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N-12 (n12-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: N-12 (n12-il)
Reynolds number: 500,000
Max Cl/Cd: 53.28 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n12-il-500000.txt
Download as CSV file: xf-n12-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-12                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7156   0.08568   0.08325  -0.0242   1.0000   0.0276
 -11.750  -0.9603   0.04772   0.04389  -0.0407   1.0000   0.0186
 -11.250  -0.9856   0.04345   0.03933  -0.0323   1.0000   0.0188
 -11.000  -0.9542   0.04422   0.04038  -0.0331   1.0000   0.0196
 -10.750  -0.9583   0.04234   0.03836  -0.0295   1.0000   0.0198
 -10.500  -0.9638   0.03993   0.03574  -0.0257   1.0000   0.0200
 -10.250  -0.9626   0.03807   0.03370  -0.0225   1.0000   0.0204
 -10.000  -0.9613   0.03593   0.03133  -0.0191   1.0000   0.0208
  -9.750  -0.9569   0.03409   0.02924  -0.0158   1.0000   0.0214
  -9.500  -0.9503   0.03252   0.02739  -0.0126   1.0000   0.0221
  -9.250  -0.9397   0.03223   0.02684  -0.0096   1.0000   0.0229
  -9.000  -0.9362   0.02903   0.02328  -0.0062   1.0000   0.0236
  -8.750  -0.9216   0.02694   0.02109  -0.0045   1.0000   0.0242
  -8.500  -0.9036   0.02581   0.01997  -0.0031   1.0000   0.0250
  -8.250  -0.8864   0.02474   0.01883  -0.0014   1.0000   0.0257
  -8.000  -0.8691   0.02377   0.01775   0.0003   1.0000   0.0266
  -7.750  -0.8514   0.02298   0.01683   0.0022   1.0000   0.0276
  -7.500  -0.8332   0.02232   0.01604   0.0040   1.0000   0.0285
  -7.250  -0.8151   0.02195   0.01553   0.0060   1.0000   0.0291
  -7.000  -0.7969   0.02062   0.01404   0.0077   1.0000   0.0297
  -6.750  -0.7772   0.01844   0.01184   0.0089   1.0000   0.0307
  -6.500  -0.7586   0.01753   0.01094   0.0105   1.0000   0.0318
  -6.250  -0.7404   0.01683   0.01023   0.0123   1.0000   0.0328
  -6.000  -0.7227   0.01616   0.00954   0.0142   1.0000   0.0334
  -5.750  -0.7058   0.01556   0.00891   0.0163   1.0000   0.0341
  -5.500  -0.6896   0.01506   0.00837   0.0185   1.0000   0.0348
  -5.250  -0.6736   0.01464   0.00792   0.0207   1.0000   0.0356
  -5.000  -0.6393   0.01416   0.00741   0.0191   0.9977   0.0365
  -4.750  -0.6040   0.01370   0.00690   0.0174   0.9949   0.0370
  -4.500  -0.5717   0.01303   0.00620   0.0162   0.9917   0.0377
  -4.250  -0.5400   0.01231   0.00545   0.0151   0.9879   0.0393
  -4.000  -0.5050   0.01183   0.00495   0.0134   0.9850   0.0409
  -3.750  -0.4715   0.01145   0.00455   0.0121   0.9810   0.0421
  -3.500  -0.4377   0.01111   0.00418   0.0108   0.9763   0.0436
  -3.250  -0.3996   0.01079   0.00383   0.0086   0.9729   0.0454
  -3.000  -0.3668   0.01049   0.00351   0.0076   0.9658   0.0473
  -2.500  -0.3013   0.00953   0.00290   0.0055   0.9526   0.1228
  -2.250  -0.2692   0.00887   0.00257   0.0044   0.9463   0.1929
  -2.000  -0.2438   0.00793   0.00230   0.0046   0.9365   0.3582
  -1.750  -0.2038   0.00750   0.00209   0.0019   0.9294   0.4167
  -1.500  -0.1613   0.00697   0.00186  -0.0015   0.9180   0.4895
  -1.250  -0.1294   0.00626   0.00174  -0.0025   0.9036   0.6391
  -1.000  -0.0988   0.00601   0.00169  -0.0029   0.8887   0.7085
  -0.750  -0.0712   0.00587   0.00170  -0.0025   0.8739   0.7558
  -0.500  -0.0444   0.00582   0.00172  -0.0020   0.8582   0.7916
  -0.250  -0.0185   0.00581   0.00177  -0.0011   0.8404   0.8259
   0.000   0.0057   0.00583   0.00180   0.0001   0.8208   0.8539
   0.250   0.0326   0.00586   0.00182   0.0007   0.7978   0.8738
