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=500,000 Ncrit=9


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 500,000
Max Cl/Cd: 98.4 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n22-il-500000.txt
Download as CSV file: xf-n22-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2706   0.09637   0.09417  -0.0413   0.9999   0.0410
 -12.000  -0.5603   0.05974   0.05745  -0.0628   0.9999   0.0336
 -11.750  -0.6368   0.03767   0.03440  -0.0833   0.9915   0.0331
 -11.500  -0.6267   0.03096   0.02700  -0.0876   0.9860   0.0339
 -11.250  -0.5961   0.02921   0.02516  -0.0897   0.9840   0.0346
 -11.000  -0.5624   0.02807   0.02396  -0.0919   0.9825   0.0352
 -10.750  -0.5344   0.02666   0.02241  -0.0930   0.9781   0.0359
 -10.500  -0.5035   0.02505   0.02058  -0.0947   0.9750   0.0369
 -10.250  -0.4725   0.02324   0.01846  -0.0963   0.9720   0.0379
 -10.000  -0.4405   0.02168   0.01661  -0.0977   0.9694   0.0386
  -9.750  -0.4151   0.02079   0.01549  -0.0974   0.9621   0.0390
  -9.500  -0.3888   0.01866   0.01316  -0.0978   0.9571   0.0400
  -9.250  -0.3629   0.01787   0.01233  -0.0975   0.9504   0.0408
  -9.000  -0.3369   0.01719   0.01158  -0.0970   0.9431   0.0416
  -8.750  -0.3113   0.01652   0.01081  -0.0964   0.9359   0.0423
  -8.500  -0.2863   0.01586   0.01005  -0.0956   0.9275   0.0431
  -8.250  -0.2608   0.01525   0.00934  -0.0949   0.9195   0.0440
  -8.000  -0.2352   0.01474   0.00872  -0.0941   0.9106   0.0449
  -7.750  -0.2088   0.01439   0.00826  -0.0935   0.9016   0.0456
  -7.500  -0.1840   0.01340   0.00718  -0.0928   0.8927   0.0467
  -7.250  -0.1580   0.01282   0.00657  -0.0922   0.8825   0.0479
  -7.000  -0.1315   0.01242   0.00612  -0.0917   0.8733   0.0491
  -6.750  -0.1047   0.01207   0.00571  -0.0912   0.8626   0.0505
  -6.500  -0.0776   0.01175   0.00532  -0.0908   0.8521   0.0519
  -6.250  -0.0502   0.01153   0.00500  -0.0903   0.8419   0.0533
  -6.000  -0.0239   0.01098   0.00442  -0.0899   0.8299   0.0559
  -5.750   0.0035   0.01071   0.00411  -0.0896   0.8183   0.0583
  -5.500   0.0311   0.01050   0.00383  -0.0893   0.8080   0.0611
  -5.250   0.0587   0.01021   0.00349  -0.0891   0.7976   0.0648
  -5.000   0.0866   0.01000   0.00327  -0.0889   0.7878   0.0701
  -4.750   0.1144   0.00980   0.00304  -0.0887   0.7784   0.0778
  -4.500   0.1426   0.00959   0.00287  -0.0886   0.7687   0.0899
  -4.250   0.1706   0.00943   0.00273  -0.0885   0.7597   0.1087
  -4.000   0.1987   0.00928   0.00263  -0.0884   0.7498   0.1300
  -3.750   0.2268   0.00916   0.00254  -0.0884   0.7406   0.1509
  -3.500   0.2550   0.00906   0.00246  -0.0883   0.7313   0.1723
  -3.250   0.2831   0.00893   0.00240  -0.0883   0.7218   0.1983
  -3.000   0.3109   0.00879   0.00233  -0.0883   0.7124   0.2361
  -2.750   0.3388   0.00857   0.00230  -0.0883   0.7021   0.2967
  -2.500   0.3661   0.00830   0.00228  -0.0883   0.6928   0.3877
  -2.250   0.3929   0.00795   0.00228  -0.0882   0.6828   0.5095
  -2.000   0.4184   0.00754   0.00233  -0.0877   0.6727   0.6575
  -1.750   0.4383   0.00704   0.00240  -0.0855   0.6625   0.8449
  -1.500   0.4834   0.00690   0.00240  -0.0886   0.6501   0.9901
  -1.250   0.5181   0.00697   0.00238  -0.0901   0.6382   1.0001
  -1.000   0.5445   0.00706   0.00237  -0.0897   0.6265   1.0001
  -0.750   0.5709   0.00717   0.00238  -0.0893   0.6138   1.0001
  -0.500   0.5975   0.00727   0.00240  -0.0891   0.5998   1.0001
  -0.250   0.6241   0.00738   0.00243  -0.0888   0.5851   1.0001
   0.000   0.6507   0.00751   0.00247  -0.0885   0.5701   1.0001
   0.250   0.6773   0.00765   0.00253  -0.0883   0.5549   1.0001
   0.500   0.7038   0.00781   0.00259  -0.0880   0.5391   1.0001
   0.750   0.7302   0.00799   0.00268  -0.0878   0.5225   1.0001
   1.000   0.7564   0.00818   0.00277  -0.0875   0.5056   1.0001
