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N-22 (n22-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 200,000
Max Cl/Cd: 70.73 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n22-il-200000-n5.txt
Download as CSV file: xf-n22-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3934   0.08863   0.08487  -0.0452   0.9999   0.0353
 -11.500  -0.4017   0.08416   0.08045  -0.0469   0.9999   0.0356
 -11.250  -0.4159   0.07984   0.07620  -0.0479   0.9999   0.0361
 -11.000  -0.5367   0.04288   0.03862  -0.0826   0.9820   0.0369
 -10.750  -0.5320   0.03435   0.02917  -0.0882   0.9734   0.0380
 -10.500  -0.5126   0.03044   0.02458  -0.0901   0.9669   0.0389
 -10.250  -0.4866   0.02819   0.02198  -0.0914   0.9616   0.0398
 -10.000  -0.4553   0.02696   0.02066  -0.0929   0.9582   0.0406
  -9.750  -0.4303   0.02583   0.01939  -0.0930   0.9505   0.0413
  -9.500  -0.4008   0.02451   0.01785  -0.0939   0.9455   0.0421
  -9.250  -0.3740   0.02332   0.01644  -0.0941   0.9387   0.0429
  -9.000  -0.3462   0.02218   0.01509  -0.0943   0.9319   0.0438
  -8.750  -0.3169   0.02120   0.01389  -0.0947   0.9264   0.0450
  -8.500  -0.2908   0.02038   0.01286  -0.0944   0.9176   0.0460
  -8.250  -0.2617   0.01944   0.01177  -0.0946   0.9119   0.0470
  -8.000  -0.2363   0.01866   0.01095  -0.0942   0.9025   0.0478
  -7.750  -0.2078   0.01798   0.01022  -0.0942   0.8959   0.0489
  -7.500  -0.1816   0.01742   0.00959  -0.0937   0.8863   0.0500
  -7.250  -0.1535   0.01684   0.00892  -0.0936   0.8792   0.0513
  -7.000  -0.1270   0.01635   0.00835  -0.0931   0.8694   0.0529
  -6.750  -0.0994   0.01591   0.00779  -0.0928   0.8612   0.0547
  -6.500  -0.0729   0.01535   0.00722  -0.0924   0.8516   0.0567
  -6.250  -0.0458   0.01494   0.00678  -0.0921   0.8423   0.0587
  -6.000  -0.0184   0.01457   0.00633  -0.0918   0.8332   0.0612
  -5.750   0.0087   0.01425   0.00593  -0.0914   0.8227   0.0640
  -5.500   0.0359   0.01388   0.00554  -0.0911   0.8130   0.0677
  -5.250   0.0632   0.01362   0.00524  -0.0907   0.8023   0.0730
  -5.000   0.0904   0.01336   0.00496  -0.0904   0.7912   0.0795
  -4.750   0.1179   0.01314   0.00469  -0.0901   0.7801   0.0882
  -4.500   0.1452   0.01293   0.00446  -0.0898   0.7687   0.1002
  -4.250   0.1726   0.01275   0.00429  -0.0896   0.7576   0.1158
  -4.000   0.2002   0.01258   0.00413  -0.0894   0.7475   0.1334
  -3.750   0.2277   0.01242   0.00400  -0.0892   0.7372   0.1532
  -3.500   0.2552   0.01228   0.00388  -0.0890   0.7273   0.1749
  -3.000   0.3101   0.01197   0.00370  -0.0887   0.7070   0.2352
  -2.750   0.3372   0.01176   0.00364  -0.0886   0.6969   0.2866
  -2.500   0.3636   0.01147   0.00361  -0.0884   0.6865   0.3733
  -2.250   0.3892   0.01110   0.00362  -0.0880   0.6759   0.4889
  -2.000   0.4136   0.01074   0.00364  -0.0872   0.6654   0.6134
  -1.750   0.4359   0.01039   0.00367  -0.0855   0.6542   0.7442
  -1.500   0.4685   0.01012   0.00370  -0.0856   0.6420   0.9174
  -1.250   0.5127   0.01014   0.00363  -0.0890   0.6293   1.0001
  -1.000   0.5389   0.01025   0.00362  -0.0886   0.6169   1.0001
  -0.500   0.5913   0.01050   0.00364  -0.0878   0.5896   1.0001
  -0.250   0.6175   0.01064   0.00367  -0.0875   0.5756   1.0001
   0.000   0.6437   0.01079   0.00372  -0.0871   0.5619   1.0001
   0.250   0.6697   0.01096   0.00379  -0.0868   0.5476   1.0001
   0.500   0.6956   0.01114   0.00387  -0.0864   0.5327   1.0001
   0.750   0.7214   0.01134   0.00397  -0.0861   0.5180   1.0001
   1.000   0.7471   0.01155   0.00408  -0.0857   0.5039   1.0001
   1.250   0.7727   0.01178   0.00421  -0.0854   0.4906   1.0001
   1.500   0.7983   0.01200   0.00436  -0.0850   0.4769   1.0001
   1.750   0.8239   0.01224   0.00453  -0.0847   0.4637   1.0001
