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N-10 (n10-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 500,000
Max Cl/Cd: 92.03 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n10-il-500000-n5.txt
Download as CSV file: xf-n10-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-10                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.8937   0.04231   0.03964  -0.0833   0.9999   0.0134
 -14.500  -0.9267   0.03655   0.03357  -0.0833   0.9999   0.0134
 -14.250  -0.9345   0.03337   0.03013  -0.0817   0.9999   0.0137
 -14.000  -0.9350   0.03083   0.02733  -0.0798   0.9999   0.0141
 -13.750  -0.9276   0.02913   0.02545  -0.0780   0.9999   0.0145
 -13.500  -0.9117   0.02849   0.02479  -0.0765   0.9999   0.0149
 -13.250  -0.8916   0.02797   0.02423  -0.0757   0.9996   0.0154
 -13.000  -0.8618   0.02715   0.02333  -0.0769   0.9977   0.0160
 -12.750  -0.8336   0.02601   0.02203  -0.0781   0.9957   0.0167
 -12.500  -0.8062   0.02455   0.02033  -0.0793   0.9937   0.0175
 -12.250  -0.7798   0.02313   0.01864  -0.0801   0.9908   0.0183
 -12.000  -0.7487   0.02268   0.01817  -0.0811   0.9882   0.0189
 -11.750  -0.7156   0.02243   0.01790  -0.0824   0.9861   0.0194
 -11.500  -0.6838   0.02203   0.01744  -0.0835   0.9836   0.0201
 -11.250  -0.6553   0.02135   0.01665  -0.0840   0.9795   0.0209
 -11.000  -0.6246   0.02052   0.01563  -0.0850   0.9764   0.0218
 -10.750  -0.5924   0.01975   0.01467  -0.0863   0.9740   0.0226
 -10.500  -0.5666   0.01899   0.01376  -0.0861   0.9675   0.0232
 -10.250  -0.5371   0.01818   0.01289  -0.0869   0.9633   0.0240
 -10.000  -0.5087   0.01777   0.01244  -0.0871   0.9571   0.0246
  -9.750  -0.4786   0.01734   0.01194  -0.0876   0.9512   0.0254
  -9.500  -0.4491   0.01683   0.01134  -0.0881   0.9447   0.0262
  -9.250  -0.4198   0.01626   0.01066  -0.0884   0.9372   0.0270
  -9.000  -0.3903   0.01574   0.01002  -0.0888   0.9292   0.0278
  -8.750  -0.3608   0.01523   0.00938  -0.0891   0.9202   0.0284
  -8.500  -0.3322   0.01476   0.00879  -0.0891   0.9088   0.0288
  -8.250  -0.3049   0.01399   0.00788  -0.0890   0.8952   0.0295
  -8.000  -0.2782   0.01337   0.00716  -0.0888   0.8805   0.0303
  -7.750  -0.2515   0.01295   0.00663  -0.0884   0.8663   0.0309
  -7.500  -0.2247   0.01259   0.00617  -0.0881   0.8539   0.0315
  -7.250  -0.1979   0.01227   0.00575  -0.0877   0.8426   0.0321
  -7.000  -0.1710   0.01199   0.00539  -0.0874   0.8316   0.0329
  -6.750  -0.1439   0.01172   0.00503  -0.0871   0.8221   0.0337
  -6.500  -0.1168   0.01144   0.00467  -0.0868   0.8129   0.0343
  -6.250  -0.0896   0.01118   0.00433  -0.0866   0.8029   0.0349
  -6.000  -0.0624   0.01095   0.00402  -0.0863   0.7925   0.0354
  -5.750  -0.0352   0.01075   0.00373  -0.0860   0.7812   0.0359
  -5.500  -0.0077   0.01053   0.00346  -0.0858   0.7702   0.0365
  -5.250   0.0196   0.01027   0.00314  -0.0856   0.7593   0.0378
  -5.000   0.0470   0.01009   0.00290  -0.0854   0.7474   0.0393
  -4.750   0.0745   0.00995   0.00271  -0.0852   0.7333   0.0412
  -4.500   0.1018   0.00984   0.00253  -0.0850   0.7165   0.0434
  -4.250   0.1290   0.00976   0.00236  -0.0847   0.6972   0.0458
  -4.000   0.1558   0.00967   0.00220  -0.0844   0.6771   0.0515
  -3.500   0.2100   0.00952   0.00200  -0.0839   0.6457   0.0790
  -3.250   0.2376   0.00946   0.00193  -0.0838   0.6346   0.0950
  -3.000   0.2650   0.00939   0.00185  -0.0837   0.6241   0.1119
  -2.750   0.2921   0.00919   0.00183  -0.0837   0.6137   0.1698
  -2.500   0.3197   0.00913   0.00182  -0.0836   0.6036   0.2038
  -2.250   0.3473   0.00910   0.00180  -0.0836   0.5929   0.2278
  -2.000   0.3745   0.00903   0.00179  -0.0835   0.5804   0.2604
  -1.750   0.4016   0.00889   0.00179  -0.0834   0.5660   0.3140
  -1.500   0.4279   0.00865   0.00182  -0.0833   0.5486   0.4254
  -1.250   0.4537   0.00842   0.00186  -0.0831   0.5254   0.5378
  -1.000   0.4779   0.00838   0.00191  -0.0825   0.4833   0.6245
  -0.750   0.4987   0.00829   0.00204  -0.0811   0.4375   0.7659
  -0.500   0.5171   0.00824   0.00222  -0.0787   0.4082   0.9036
  -0.250   0.5529   0.00841   0.00232  -0.0803   0.3877   0.9723