   0.500   0.0599   0.00591   0.00182   0.0011   0.7713   0.8883
   0.750   0.0871   0.00598   0.00182   0.0015   0.7427   0.9004
   1.000   0.1196   0.00610   0.00187   0.0008   0.7105   0.9123
   1.250   0.1554   0.00633   0.00195  -0.0007   0.6676   0.9217
   1.500   0.1854   0.00660   0.00203  -0.0010   0.6177   0.9308
   1.750   0.2218   0.00697   0.00217  -0.0028   0.5603   0.9365
   2.000   0.2521   0.00731   0.00231  -0.0032   0.5066   0.9448
   2.250   0.2892   0.00780   0.00253  -0.0052   0.4362   0.9491
   2.500   0.3185   0.00828   0.00272  -0.0056   0.3669   0.9546
   2.750   0.3486   0.00869   0.00292  -0.0062   0.3198   0.9597
   3.000   0.3845   0.00900   0.00312  -0.0080   0.2912   0.9626
   3.250   0.4177   0.00929   0.00331  -0.0093   0.2665   0.9671
   3.500   0.4469   0.00958   0.00349  -0.0096   0.2397   0.9722
   3.750   0.4825   0.00989   0.00366  -0.0115   0.1985   0.9746
   4.000   0.5125   0.01070   0.00403  -0.0124   0.1040   0.9788
   4.250   0.5405   0.01126   0.00436  -0.0127   0.0596   0.9838
   4.500   0.5759   0.01168   0.00471  -0.0145   0.0495   0.9860
   4.750   0.6117   0.01201   0.00507  -0.0163   0.0464   0.9890
   5.000   0.6451   0.01238   0.00549  -0.0176   0.0437   0.9924
   5.250   0.6783   0.01287   0.00599  -0.0190   0.0412   0.9953
   5.500   0.7123   0.01355   0.00673  -0.0206   0.0389   0.9984
   5.750   0.7416   0.01392   0.00715  -0.0212   0.0377   1.0000
   6.000   0.7573   0.01430   0.00758  -0.0189   0.0366   1.0000
   6.250   0.7726   0.01470   0.00802  -0.0165   0.0355   1.0000
   6.500   0.7876   0.01515   0.00849  -0.0141   0.0342   1.0000
   6.750   0.8015   0.01574   0.00910  -0.0116   0.0328   1.0000
   7.000   0.8117   0.01702   0.01041  -0.0085   0.0314   1.0000
   7.250   0.8280   0.01769   0.01116  -0.0063   0.0307   1.0000
   7.500   0.8458   0.01816   0.01170  -0.0044   0.0299   1.0000
   7.750   0.8636   0.01865   0.01225  -0.0025   0.0287   1.0000
   8.000   0.8810   0.01923   0.01288  -0.0007   0.0275   1.0000
   8.250   0.8980   0.01988   0.01356   0.0012   0.0265   1.0000
   8.500   0.9144   0.02077   0.01447   0.0031   0.0257   1.0000
   8.750   0.9284   0.02327   0.01706   0.0050   0.0246   1.0000
   9.000   0.9450   0.02355   0.01748   0.0071   0.0239   1.0000
   9.250   0.9610   0.02422   0.01829   0.0092   0.0231   1.0000
   9.500   0.9764   0.02501   0.01919   0.0112   0.0222   1.0000
   9.750   0.9916   0.02576   0.02001   0.0132   0.0214   1.0000
  10.000   1.0058   0.02655   0.02087   0.0152   0.0208   1.0000
  10.250   1.0192   0.02748   0.02184   0.0172   0.0202   1.0000
  10.500   1.0267   0.03030   0.02482   0.0196   0.0195   1.0000
  10.750   1.0320   0.03170   0.02646   0.0228   0.0192   1.0000
  11.000   1.0370   0.03297   0.02797   0.0260   0.0187   1.0000
  11.250   1.0382   0.03459   0.02983   0.0296   0.0182   1.0000
  11.500   1.0348   0.03640   0.03185   0.0336   0.0178   1.0000
  11.750   1.0263   0.03823   0.03386   0.0381   0.0175   1.0000
  12.000   1.0258   0.03927   0.03500   0.0411   0.0171   1.0000
  12.250   1.0186   0.04126   0.03714   0.0441   0.0169   1.0000
  12.500   1.0246   0.04197   0.03787   0.0455   0.0164   1.0000
  12.750   1.0148   0.04459   0.04066   0.0472   0.0163   1.0000
  13.000   1.0020   0.04780   0.04404   0.0479   0.0162   1.0000
  13.250   0.9912   0.05113   0.04751   0.0477   0.0161   1.0000
  13.500   0.9769   0.05537   0.05191   0.0463   0.0160   1.0000
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