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

N-22 (n22-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 100,000
Max Cl/Cd: 54.14 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n22-il-100000-n5.txt
Download as CSV file: xf-n22-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-22                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3702   0.09205   0.08684  -0.0446   0.9999   0.0536
 -11.000  -0.3773   0.08848   0.08334  -0.0451   0.9999   0.0533
 -10.750  -0.3892   0.08509   0.08004  -0.0451   0.9999   0.0531
 -10.500  -0.4078   0.08205   0.07711  -0.0441   0.9999   0.0531
 -10.250  -0.4331   0.07950   0.07468  -0.0421   0.9999   0.0529
 -10.000  -0.4507   0.07442   0.06966  -0.0451   0.9977   0.0530
  -9.750  -0.4511   0.05877   0.05365  -0.0639   0.9853   0.0536
  -9.500  -0.4460   0.04778   0.04199  -0.0733   0.9751   0.0539
  -9.250  -0.4304   0.04070   0.03410  -0.0781   0.9670   0.0545
  -9.000  -0.4042   0.03711   0.03008  -0.0808   0.9610   0.0557
  -8.750  -0.3740   0.03553   0.02839  -0.0826   0.9556   0.0571
  -8.500  -0.3453   0.03363   0.02623  -0.0840   0.9489   0.0586
  -8.250  -0.3122   0.03118   0.02336  -0.0863   0.9447   0.0599
  -8.000  -0.2854   0.02923   0.02102  -0.0869   0.9370   0.0611
  -7.750  -0.2535   0.02743   0.01883  -0.0882   0.9313   0.0627
  -7.500  -0.2203   0.02598   0.01697  -0.0894   0.9262   0.0649
  -7.250  -0.1928   0.02500   0.01599  -0.0896   0.9179   0.0668
  -7.000  -0.1589   0.02403   0.01491  -0.0909   0.9129   0.0689
  -6.750  -0.1311   0.02316   0.01390  -0.0908   0.9045   0.0710
  -6.500  -0.0989   0.02224   0.01281  -0.0915   0.8983   0.0736
  -6.250  -0.0696   0.02147   0.01195  -0.0916   0.8907   0.0768
  -6.000  -0.0397   0.02089   0.01139  -0.0920   0.8832   0.0809
  -5.750  -0.0100   0.02030   0.01071  -0.0921   0.8757   0.0858
  -5.500   0.0189   0.01967   0.01007  -0.0921   0.8675   0.0905
  -5.250   0.0478   0.01920   0.00958  -0.0921   0.8593   0.0977
  -5.000   0.0766   0.01871   0.00910  -0.0920   0.8508   0.1071
  -4.750   0.1043   0.01828   0.00866  -0.0918   0.8415   0.1190
  -4.500   0.1339   0.01782   0.00823  -0.0918   0.8332   0.1356
  -4.250   0.1604   0.01748   0.00794  -0.0913   0.8225   0.1550
  -4.000   0.1893   0.01710   0.00757  -0.0912   0.8135   0.1800
  -3.750   0.2164   0.01675   0.00732  -0.0908   0.8027   0.2082
  -3.500   0.2433   0.01642   0.00710  -0.0905   0.7918   0.2453
  -3.250   0.2715   0.01598   0.00686  -0.0903   0.7824   0.3047
  -3.000   0.2970   0.01554   0.00676  -0.0898   0.7710   0.3985
  -2.750   0.3218   0.01501   0.00669  -0.0889   0.7605   0.5321
  -2.500   0.3446   0.01444   0.00662  -0.0870   0.7511   0.6963
  -2.250   0.3843   0.01398   0.00658  -0.0879   0.7396   0.9240
  -2.000   0.4252   0.01395   0.00637  -0.0904   0.7285   1.0001
  -1.750   0.4520   0.01400   0.00622  -0.0900   0.7179   1.0001
  -1.500   0.4775   0.01410   0.00619  -0.0894   0.7055   1.0001
  -1.250   0.5036   0.01420   0.00615  -0.0889   0.6936   1.0001
  -1.000   0.5301   0.01429   0.00609  -0.0885   0.6820   1.0001
  -0.750   0.5563   0.01440   0.00607  -0.0880   0.6698   1.0001
  -0.500   0.5821   0.01453   0.00610  -0.0876   0.6565   1.0001
  -0.250   0.6081   0.01466   0.00613  -0.0871   0.6433   1.0001
   0.000   0.6341   0.01481   0.00617  -0.0867   0.6303   1.0001
   0.250   0.6603   0.01495   0.00620  -0.0862   0.6172   1.0001
   0.500   0.6862   0.01511   0.00626  -0.0858   0.6037   1.0001
   0.750   0.7118   0.01530   0.00636  -0.0853   0.5892   1.0001
   1.000   0.7373   0.01549   0.00649  -0.0849   0.5750   1.0001
