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NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 23112 (naca23112-jf)
Reynolds number: 500,000
Max Cl/Cd: 78.21 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca23112-jf-500000-n5.txt
Download as CSV file: xf-naca23112-jf-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23112                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.9326   0.08024   0.07756  -0.0137   1.0000   0.0137
 -14.250  -1.0306   0.05587   0.05265  -0.0326   1.0000   0.0135
 -14.000  -1.0635   0.04843   0.04489  -0.0360   1.0000   0.0135
 -13.750  -1.0856   0.04340   0.03957  -0.0364   1.0000   0.0136
 -13.500  -1.0995   0.03974   0.03562  -0.0351   1.0000   0.0137
 -13.250  -1.1073   0.03694   0.03258  -0.0331   1.0000   0.0138
 -13.000  -1.1097   0.03488   0.03037  -0.0306   1.0000   0.0139
 -12.750  -1.1068   0.03336   0.02873  -0.0281   1.0000   0.0140
 -12.500  -1.0993   0.03208   0.02735  -0.0259   1.0000   0.0142
 -12.250  -1.0874   0.03093   0.02610  -0.0243   1.0000   0.0143
 -12.000  -1.0737   0.02983   0.02490  -0.0227   1.0000   0.0145
 -11.750  -1.0589   0.02874   0.02370  -0.0213   1.0000   0.0147
 -11.500  -1.0431   0.02767   0.02250  -0.0199   1.0000   0.0149
 -11.250  -1.0266   0.02656   0.02127  -0.0185   1.0000   0.0152
 -11.000  -1.0093   0.02546   0.02002  -0.0172   1.0000   0.0154
 -10.750  -0.9912   0.02439   0.01880  -0.0160   1.0000   0.0158
 -10.500  -0.9722   0.02338   0.01763  -0.0148   1.0000   0.0161
 -10.250  -0.9525   0.02242   0.01652  -0.0136   1.0000   0.0165
 -10.000  -0.9324   0.02153   0.01549  -0.0125   1.0000   0.0168
  -9.750  -0.9123   0.02073   0.01464  -0.0113   1.0000   0.0172
  -9.500  -0.8909   0.02011   0.01398  -0.0103   1.0000   0.0175
  -9.250  -0.8693   0.01953   0.01336  -0.0093   1.0000   0.0178
  -9.000  -0.8477   0.01895   0.01273  -0.0082   1.0000   0.0182
  -8.750  -0.8263   0.01837   0.01209  -0.0071   1.0000   0.0186
  -8.500  -0.8053   0.01778   0.01143  -0.0058   1.0000   0.0190
  -8.250  -0.7845   0.01721   0.01078  -0.0045   1.0000   0.0195
  -8.000  -0.7639   0.01668   0.01017  -0.0031   1.0000   0.0199
  -7.750  -0.7438   0.01614   0.00959  -0.0016   1.0000   0.0204
  -7.500  -0.7235   0.01571   0.00916  -0.0001   1.0000   0.0209
  -7.250  -0.6958   0.01532   0.00877  -0.0002   0.9981   0.0216
  -7.000  -0.6620   0.01487   0.00829  -0.0016   0.9945   0.0224
  -6.750  -0.6295   0.01438   0.00775  -0.0027   0.9899   0.0232
  -6.500  -0.5963   0.01393   0.00724  -0.0038   0.9846   0.0239
  -6.250  -0.5654   0.01342   0.00674  -0.0046   0.9774   0.0248
  -6.000  -0.5321   0.01306   0.00638  -0.0057   0.9702   0.0258
  -5.750  -0.5014   0.01273   0.00604  -0.0063   0.9595   0.0270
  -5.500  -0.4709   0.01241   0.00567  -0.0067   0.9469   0.0282
  -5.250  -0.4423   0.01203   0.00527  -0.0068   0.9313   0.0293
  -5.000  -0.4150   0.01175   0.00497  -0.0065   0.9119   0.0305
  -4.750  -0.3892   0.01152   0.00467  -0.0057   0.8880   0.0319
  -4.500  -0.3646   0.01137   0.00438  -0.0047   0.8543   0.0334
  -4.250  -0.3404   0.01119   0.00409  -0.0037   0.8166   0.0351
  -4.000  -0.3152   0.01107   0.00386  -0.0029   0.7836   0.0370
  -3.750  -0.2894   0.01097   0.00362  -0.0023   0.7557   0.0389
  -3.500  -0.2635   0.01083   0.00339  -0.0018   0.7276   0.0413
  -3.250  -0.2371   0.01074   0.00321  -0.0013   0.7021   0.0442
  -3.000  -0.2106   0.01066   0.00303  -0.0009   0.6764   0.0469
  -2.750  -0.1842   0.01056   0.00286  -0.0005   0.6498   0.0507
  -2.500  -0.1575   0.01053   0.00271  -0.0001   0.6234   0.0548
  -2.250  -0.1307   0.01043   0.00257   0.0002   0.5996   0.0605
  -2.000  -0.1038   0.01039   0.00245   0.0005   0.5751   0.0667
  -1.750  -0.0769   0.01034   0.00234   0.0008   0.5498   0.0759
  -1.500  -0.0502   0.01029   0.00223   0.0011   0.5246   0.0891
  -1.250  -0.0236   0.01017   0.00213   0.0014   0.5027   0.1171
  -1.000  -0.0045   0.00901   0.00185   0.0024   0.4825   0.3913
  -0.750   0.0183   0.00854   0.00176   0.0033   0.4601   0.5188
  -0.500   0.0423   0.00828   0.00173   0.0041   0.4378   0.6037
  -0.250   0.0665   0.00810   0.00173   0.0049   0.4168   0.6764
   0.000   0.0912   0.00798   0.00175   0.0057   0.3977   0.7338