   2.000   0.8493   0.01248   0.00471  -0.0844   0.4515   1.0001
   2.250   0.8746   0.01275   0.00491  -0.0840   0.4405   1.0001
   2.500   0.8998   0.01302   0.00513  -0.0837   0.4288   1.0001
   2.750   0.9245   0.01330   0.00535  -0.0833   0.4152   1.0001
   3.000   0.9487   0.01361   0.00558  -0.0828   0.4003   1.0001
   3.250   0.9728   0.01393   0.00583  -0.0823   0.3864   1.0001
   3.500   0.9970   0.01424   0.00610  -0.0819   0.3755   1.0001
   3.750   1.0214   0.01455   0.00637  -0.0815   0.3654   1.0001
   4.000   1.0459   0.01484   0.00667  -0.0811   0.3564   1.0001
   4.250   1.0698   0.01518   0.00697  -0.0807   0.3476   1.0001
   4.500   1.0942   0.01547   0.00729  -0.0803   0.3391   1.0001
   4.750   1.1174   0.01583   0.00763  -0.0798   0.3308   1.0001
   5.000   1.1413   0.01614   0.00797  -0.0794   0.3219   1.0001
   5.250   1.1639   0.01652   0.00834  -0.0788   0.3134   1.0001
   5.500   1.1873   0.01684   0.00872  -0.0783   0.3045   1.0001
   5.750   1.2094   0.01723   0.00911  -0.0776   0.2963   1.0001
   6.000   1.2317   0.01759   0.00952  -0.0770   0.2870   1.0001
   6.250   1.2532   0.01799   0.00994  -0.0763   0.2778   1.0001
   6.500   1.2733   0.01844   0.01041  -0.0753   0.2673   1.0001
   6.750   1.2936   0.01886   0.01087  -0.0745   0.2553   1.0001
   7.000   1.3126   0.01935   0.01137  -0.0734   0.2426   1.0001
   7.250   1.3301   0.01989   0.01192  -0.0721   0.2293   1.0001
   7.500   1.3457   0.02048   0.01252  -0.0705   0.2162   1.0001
   7.750   1.3585   0.02115   0.01317  -0.0686   0.2026   1.0001
   8.000   1.3702   0.02193   0.01392  -0.0665   0.1891   1.0001
   8.250   1.3808   0.02282   0.01478  -0.0645   0.1769   1.0001
   8.500   1.3908   0.02379   0.01573  -0.0625   0.1659   1.0001
   8.750   1.4021   0.02474   0.01669  -0.0609   0.1566   1.0001
   9.000   1.4115   0.02582   0.01779  -0.0591   0.1487   1.0001
   9.250   1.4219   0.02690   0.01889  -0.0575   0.1407   1.0001
   9.500   1.4310   0.02808   0.02010  -0.0560   0.1337   1.0001
   9.750   1.4406   0.02928   0.02136  -0.0546   0.1271   1.0001
  10.000   1.4485   0.03064   0.02276  -0.0532   0.1215   1.0001
  10.250   1.4583   0.03191   0.02411  -0.0521   0.1155   1.0001
  10.500   1.4636   0.03357   0.02580  -0.0508   0.1100   1.0001
  10.750   1.4731   0.03496   0.02729  -0.0499   0.1038   1.0001
  11.000   1.4771   0.03686   0.02922  -0.0488   0.0975   1.0001
  11.250   1.4842   0.03856   0.03101  -0.0481   0.0903   1.0001
  11.500   1.4874   0.04066   0.03316  -0.0473   0.0834   1.0001
  11.750   1.4896   0.04294   0.03548  -0.0466   0.0746   1.0001
  12.000   1.4894   0.04553   0.03810  -0.0459   0.0630   1.0001
  12.250   1.4821   0.04895   0.04147  -0.0454   0.0478   1.0001
  12.500   1.4708   0.05295   0.04544  -0.0450   0.0383   1.0001
  12.750   1.4607   0.05703   0.04955  -0.0449   0.0331   1.0001
  13.000   1.4519   0.06111   0.05371  -0.0450   0.0299   1.0001
  13.250   1.4429   0.06540   0.05810  -0.0454   0.0278   1.0001
  13.500   1.4351   0.06967   0.06251  -0.0460   0.0261   1.0001
  13.750   1.4254   0.07433   0.06729  -0.0469   0.0248   1.0001
  14.000   1.4143   0.07934   0.07241  -0.0480   0.0239   1.0001
  14.250   1.4045   0.08431   0.07752  -0.0492   0.0231   1.0001
  14.500   1.3949   0.08934   0.08270  -0.0506   0.0224   1.0001
  14.750   1.3841   0.09464   0.08815  -0.0522   0.0218   1.0001
  15.000   1.3727   0.10016   0.09381  -0.0540   0.0213   1.0001
  15.250   1.3606   0.10589   0.09967  -0.0559   0.0208   1.0001
  15.500   1.3478   0.11182   0.10574  -0.0581   0.0205   1.0001
  15.750   1.3346   0.11791   0.11196  -0.0604   0.0201   1.0001
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