   0.000   0.5909   0.00859   0.00240  -0.0827   0.3744   1.0001
   0.250   0.6165   0.00877   0.00249  -0.0823   0.3638   1.0001
   0.500   0.6423   0.00894   0.00258  -0.0820   0.3537   1.0001
   0.750   0.6684   0.00910   0.00268  -0.0817   0.3459   1.0001
   1.000   0.6946   0.00925   0.00279  -0.0815   0.3389   1.0001
   1.250   0.7207   0.00943   0.00290  -0.0812   0.3323   1.0001
   1.500   0.7472   0.00957   0.00301  -0.0811   0.3264   1.0001
   1.750   0.7736   0.00972   0.00314  -0.0809   0.3216   1.0001
   2.000   0.7998   0.00990   0.00328  -0.0807   0.3173   1.0001
   2.250   0.8265   0.01003   0.00341  -0.0806   0.3129   1.0001
   2.500   0.8530   0.01018   0.00356  -0.0805   0.3085   1.0001
   2.750   0.8792   0.01035   0.00371  -0.0803   0.3046   1.0001
   3.000   0.9054   0.01053   0.00388  -0.0801   0.3010   1.0001
   3.250   0.9320   0.01067   0.00404  -0.0801   0.2967   1.0001
   3.500   0.9583   0.01084   0.00421  -0.0799   0.2919   1.0001
   3.750   0.9840   0.01104   0.00440  -0.0797   0.2872   1.0001
   4.000   1.0103   0.01119   0.00459  -0.0796   0.2823   1.0001
   4.250   1.0363   0.01137   0.00478  -0.0795   0.2759   1.0001
   4.500   1.0618   0.01158   0.00498  -0.0793   0.2691   1.0001
   4.750   1.0869   0.01182   0.00519  -0.0791   0.2566   1.0001
   5.000   1.1117   0.01208   0.00541  -0.0788   0.2380   1.0001
   5.250   1.1328   0.01263   0.00574  -0.0780   0.1949   1.0001
   5.500   1.1511   0.01342   0.00629  -0.0768   0.1574   1.0001
   5.750   1.1721   0.01398   0.00677  -0.0759   0.1407   1.0001
   6.000   1.1936   0.01449   0.00722  -0.0752   0.1292   1.0001
   6.250   1.2160   0.01489   0.00762  -0.0746   0.1215   1.0001
   6.500   1.2378   0.01533   0.00804  -0.0739   0.1146   1.0001
   6.750   1.2599   0.01572   0.00845  -0.0733   0.1077   1.0001
   7.000   1.2809   0.01619   0.00890  -0.0725   0.0998   1.0001
   7.250   1.3009   0.01670   0.00938  -0.0715   0.0871   1.0001
   7.500   1.3117   0.01788   0.01025  -0.0693   0.0480   1.0001
   8.000   1.3310   0.01996   0.01218  -0.0642   0.0163   1.0001
   8.250   1.3453   0.02064   0.01291  -0.0624   0.0146   1.0001
   8.500   1.3600   0.02131   0.01365  -0.0607   0.0136   1.0001
   8.750   1.3732   0.02208   0.01449  -0.0589   0.0126   1.0001
   9.000   1.3848   0.02298   0.01545  -0.0570   0.0117   1.0001
   9.250   1.3956   0.02395   0.01650  -0.0552   0.0110   1.0001
   9.500   1.4078   0.02484   0.01749  -0.0536   0.0106   1.0001
   9.750   1.4188   0.02586   0.01859  -0.0520   0.0102   1.0001
  10.000   1.4286   0.02699   0.01980  -0.0504   0.0098   1.0001
  10.250   1.4373   0.02825   0.02115  -0.0489   0.0095   1.0001
  10.500   1.4448   0.02966   0.02264  -0.0475   0.0091   1.0001
  10.750   1.4507   0.03127   0.02434  -0.0461   0.0088   1.0001
  11.000   1.4538   0.03320   0.02636  -0.0447   0.0085   1.0001
  11.250   1.4538   0.03551   0.02878  -0.0434   0.0083   1.0001
  11.500   1.4589   0.03743   0.03081  -0.0425   0.0081   1.0001
  11.750   1.4625   0.03957   0.03305  -0.0418   0.0079   1.0001
  12.000   1.4646   0.04194   0.03553  -0.0413   0.0077   1.0001
  12.250   1.4649   0.04461   0.03831  -0.0409   0.0075   1.0001
  12.500   1.4634   0.04759   0.04141  -0.0407   0.0073   1.0001
  12.750   1.4607   0.05084   0.04477  -0.0407   0.0072   1.0001
  13.000   1.4567   0.05439   0.04844  -0.0409   0.0070   1.0001
  13.250   1.4516   0.05819   0.05235  -0.0414   0.0069   1.0001
  13.500   1.4448   0.06231   0.05659  -0.0420   0.0068   1.0001
  13.750   1.4372   0.06673   0.06113  -0.0429   0.0067   1.0001
  14.000   1.4285   0.07144   0.06596  -0.0440   0.0067   1.0001
  14.250   1.4185   0.07646   0.07112  -0.0454   0.0066   1.0001
  14.500   1.4081   0.08172   0.07649  -0.0469   0.0065   1.0001
  14.750   1.3971   0.08717   0.08206  -0.0486   0.0065   1.0001
  15.000   1.3857   0.09273   0.08773  -0.0505   0.0064   1.0001
  15.250   1.3740   0.09837   0.09349  -0.0523   0.0064   1.0001
  15.500   1.3623   0.10407   0.09929  -0.0543   0.0063   1.0001
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