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N-10 (n10-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 100,000
Max Cl/Cd: 52.04 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n10-il-100000.txt
Download as CSV file: xf-n10-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3590   0.09733   0.09239  -0.0326   0.9999   0.1208
 -10.000  -0.3800   0.09546   0.09066  -0.0343   0.9999   0.1247
  -9.750  -0.4194   0.09421   0.08962  -0.0369   0.9999   0.1258
  -9.500  -0.4104   0.08996   0.08541  -0.0335   0.9999   0.1277
  -9.250  -0.3892   0.08732   0.08274  -0.0295   0.9999   0.1322
  -9.000  -0.4020   0.08541   0.08094  -0.0281   0.9999   0.1360
  -8.750  -0.4325   0.08331   0.07896  -0.0305   0.9999   0.1397
  -8.500  -0.4519   0.07984   0.07553  -0.0321   0.9999   0.1420
  -8.250  -0.4385   0.07829   0.07405  -0.0252   0.9999   0.1458
  -8.000  -0.4446   0.07615   0.07193  -0.0245   0.9999   0.1517
  -7.750  -0.4557   0.07239   0.06814  -0.0274   0.9999   0.1576
  -7.500  -0.4507   0.07061   0.06641  -0.0237   0.9999   0.1613
  -7.250  -0.4529   0.06693   0.06260  -0.0278   0.9999   0.1720
  -7.000  -0.4465   0.06537   0.06082  -0.0299   0.9999   0.1853
  -6.750  -0.4405   0.06174   0.05734  -0.0272   0.9999   0.1877
  -6.500  -0.4169   0.05865   0.05412  -0.0305   0.9966   0.2028
  -6.250  -0.3571   0.03989   0.03339  -0.0468   0.9937   0.1124
  -6.000  -0.3190   0.03588   0.02906  -0.0499   0.9888   0.1043
  -5.750  -0.2768   0.03233   0.02482  -0.0535   0.9847   0.1019
  -5.500  -0.2371   0.02995   0.02190  -0.0562   0.9794   0.1016
  -5.250  -0.1949   0.02807   0.01955  -0.0590   0.9738   0.1018
  -5.000  -0.1526   0.02671   0.01788  -0.0619   0.9672   0.1045
  -4.750  -0.1070   0.02568   0.01651  -0.0651   0.9596   0.1099
  -4.500  -0.0649   0.02427   0.01504  -0.0677   0.9509   0.1147
  -4.250  -0.0136   0.02313   0.01385  -0.0718   0.9436   0.1240
  -4.000   0.0248   0.02216   0.01300  -0.0736   0.9327   0.1393
  -3.750   0.0677   0.02118   0.01224  -0.0762   0.9237   0.1710
  -3.500   0.1115   0.01962   0.01150  -0.0791   0.9161   0.3113
  -3.250   0.1445   0.01821   0.01130  -0.0799   0.9080   0.5771
  -3.000   0.2028   0.01716   0.01106  -0.0834   0.9037   1.0001
  -2.750   0.2533   0.01688   0.01048  -0.0874   0.8985   1.0001
  -2.500   0.2838   0.01686   0.01025  -0.0878   0.8869   1.0001
  -2.250   0.3193   0.01676   0.00997  -0.0889   0.8775   1.0001
  -2.000   0.3595   0.01650   0.00955  -0.0908   0.8694   1.0001
  -1.750   0.3893   0.01645   0.00936  -0.0908   0.8577   1.0001
  -1.500   0.4229   0.01628   0.00908  -0.0913   0.8473   1.0001
  -1.250   0.4585   0.01603   0.00870  -0.0921   0.8375   1.0001
  -1.000   0.4856   0.01600   0.00858  -0.0914   0.8242   1.0001
  -0.750   0.5133   0.01596   0.00845  -0.0909   0.8110   1.0001
  -0.500   0.5414   0.01589   0.00831  -0.0903   0.7973   1.0001
  -0.250   0.5691   0.01581   0.00815  -0.0896   0.7826   1.0001
   0.000   0.5959   0.01574   0.00799  -0.0888   0.7663   1.0001
   0.250   0.6223   0.01566   0.00783  -0.0878   0.7486   1.0001
   0.500   0.6491   0.01555   0.00764  -0.0869   0.7299   1.0001
   0.750   0.6753   0.01549   0.00747  -0.0859   0.7091   1.0001
   1.000   0.7006   0.01548   0.00737  -0.0849   0.6854   1.0001
   1.250   0.7266   0.01555   0.00729  -0.0840   0.6611   1.0001
   1.500   0.7527   0.01574   0.00729  -0.0832   0.6366   1.0001
   1.750   0.7774   0.01606   0.00749  -0.0823   0.6121   1.0001
   2.000   0.8028   0.01643   0.00771  -0.0817   0.5911   1.0001
   2.250   0.8284   0.01680   0.00796  -0.0812   0.5731   1.0001
   2.500   0.8537   0.01717   0.00824  -0.0807   0.5567   1.0001