   0.250   0.1165   0.00795   0.00180   0.0065   0.3782   0.7795
   0.500   0.1419   0.00797   0.00187   0.0073   0.3590   0.8214
   0.750   0.1678   0.00804   0.00195   0.0080   0.3413   0.8552
   1.000   0.1939   0.00813   0.00206   0.0087   0.3262   0.8873
   1.250   0.2212   0.00826   0.00215   0.0091   0.3125   0.9055
   1.500   0.2494   0.00839   0.00223   0.0092   0.2993   0.9157
   1.750   0.2773   0.00854   0.00231   0.0093   0.2874   0.9259
   2.250   0.3353   0.00882   0.00249   0.0090   0.2687   0.9423
   2.500   0.3660   0.00899   0.00260   0.0085   0.2600   0.9487
   2.750   0.3944   0.00912   0.00270   0.0085   0.2523   0.9564
   3.000   0.4269   0.00931   0.00282   0.0075   0.2452   0.9607
   3.250   0.4580   0.00944   0.00294   0.0069   0.2397   0.9661
   3.500   0.4883   0.00960   0.00306   0.0063   0.2333   0.9713
   3.750   0.5220   0.00978   0.00319   0.0051   0.2276   0.9743
   4.000   0.5551   0.00992   0.00333   0.0039   0.2226   0.9777
   4.250   0.5866   0.01010   0.00347   0.0031   0.2172   0.9816
   4.500   0.6198   0.01028   0.00363   0.0018   0.2122   0.9841
   4.750   0.6543   0.01043   0.00378   0.0003   0.2075   0.9862
   5.000   0.6877   0.01060   0.00394  -0.0010   0.2025   0.9886
   5.250   0.7201   0.01080   0.00412  -0.0021   0.1977   0.9913
   5.500   0.7521   0.01096   0.00429  -0.0031   0.1935   0.9939
   5.750   0.7857   0.01114   0.00446  -0.0045   0.1884   0.9956
   6.000   0.8185   0.01136   0.00466  -0.0057   0.1835   0.9976
   6.250   0.8513   0.01152   0.00486  -0.0070   0.1793   0.9994
   6.500   0.8775   0.01171   0.00504  -0.0068   0.1745   1.0000
   6.750   0.8998   0.01193   0.00525  -0.0058   0.1701   1.0000
   7.000   0.9227   0.01210   0.00545  -0.0049   0.1663   1.0000
   7.250   0.9453   0.01230   0.00566  -0.0040   0.1616   1.0000
   7.500   0.9675   0.01255   0.00590  -0.0030   0.1567   1.0000
   7.750   0.9902   0.01276   0.00614  -0.0021   0.1524   1.0000
   8.000   1.0127   0.01299   0.00638  -0.0012   0.1471   1.0000
   8.250   1.0347   0.01329   0.00666  -0.0003   0.1417   1.0000
   8.500   1.0574   0.01352   0.00693   0.0006   0.1366   1.0000
   8.750   1.0793   0.01384   0.00723   0.0015   0.1305   1.0000
   9.000   1.1016   0.01412   0.00754   0.0024   0.1250   1.0000
   9.250   1.1234   0.01447   0.00788   0.0033   0.1186   1.0000
   9.500   1.1454   0.01481   0.00824   0.0041   0.1128   1.0000
   9.750   1.1670   0.01521   0.00863   0.0050   0.1060   1.0000
  10.000   1.1889   0.01560   0.00904   0.0058   0.0998   1.0000
  10.500   1.2312   0.01653   0.00997   0.0074   0.0864   1.0000
  10.750   1.2515   0.01707   0.01050   0.0083   0.0799   1.0000
  11.000   1.2713   0.01763   0.01107   0.0092   0.0731   1.0000
  11.250   1.2910   0.01821   0.01166   0.0102   0.0671   1.0000
  11.500   1.3093   0.01888   0.01233   0.0112   0.0612   1.0000
  11.750   1.3273   0.01954   0.01301   0.0123   0.0558   1.0000
  12.000   1.3445   0.02024   0.01374   0.0135   0.0512   1.0000
  12.250   1.3600   0.02103   0.01455   0.0148   0.0467   1.0000
  12.500   1.3753   0.02178   0.01534   0.0161   0.0431   1.0000
  12.750   1.3866   0.02266   0.01625   0.0179   0.0397   1.0000
  13.000   1.3973   0.02350   0.01716   0.0198   0.0372   1.0000
  13.250   1.4063   0.02450   0.01821   0.0217   0.0347   1.0000
  13.500   1.4139   0.02566   0.01943   0.0234   0.0327   1.0000
  13.750   1.4219   0.02688   0.02073   0.0247   0.0308   1.0000
  14.000   1.4272   0.02840   0.02232   0.0259   0.0291   1.0000
  14.250   1.4311   0.03017   0.02417   0.0268   0.0277   1.0000
  14.500   1.4353   0.03207   0.02619   0.0272   0.0265   1.0000
  14.750   1.4370   0.03441   0.02863   0.0272   0.0253   1.0000
  15.000   1.4357   0.03729   0.03161   0.0267   0.0244   1.0000
  15.500   1.4267   0.04458   0.03915   0.0241   0.0230   1.0000
  15.750   1.4188   0.04900   0.04371   0.0221   0.0225   1.0000
  16.000   1.4063   0.05420   0.04906   0.0197   0.0220   1.0000
  16.250   1.3893   0.06019   0.05520   0.0169   0.0217   1.0000
  16.500   1.3678   0.06689   0.06206   0.0138   0.0215   1.0000
  16.750   1.3432   0.07412   0.06944   0.0106   0.0214   1.0000
  17.000   1.3168   0.08168   0.07714   0.0072   0.0213   1.0000
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