Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

N-12 (n12-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-12 (n12-il)
Reynolds number: 100,000
Max Cl/Cd: 36.11 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n12-il-100000-n5.txt
Download as CSV file: xf-n12-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7561   0.07847   0.07287  -0.0354   1.0000   0.0320
 -11.750  -0.7982   0.06986   0.06401  -0.0417   1.0000   0.0313
 -11.500  -0.8221   0.06523   0.05917  -0.0428   1.0000   0.0312
 -11.250  -0.8426   0.06155   0.05530  -0.0421   1.0000   0.0311
 -11.000  -0.8598   0.05820   0.05180  -0.0399   1.0000   0.0314
 -10.750  -0.8752   0.05550   0.04891  -0.0366   1.0000   0.0315
 -10.500  -0.8844   0.05282   0.04607  -0.0335   1.0000   0.0319
 -10.250  -0.8877   0.05032   0.04340  -0.0309   1.0000   0.0326
 -10.000  -0.8856   0.04816   0.04112  -0.0285   1.0000   0.0336
  -9.750  -0.8847   0.04591   0.03866  -0.0258   1.0000   0.0346
  -9.500  -0.8833   0.04347   0.03592  -0.0229   1.0000   0.0355
  -9.250  -0.8793   0.04104   0.03315  -0.0201   1.0000   0.0363
  -9.000  -0.8719   0.03875   0.03052  -0.0175   1.0000   0.0369
  -8.750  -0.8620   0.03681   0.02822  -0.0150   1.0000   0.0381
  -8.500  -0.8502   0.03528   0.02632  -0.0126   1.0000   0.0394
  -8.250  -0.8361   0.03341   0.02415  -0.0106   1.0000   0.0405
  -8.000  -0.8183   0.03107   0.02164  -0.0093   1.0000   0.0415
  -7.750  -0.8000   0.02936   0.01985  -0.0080   1.0000   0.0427
  -7.500  -0.7820   0.02800   0.01842  -0.0065   1.0000   0.0446
  -7.250  -0.7635   0.02679   0.01710  -0.0050   1.0000   0.0464
  -7.000  -0.7445   0.02564   0.01584  -0.0034   1.0000   0.0475
  -6.750  -0.7260   0.02459   0.01469  -0.0018   1.0000   0.0485
  -6.500  -0.7080   0.02365   0.01364   0.0000   1.0000   0.0494
  -6.250  -0.6902   0.02287   0.01274   0.0018   1.0000   0.0510
  -6.000  -0.6752   0.02188   0.01175   0.0040   1.0000   0.0527
  -5.750  -0.6597   0.02104   0.01088   0.0062   1.0000   0.0545
  -5.500  -0.6432   0.02036   0.01013   0.0082   1.0000   0.0560
  -5.250  -0.6260   0.01976   0.00943   0.0102   1.0000   0.0575
  -5.000  -0.6083   0.01922   0.00882   0.0121   1.0000   0.0593
  -4.750  -0.5905   0.01873   0.00825   0.0139   1.0000   0.0617
  -4.500  -0.5728   0.01822   0.00777   0.0158   1.0000   0.0658
  -4.250  -0.5557   0.01768   0.00737   0.0177   1.0000   0.0765
  -4.000  -0.5381   0.01721   0.00704   0.0195   1.0000   0.1147
  -3.750  -0.5206   0.01677   0.00671   0.0213   1.0000   0.1436
  -3.500  -0.5034   0.01632   0.00641   0.0231   1.0000   0.1761
  -3.250  -0.4862   0.01591   0.00615   0.0249   1.0000   0.2124
  -3.000  -0.4706   0.01540   0.00600   0.0269   1.0000   0.2788
  -2.750  -0.4549   0.01499   0.00592   0.0289   1.0000   0.3628
  -2.500  -0.4287   0.01478   0.00580   0.0289   0.9971   0.4058
  -2.250  -0.3943   0.01449   0.00570   0.0272   0.9903   0.4558
  -2.000  -0.3639   0.01388   0.00580   0.0265   0.9836   0.5794
  -1.750  -0.3305   0.01357   0.00599   0.0258   0.9772   0.6982
  -1.500  -0.2895   0.01356   0.00629   0.0240   0.9727   0.7863
  -1.250  -0.2460   0.01373   0.00658   0.0216   0.9677   0.8518
  -1.000  -0.1965   0.01392   0.00676   0.0177   0.9635   0.8839
  -0.750  -0.1447   0.01403   0.00684   0.0133   0.9544   0.9058
  -0.500  -0.0891   0.01405   0.00681   0.0081   0.9417   0.9199
  -0.250  -0.0306   0.01397   0.00667   0.0023   0.9271   0.9266
