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N-12 (n12-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-12 (n12-il)
Reynolds number: 100,000
Max Cl/Cd: 38.99 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n12-il-100000.txt
Download as CSV file: xf-n12-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6109   0.09082   0.08562  -0.0134   1.0000   0.1717
  -9.250  -0.7232   0.05225   0.04692  -0.0331   1.0000   0.0900
  -9.000  -0.7988   0.05855   0.05275  -0.0263   1.0000   0.0883
  -8.750  -0.8349   0.05165   0.04498  -0.0206   1.0000   0.0790
  -8.500  -0.8328   0.04784   0.04092  -0.0179   1.0000   0.0784
  -8.250  -0.8291   0.04435   0.03711  -0.0151   1.0000   0.0778
  -8.000  -0.8226   0.04092   0.03333  -0.0122   1.0000   0.0768
  -7.750  -0.8140   0.03761   0.02962  -0.0094   1.0000   0.0755
  -7.500  -0.8023   0.03460   0.02618  -0.0067   1.0000   0.0746
  -7.250  -0.7870   0.03230   0.02350  -0.0045   1.0000   0.0754
  -7.000  -0.7697   0.03035   0.02123  -0.0024   1.0000   0.0769
  -6.750  -0.7497   0.02842   0.01900  -0.0007   1.0000   0.0780
  -6.500  -0.7273   0.02663   0.01699   0.0006   1.0000   0.0787
  -6.250  -0.7043   0.02517   0.01532   0.0018   1.0000   0.0800
  -6.000  -0.6824   0.02373   0.01398   0.0029   1.0000   0.0832
  -5.750  -0.6614   0.02271   0.01297   0.0043   1.0000   0.0867
  -5.500  -0.6406   0.02168   0.01190   0.0059   1.0000   0.0895
  -5.250  -0.6213   0.02076   0.01093   0.0077   1.0000   0.0928
  -5.000  -0.6051   0.01985   0.01011   0.0099   1.0000   0.0976
  -4.750  -0.5877   0.01919   0.00942   0.0121   1.0000   0.1061
  -4.500  -0.5726   0.01838   0.00869   0.0145   1.0000   0.1193
  -4.250  -0.5594   0.01733   0.00788   0.0172   1.0000   0.1496
  -4.000  -0.5499   0.01593   0.00717   0.0203   1.0000   0.2407
  -3.750  -0.5397   0.01504   0.00695   0.0234   1.0000   0.3811
  -3.500  -0.5258   0.01452   0.00673   0.0262   1.0000   0.4546
  -3.250  -0.5121   0.01402   0.00663   0.0291   1.0000   0.5288
  -3.000  -0.4971   0.01365   0.00669   0.0321   1.0000   0.6180
  -2.750  -0.4780   0.01347   0.00677   0.0344   1.0000   0.6956
  -2.500  -0.4525   0.01348   0.00699   0.0358   1.0000   0.7679
  -2.250  -0.4234   0.01366   0.00724   0.0364   1.0000   0.8272
  -2.000  -0.3815   0.01405   0.00760   0.0348   1.0000   0.8811
  -1.750  -0.2796   0.01543   0.00881   0.0232   1.0000   0.9315
  -1.500  -0.1891   0.01620   0.00936   0.0123   1.0000   0.9540
  -1.250  -0.1123   0.01646   0.00945   0.0029   1.0000   0.9735
  -1.000  -0.0360   0.01632   0.00920  -0.0069   1.0000   0.9897
  -0.750   0.0175   0.01603   0.00885  -0.0130   1.0000   1.0000
  -0.500   0.0174   0.01590   0.00874  -0.0093   1.0000   1.0000
  -0.250   0.0127   0.01587   0.00872  -0.0049   1.0000   1.0000
   0.000   0.0054   0.01591   0.00876  -0.0001   1.0000   1.0000
   0.250  -0.0025   0.01601   0.00886   0.0047   1.0000   1.0000
