  -0.3807   0.10276   0.10032   0.0066   0.6879   0.0118
  -8.000  -0.3735   0.09998   0.09754   0.0052   0.6819   0.0120
  -7.750  -0.3663   0.09719   0.09473   0.0037   0.6756   0.0122
  -7.500  -0.3593   0.09433   0.09186   0.0018   0.6698   0.0125
  -7.250  -0.3529   0.09153   0.08904  -0.0004   0.6638   0.0130
  -7.000  -0.3414   0.08817   0.08565  -0.0038   0.6583   0.0140
  -6.750  -0.3241   0.08370   0.08114  -0.0107   0.6536   0.0147
  -6.500  -0.3070   0.07937   0.07677  -0.0161   0.6484   0.0148
  -6.250  -0.2890   0.07531   0.07264  -0.0201   0.6432   0.0148
  -6.000  -0.2762   0.07030   0.06760  -0.0226   0.6384   0.0150
  -5.750  -0.2603   0.06767   0.06493  -0.0237   0.6324   0.0153
  -5.500  -0.2411   0.06513   0.06233  -0.0256   0.6268   0.0156
  -5.250  -0.2200   0.06255   0.05970  -0.0278   0.6214   0.0162
  -5.000  -0.1864   0.05902   0.05604  -0.0327   0.6161   0.0185
  -4.750  -0.1582   0.05517   0.05205  -0.0361   0.6112   0.0187
  -4.500  -0.1324   0.05154   0.04833  -0.0383   0.6059   0.0187
  -4.250  -0.1124   0.04640   0.04307  -0.0403   0.6009   0.0191
  -4.000  -0.0913   0.04470   0.04131  -0.0408   0.5954   0.0195
  -3.750  -0.0672   0.04284   0.03940  -0.0418   0.5899   0.0201
  -3.500  -0.0411   0.04073   0.03717  -0.0429   0.5845   0.0211
  -3.250  -0.0046   0.03834   0.03459  -0.0443   0.5795   0.0234
  -3.000   0.0241   0.03569   0.03180  -0.0451   0.5741   0.0236
  -2.750   0.0523   0.03289   0.02881  -0.0456   0.5688   0.0236
  -2.500   0.0754   0.02821   0.02392  -0.0462   0.5645   0.0244
  -2.250   0.1011   0.02691   0.02254  -0.0465   0.5589   0.0249
  -2.000   0.1275   0.02565   0.02116  -0.0468   0.5536   0.0254
  -1.750   0.1549   0.02425   0.01966  -0.0470   0.5485   0.0263
  -1.500   0.1836   0.02274   0.01800  -0.0470   0.5430   0.0284
  -1.250   0.2153   0.02170   0.01675  -0.0466   0.5377   0.0301
  -1.000   0.2419   0.01709   0.01167  -0.0461   0.5336   0.0310
  -0.750   0.2691   0.01602   0.01048  -0.0462   0.5283   0.0318
  -0.500   0.2967   0.01539   0.00976  -0.0464   0.5231   0.0325
  -0.250   0.3247   0.01469   0.00898  -0.0465   0.5181   0.0335
   0.000   0.3530   0.01399   0.00815  -0.0466   0.5127   0.0350
   0.250   0.3817   0.01368   0.00772  -0.0466   0.5076   0.0378
   0.500   0.4108   0.01396   0.00793  -0.0466   0.5027   0.0390
   0.750   0.4387   0.01039   0.00388  -0.0460   0.4985   0.0323
   1.000   0.4668   0.00999   0.00340  -0.0460   0.4935   0.0322
   1.250   0.4950   0.00964   0.00302  -0.0461   0.4888   0.0322
   1.500   0.5229   0.00938   0.00272  -0.0461   0.4839   0.0321
   1.750   0.5508   0.00920   0.00249  -0.0462   0.4791   0.0325
   2.000   0.5789   0.00901   0.00232  -0.0462   0.4751   0.0332
   2.250   0.6069   0.00886   0.00215  -0.0463   0.4704   0.0334
   2.500   0.6349   0.00879   0.00204  -0.0464   0.4656   0.0341
   2.750   0.6631   0.00870   0.00196  -0.0466   0.4613   0.0355
   3.000   0.6913   0.00866   0.00191  -0.0467   0.4561   0.0371
   3.250   0.7195   0.00869   0.00190  -0.0469   0.4505   0.0384
   3.500   0.7478   0.00866   0.00190  -0.0471   0.4463   0.0398
   3.750   0.7761   0.00866   0.00191  -0.0473   0.4418   0.0469
   4.000   0.8037   0.00852   0.00206  -0.0475   0.4371   0.1993
   4.250   0.8451   0.00705   0.00232  -0.0510   0.4316   0.9958
   4.500   0.8922   0.00719   0.00242  -0.0556   0.4251   1.0000
   4.750   0.9184   0.00729   0.00249  -0.0554   0.4175   1.0000
   5.000   0.9445   0.00739   0.00256  -0.0552   0.4098   1.0000
   5.250   0.9706   0.00750   0.00266  -0.0550   0.4017   1.0000