   2.750   0.8786   0.01751   0.00852  -0.0802   0.5413   1.0001
   3.000   0.9031   0.01783   0.00879  -0.0795   0.5263   1.0001
   3.250   0.9275   0.01816   0.00910  -0.0790   0.5121   1.0001
   3.500   0.9520   0.01853   0.00947  -0.0785   0.4996   1.0001
   3.750   0.9769   0.01892   0.00985  -0.0780   0.4883   1.0001
   4.000   1.0023   0.01931   0.01019  -0.0777   0.4775   1.0001
   4.250   1.0273   0.01974   0.01062  -0.0773   0.4667   1.0001
   4.500   1.0516   0.02023   0.01118  -0.0769   0.4570   1.0001
   4.750   1.0777   0.02073   0.01164  -0.0767   0.4478   1.0001
   5.000   1.1016   0.02123   0.01223  -0.0762   0.4374   1.0001
   5.250   1.1253   0.02177   0.01285  -0.0757   0.4268   1.0001
   5.500   1.1503   0.02232   0.01338  -0.0754   0.4163   1.0001
   5.750   1.1740   0.02288   0.01399  -0.0748   0.4050   1.0001
   6.000   1.1957   0.02348   0.01473  -0.0740   0.3930   1.0001
   6.250   1.2179   0.02409   0.01543  -0.0732   0.3801   1.0001
   6.500   1.2394   0.02472   0.01611  -0.0724   0.3658   1.0001
   6.750   1.2594   0.02535   0.01682  -0.0712   0.3496   1.0001
   7.000   1.2780   0.02597   0.01749  -0.0698   0.3315   1.0001
   7.250   1.2959   0.02654   0.01806  -0.0683   0.3129   1.0001
   7.500   1.3127   0.02705   0.01855  -0.0667   0.2952   1.0001
   7.750   1.3259   0.02746   0.01902  -0.0645   0.2779   1.0001
   8.000   1.3370   0.02784   0.01954  -0.0621   0.2614   1.0001
   8.250   1.3482   0.02826   0.02007  -0.0597   0.2462   1.0001
   8.500   1.3581   0.02874   0.02063  -0.0572   0.2316   1.0001
   8.750   1.3662   0.02931   0.02128  -0.0546   0.2172   1.0001
   9.000   1.3716   0.03001   0.02203  -0.0517   0.2035   1.0001
   9.250   1.3755   0.03093   0.02299  -0.0487   0.1909   1.0001
   9.500   1.3779   0.03211   0.02417  -0.0458   0.1782   1.0001
   9.750   1.3778   0.03359   0.02567  -0.0430   0.1645   1.0001
  10.000   1.3749   0.03541   0.02756  -0.0403   0.1492   1.0001
  10.250   1.3673   0.03775   0.03001  -0.0377   0.1304   1.0001
  10.500   1.3530   0.04092   0.03314  -0.0353   0.1109   1.0001
  10.750   1.3393   0.04454   0.03680  -0.0335   0.0896   1.0001
  11.000   1.3290   0.04808   0.04032  -0.0323   0.0776   1.0001
  11.250   1.3201   0.05168   0.04389  -0.0316   0.0706   1.0001
  11.500   1.3125   0.05528   0.04753  -0.0312   0.0654   1.0001
  11.750   1.3053   0.05891   0.05116  -0.0307   0.0617   1.0001
  12.000   1.3019   0.06222   0.05457  -0.0303   0.0583   1.0001
  12.250   1.2987   0.06550   0.05789  -0.0299   0.0558   1.0001
  12.500   1.3004   0.06804   0.06032  -0.0287   0.0534   1.0001
  12.750   1.3031   0.07085   0.06333  -0.0280   0.0516   1.0001
  13.000   1.3053   0.07378   0.06641  -0.0275   0.0498   1.0001
  13.250   1.3070   0.07678   0.06952  -0.0272   0.0481   1.0001
  13.500   1.3098   0.07960   0.07236  -0.0269   0.0464   1.0001
  13.750   1.3199   0.08177   0.07447  -0.0254   0.0445   1.0001
  14.000   1.3139   0.08603   0.07900  -0.0261   0.0439   1.0001
  14.250   1.3074   0.09055   0.08379  -0.0269   0.0435   1.0001
  14.500   1.2983   0.09555   0.08905  -0.0282   0.0432   1.0001
  14.750   1.2861   0.10115   0.09491  -0.0300   0.0431   1.0001
  15.000   1.2712   0.10743   0.10144  -0.0326   0.0431   1.0001
  15.250   1.2533   0.11451   0.10876  -0.0360   0.0431   1.0001
  15.500   1.2328   0.12240   0.11687  -0.0402   0.0433   1.0001
  15.750   1.2100   0.13122   0.12591  -0.0453   0.0436   1.0001
  16.000   1.1852   0.14101   0.13589  -0.0512   0.0440   1.0001
  16.250   1.1592   0.15175   0.14679  -0.0577   0.0445   1.0001
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