   1.250   0.7827   0.00838   0.00289  -0.0873   0.4895   1.0001
   1.500   0.8089   0.00859   0.00301  -0.0871   0.4735   1.0001
   1.750   0.8346   0.00883   0.00315  -0.0868   0.4556   1.0001
   2.250   0.8857   0.00935   0.00345  -0.0862   0.4203   1.0001
   2.500   0.9118   0.00956   0.00362  -0.0860   0.4073   1.0001
   2.750   0.9380   0.00978   0.00379  -0.0859   0.3961   1.0001
   3.000   0.9639   0.01002   0.00397  -0.0857   0.3862   1.0001
   3.250   0.9899   0.01024   0.00417  -0.0855   0.3765   1.0001
   3.500   1.0159   0.01046   0.00436  -0.0854   0.3676   1.0001
   3.750   1.0414   0.01071   0.00457  -0.0852   0.3585   1.0001
   4.000   1.0675   0.01092   0.00478  -0.0850   0.3508   1.0001
   4.250   1.0928   0.01118   0.00501  -0.0848   0.3429   1.0001
   4.500   1.1186   0.01139   0.00523  -0.0847   0.3357   1.0001
   4.750   1.1437   0.01165   0.00547  -0.0844   0.3279   1.0001
   5.000   1.1690   0.01188   0.00572  -0.0842   0.3204   1.0001
   5.250   1.1937   0.01215   0.00597  -0.0839   0.3118   1.0001
   5.500   1.2187   0.01239   0.00623  -0.0837   0.3036   1.0001
   5.750   1.2426   0.01270   0.00651  -0.0833   0.2949   1.0001
   6.000   1.2673   0.01294   0.00678  -0.0831   0.2852   1.0001
   6.250   1.2906   0.01325   0.00707  -0.0826   0.2732   1.0001
   6.500   1.3133   0.01360   0.00739  -0.0821   0.2590   1.0001
   6.750   1.3353   0.01399   0.00773  -0.0815   0.2426   1.0001
   7.000   1.3558   0.01446   0.00813  -0.0806   0.2230   1.0001
   7.250   1.3742   0.01506   0.00862  -0.0795   0.2021   1.0001
   7.500   1.3915   0.01570   0.00916  -0.0782   0.1823   1.0001
   7.750   1.4077   0.01638   0.00976  -0.0767   0.1667   1.0001
   8.000   1.4226   0.01702   0.01035  -0.0750   0.1550   1.0001
   8.250   1.4360   0.01769   0.01100  -0.0730   0.1457   1.0001
   8.500   1.4514   0.01829   0.01160  -0.0714   0.1380   1.0001
   8.750   1.4654   0.01898   0.01229  -0.0697   0.1313   1.0001
   9.000   1.4808   0.01961   0.01294  -0.0683   0.1253   1.0001
   9.250   1.4934   0.02041   0.01374  -0.0667   0.1189   1.0001
   9.500   1.5087   0.02108   0.01445  -0.0654   0.1125   1.0001
   9.750   1.5204   0.02199   0.01535  -0.0638   0.1060   1.0001
  10.000   1.5346   0.02277   0.01616  -0.0626   0.0994   1.0001
  10.250   1.5458   0.02376   0.01717  -0.0611   0.0920   1.0001
  10.500   1.5551   0.02494   0.01832  -0.0596   0.0809   1.0001
  10.750   1.5561   0.02677   0.02001  -0.0574   0.0584   1.0001
  11.000   1.5445   0.02971   0.02275  -0.0545   0.0357   1.0001
  11.250   1.5409   0.03221   0.02525  -0.0526   0.0295   1.0001
  11.500   1.5417   0.03443   0.02755  -0.0513   0.0266   1.0001
  11.750   1.5411   0.03688   0.03006  -0.0501   0.0247   1.0001
  12.000   1.5399   0.03951   0.03278  -0.0492   0.0234   1.0001
  12.250   1.5411   0.04196   0.03533  -0.0485   0.0225   1.0001
  12.500   1.5399   0.04476   0.03825  -0.0479   0.0217   1.0001
  12.750   1.5361   0.04794   0.04152  -0.0476   0.0210   1.0001
  13.000   1.5285   0.05170   0.04537  -0.0473   0.0204   1.0001
  13.500   1.5135   0.05966   0.05357  -0.0477   0.0195   1.0001
  13.750   1.5079   0.06357   0.05761  -0.0481   0.0192   1.0001
  14.000   1.5007   0.06783   0.06198  -0.0488   0.0188   1.0001
  14.250   1.4925   0.07232   0.06660  -0.0496   0.0185   1.0001
  14.500   1.4830   0.07709   0.07147  -0.0506   0.0182   1.0001
  14.750   1.4729   0.08203   0.07652  -0.0518   0.0179   1.0001
  15.000   1.4621   0.08717   0.08178  -0.0531   0.0176   1.0001
  15.250   1.4502   0.09255   0.08726  -0.0545   0.0174   1.0001
  15.500   1.4377   0.09805   0.09287  -0.0561   0.0172   1.0001
  15.750   1.4243   0.10375   0.09866  -0.0578   0.0169   1.0001
<< Back to N-22 (n22-il)

Polar data table (+)

Polar graphs


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