   0.500   0.0239   0.01617   0.00904   0.0034   0.9946   1.0000
   0.750   0.0867   0.01623   0.00913  -0.0041   0.9814   1.0000
   1.000   0.1458   0.01611   0.00908  -0.0107   0.9658   1.0000
   1.250   0.2091   0.01580   0.00887  -0.0177   0.9487   1.0000
   1.500   0.2760   0.01527   0.00848  -0.0249   0.9319   1.0000
   1.750   0.3399   0.01473   0.00807  -0.0314   0.9105   1.0000
   2.000   0.4032   0.01421   0.00768  -0.0376   0.8829   1.0000
   2.250   0.4503   0.01392   0.00744  -0.0407   0.8434   1.0000
   2.500   0.4832   0.01377   0.00728  -0.0408   0.7948   1.0000
   2.750   0.5061   0.01374   0.00715  -0.0390   0.7373   1.0000
   3.000   0.5253   0.01382   0.00698  -0.0364   0.6711   1.0000
   3.250   0.5414   0.01406   0.00692  -0.0334   0.6020   1.0000
   3.500   0.5571   0.01439   0.00698  -0.0307   0.5440   1.0000
   3.750   0.5725   0.01472   0.00712  -0.0281   0.4918   1.0000
   4.000   0.5875   0.01507   0.00726  -0.0255   0.4422   1.0000
   4.250   0.6024   0.01545   0.00746  -0.0229   0.3957   1.0000
   4.500   0.6159   0.01593   0.00773  -0.0202   0.3407   1.0000
   4.750   0.6245   0.01685   0.00816  -0.0166   0.2298   1.0000
   5.000   0.6310   0.01846   0.00891  -0.0128   0.1345   1.0000
   5.250   0.6424   0.01971   0.01000  -0.0097   0.1183   1.0000
   5.500   0.6560   0.02098   0.01116  -0.0071   0.1081   1.0000
   5.750   0.6739   0.02207   0.01221  -0.0052   0.1010   1.0000
   6.000   0.6950   0.02368   0.01370  -0.0039   0.0962   1.0000
   6.250   0.7164   0.02471   0.01489  -0.0024   0.0920   1.0000
   6.500   0.7372   0.02592   0.01614  -0.0010   0.0868   1.0000
   6.750   0.7618   0.02825   0.01835  -0.0006   0.0835   1.0000
   7.000   0.7813   0.02960   0.02004   0.0013   0.0819   1.0000
   7.250   0.7991   0.03106   0.02185   0.0034   0.0793   1.0000
   7.500   0.8159   0.03274   0.02379   0.0055   0.0767   1.0000
   7.750   0.8314   0.03489   0.02626   0.0077   0.0757   1.0000
   8.000   0.8441   0.03731   0.02903   0.0102   0.0751   1.0000
   8.250   0.8575   0.03963   0.03154   0.0123   0.0735   1.0000
   8.500   0.8706   0.04265   0.03466   0.0139   0.0717   1.0000
   8.750   0.8771   0.04587   0.03821   0.0167   0.0716   1.0000
   9.000   0.8610   0.04926   0.04254   0.0227   0.0749   1.0000
   9.250   0.8475   0.05385   0.04760   0.0268   0.0782   1.0000
   9.500   0.8395   0.05828   0.05227   0.0296   0.0808   1.0000
   9.750   0.7922   0.06447   0.05899   0.0343   0.0896   1.0000
  10.000   0.4913   0.09398   0.08892   0.0143   0.1975   1.0000
  10.250   0.5860   0.07454   0.06955   0.0313   0.1033   1.0000
  10.500   0.6061   0.07352   0.06852   0.0352   0.0943   1.0000
  10.750   0.6117   0.10990   0.10452   0.0094   0.1681   1.0000
  11.000   0.5962   0.11450   0.10904   0.0064   0.1614   1.0000
  11.250   0.6236   0.11674   0.11134   0.0098   0.1537   1.0000
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