   1.250   0.7629   0.01571   0.00663  -0.0844   0.5611   1.0001
   1.500   0.7883   0.01594   0.00678  -0.0840   0.5471   1.0001
   1.750   0.8136   0.01618   0.00695  -0.0835   0.5334   1.0001
   2.000   0.8389   0.01645   0.00713  -0.0831   0.5205   1.0001
   2.250   0.8641   0.01673   0.00734  -0.0827   0.5079   1.0001
   2.500   0.8890   0.01703   0.00762  -0.0822   0.4949   1.0001
   2.750   0.9138   0.01735   0.00789  -0.0818   0.4829   1.0001
   3.000   0.9387   0.01769   0.00817  -0.0814   0.4719   1.0001
   3.250   0.9633   0.01804   0.00848  -0.0809   0.4605   1.0001
   3.500   0.9871   0.01840   0.00882  -0.0804   0.4477   1.0001
   3.750   1.0106   0.01876   0.00915  -0.0798   0.4345   1.0001
   4.000   1.0337   0.01915   0.00949  -0.0792   0.4216   1.0001
   4.250   1.0566   0.01955   0.00983  -0.0785   0.4097   1.0001
   4.500   1.0794   0.01995   0.01025  -0.0779   0.3978   1.0001
   4.750   1.1022   0.02036   0.01070  -0.0773   0.3870   1.0001
   5.000   1.1247   0.02081   0.01111  -0.0766   0.3772   1.0001
   5.250   1.1467   0.02124   0.01160  -0.0759   0.3666   1.0001
   5.500   1.1686   0.02170   0.01210  -0.0752   0.3568   1.0001
   5.750   1.1899   0.02218   0.01259  -0.0744   0.3471   1.0001
   6.000   1.2107   0.02266   0.01316  -0.0736   0.3367   1.0001
   6.250   1.2309   0.02318   0.01370  -0.0727   0.3271   1.0001
   6.500   1.2502   0.02370   0.01430  -0.0717   0.3165   1.0001
   6.750   1.2689   0.02425   0.01494  -0.0706   0.3056   1.0001
   7.000   1.2864   0.02484   0.01556  -0.0693   0.2950   1.0001
   7.250   1.3029   0.02545   0.01623  -0.0679   0.2841   1.0001
   7.500   1.3189   0.02609   0.01700  -0.0665   0.2727   1.0001
   7.750   1.3333   0.02679   0.01776  -0.0649   0.2617   1.0001
   8.000   1.3443   0.02753   0.01853  -0.0627   0.2509   1.0001
   8.250   1.3549   0.02835   0.01942  -0.0606   0.2393   1.0001
   8.500   1.3651   0.02926   0.02040  -0.0586   0.2282   1.0001
   8.750   1.3741   0.03027   0.02147  -0.0566   0.2183   1.0001
   9.000   1.3823   0.03139   0.02261  -0.0547   0.2092   1.0001
   9.250   1.3917   0.03255   0.02386  -0.0530   0.2009   1.0001
   9.500   1.3983   0.03387   0.02518  -0.0512   0.1940   1.0001
   9.750   1.4064   0.03521   0.02663  -0.0496   0.1861   1.0001
  10.250   1.4157   0.03839   0.02994  -0.0465   0.1709   1.0001
  10.500   1.4173   0.04028   0.03181  -0.0451   0.1637   1.0001
  10.750   1.4195   0.04225   0.03392  -0.0439   0.1555   1.0001
  11.000   1.4197   0.04446   0.03615  -0.0428   0.1487   1.0001
  11.250   1.4208   0.04672   0.03855  -0.0420   0.1416   1.0001
  11.500   1.4190   0.04930   0.04115  -0.0413   0.1359   1.0001
  11.750   1.4190   0.05188   0.04395  -0.0408   0.1292   1.0001
  12.000   1.4147   0.05493   0.04704  -0.0405   0.1238   1.0001
  12.250   1.4132   0.05789   0.05018  -0.0404   0.1179   1.0001
  12.500   1.4087   0.06124   0.05366  -0.0405   0.1128   1.0001
  12.750   1.4029   0.06488   0.05739  -0.0407   0.1082   1.0001
  13.000   1.3980   0.06865   0.06137  -0.0413   0.1026   1.0001
  13.250   1.3882   0.07312   0.06592  -0.0421   0.0978   1.0001
  13.500   1.3806   0.07756   0.07055  -0.0432   0.0919   1.0001
  13.750   1.3687   0.08275   0.07586  -0.0446   0.0865   1.0001
  14.000   1.3575   0.08801   0.08129  -0.0462   0.0805   1.0001
  14.250   1.3429   0.09394   0.08732  -0.0482   0.0750   1.0001
  14.500   1.3296   0.09985   0.09337  -0.0502   0.0685   1.0001
  14.750   1.3140   0.10623   0.09983  -0.0526   0.0629   1.0001
  15.000   1.2992   0.11256   0.10625  -0.0550   0.0571   1.0001
<< Back to N-22 (n22-il)

Polar data table (+)

Polar graphs


<< Back to N-22 (n22-il)