   0.000   0.0223   0.01387   0.00653  -0.0024   0.9113   0.9335
   0.250   0.0754   0.01381   0.00643  -0.0074   0.8968   0.9381
   0.500   0.1248   0.01375   0.00636  -0.0116   0.8816   0.9435
   0.750   0.1709   0.01370   0.00629  -0.0152   0.8626   0.9499
   1.000   0.2198   0.01366   0.00623  -0.0192   0.8355   0.9555
   1.250   0.2636   0.01367   0.00620  -0.0221   0.8018   0.9636
   1.500   0.3064   0.01367   0.00615  -0.0249   0.7621   0.9705
   1.750   0.3463   0.01371   0.00610  -0.0271   0.7172   0.9774
   2.000   0.3843   0.01380   0.00607  -0.0290   0.6710   0.9847
   2.250   0.4240   0.01388   0.00600  -0.0313   0.6199   0.9911
   2.500   0.4615   0.01403   0.00598  -0.0333   0.5676   0.9980
   2.750   0.4852   0.01426   0.00601  -0.0326   0.5125   1.0000
   3.000   0.5015   0.01456   0.00606  -0.0304   0.4535   1.0000
   3.250   0.5174   0.01491   0.00616  -0.0282   0.4000   1.0000
   3.500   0.5334   0.01529   0.00630  -0.0261   0.3546   1.0000
   3.750   0.5505   0.01563   0.00650  -0.0242   0.3210   1.0000
   4.000   0.5678   0.01597   0.00674  -0.0224   0.2909   1.0000
   4.250   0.5852   0.01631   0.00702  -0.0205   0.2577   1.0000
   4.500   0.6026   0.01669   0.00732  -0.0187   0.2194   1.0000
   4.750   0.6161   0.01748   0.00763  -0.0164   0.1327   1.0000
   5.000   0.6294   0.01845   0.00835  -0.0140   0.1043   1.0000
   5.250   0.6456   0.01911   0.00906  -0.0119   0.0864   1.0000
   5.500   0.6621   0.01974   0.00970  -0.0098   0.0770   1.0000
   5.750   0.6787   0.02034   0.01036  -0.0078   0.0708   1.0000
   6.000   0.6942   0.02106   0.01106  -0.0056   0.0669   1.0000
   6.250   0.7102   0.02175   0.01186  -0.0034   0.0636   1.0000
   6.500   0.7263   0.02245   0.01264  -0.0014   0.0601   1.0000
   6.750   0.7414   0.02325   0.01343   0.0007   0.0570   1.0000
   7.000   0.7562   0.02425   0.01445   0.0030   0.0549   1.0000
   7.250   0.7729   0.02522   0.01555   0.0050   0.0532   1.0000
   7.500   0.7900   0.02625   0.01668   0.0068   0.0509   1.0000
   7.750   0.8068   0.02726   0.01775   0.0085   0.0482   1.0000
   8.000   0.8234   0.02846   0.01898   0.0102   0.0461   1.0000
   8.250   0.8410   0.03029   0.02085   0.0116   0.0444   1.0000
   8.500   0.8577   0.03163   0.02248   0.0134   0.0426   1.0000
   8.750   0.8727   0.03307   0.02417   0.0153   0.0403   1.0000
   9.000   0.8870   0.03479   0.02612   0.0173   0.0388   1.0000
   9.250   0.8991   0.03658   0.02812   0.0193   0.0375   1.0000
   9.500   0.9100   0.03830   0.02998   0.0213   0.0360   1.0000
   9.750   0.9184   0.04097   0.03275   0.0232   0.0346   1.0000
  10.000   0.9194   0.04296   0.03517   0.0266   0.0335   1.0000
  10.250   0.9179   0.04546   0.03806   0.0298   0.0328   1.0000
  10.500   0.9115   0.04823   0.04118   0.0333   0.0322   1.0000
  10.750   0.8996   0.05102   0.04427   0.0370   0.0318   1.0000
  11.000   0.8832   0.05373   0.04722   0.0408   0.0315   1.0000
  11.250   0.8654   0.05678   0.05050   0.0433   0.0312   1.0000
  11.500   0.8439   0.06071   0.05464   0.0443   0.0313   1.0000
  11.750   0.8209   0.06538   0.05950   0.0434   0.0314   1.0000
  12.000   0.7954   0.07135   0.06566   0.0403   0.0317   1.0000
  12.250   0.7653   0.07953   0.07398   0.0347   0.0321   1.0000
  12.500   0.7308   0.09072   0.08526   0.0266   0.0326   1.0000
<< Back to N-12 (n12-il)

Polar data table (+)

Polar graphs


<< Back to N-12 (n12-il)