   5.500   0.9965   0.00765   0.00276  -0.0548   0.3914   1.0000
   5.750   1.0226   0.00777   0.00286  -0.0547   0.3809   1.0000
   6.000   1.0483   0.00795   0.00301  -0.0545   0.3663   1.0000
   6.250   1.0737   0.00821   0.00318  -0.0543   0.3461   1.0000
   6.500   1.0975   0.00877   0.00349  -0.0541   0.2993   1.0000
   6.750   1.1116   0.01096   0.00482  -0.0532   0.1520   1.0000
   7.000   1.1239   0.01308   0.00630  -0.0519   0.0244   1.0000
   7.250   1.1466   0.01354   0.00679  -0.0513   0.0202   1.0000
   7.500   1.1691   0.01401   0.00730  -0.0507   0.0178   1.0000
   7.750   1.1919   0.01443   0.00774  -0.0502   0.0165   1.0000
   8.000   1.2139   0.01491   0.00826  -0.0496   0.0153   1.0000
   8.250   1.2339   0.01561   0.00901  -0.0488   0.0140   1.0000
   8.500   1.2520   0.01647   0.00997  -0.0477   0.0132   1.0000
   8.750   1.2726   0.01701   0.01055  -0.0471   0.0127   1.0000
   9.000   1.2923   0.01762   0.01119  -0.0463   0.0120   1.0000
   9.250   1.3109   0.01827   0.01189  -0.0455   0.0114   1.0000
   9.500   1.3273   0.01906   0.01272  -0.0444   0.0108   1.0000
   9.750   1.3402   0.02005   0.01377  -0.0430   0.0104   1.0000
  10.000   1.3399   0.02165   0.01547  -0.0402   0.0099   1.0000
  10.250   1.3291   0.02460   0.01857  -0.0380   0.0096   1.0000
  10.500   1.3364   0.02640   0.02044  -0.0375   0.0095   1.0000
  10.750   1.3450   0.02814   0.02226  -0.0371   0.0093   1.0000
  11.000   1.3511   0.03019   0.02439  -0.0367   0.0091   1.0000
  11.250   1.3554   0.03243   0.02670  -0.0363   0.0089   1.0000
  11.500   1.3586   0.03478   0.02914  -0.0359   0.0087   1.0000
  11.750   1.3611   0.03719   0.03162  -0.0354   0.0085   1.0000
  12.000   1.3646   0.03951   0.03400  -0.0350   0.0083   1.0000
  12.250   1.3686   0.04180   0.03635  -0.0347   0.0080   1.0000
  12.500   1.3726   0.04407   0.03867  -0.0344   0.0078   1.0000
  12.750   1.3760   0.04644   0.04110  -0.0341   0.0076   1.0000
  13.000   1.3776   0.04897   0.04368  -0.0338   0.0074   1.0000
  13.250   1.3771   0.05169   0.04645  -0.0334   0.0072   1.0000
  13.500   1.3745   0.05460   0.04943  -0.0328   0.0071   1.0000
  13.750   1.3675   0.05736   0.05224  -0.0305   0.0068   1.0000
  14.000   1.3706   0.05958   0.05455  -0.0295   0.0067   1.0000
  14.250   1.3750   0.06199   0.05705  -0.0294   0.0066   1.0000
  14.500   1.3791   0.06439   0.05953  -0.0291   0.0065   1.0000
  14.750   1.3828   0.06681   0.06204  -0.0288   0.0064   1.0000
  15.000   1.3862   0.06929   0.06462  -0.0284   0.0063   1.0000
  15.250   1.3891   0.07180   0.06723  -0.0279   0.0062   1.0000
  15.500   1.3910   0.07448   0.07003  -0.0275   0.0061   1.0000
  15.750   1.3918   0.07737   0.07304  -0.0271   0.0060   1.0000
  16.000   1.3918   0.08045   0.07624  -0.0270   0.0059   1.0000
  16.250   1.3898   0.08384   0.07977  -0.0269   0.0058   1.0000
  16.500   1.3863   0.08757   0.08363  -0.0271   0.0057   1.0000
  16.750   1.3809   0.09170   0.08791  -0.0277   0.0056   1.0000
  17.000   1.3738   0.09621   0.09257  -0.0286   0.0055   1.0000
  17.250   1.3651   0.10106   0.09757  -0.0298   0.0054   1.0000
  17.500   1.3564   0.10605   0.10270  -0.0313   0.0054   1.0000
  17.750   1.3488   0.11101   0.10777  -0.0333   0.0053   1.0000
  18.000   1.3410   0.11611   0.11298  -0.0354   0.0052   1.0000
  18.250   1.3320   0.12155   0.11854  -0.0377   0.0052   1.0000
  18.500   1.3246   0.12678   0.12387  -0.0402   0.0051   1.0000
  18.750   1.3154   0.13248   0.12968  -0.0430   0.0051   1.0000
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