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N-10 (n10-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 200,000
Max Cl/Cd: 68.62 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n10-il-200000.txt
Download as CSV file: xf-n10-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3656   0.09609   0.09250  -0.0354   0.9999   0.0634
 -10.500  -0.3695   0.09294   0.08940  -0.0366   0.9999   0.0657
 -10.250  -0.3944   0.08957   0.08616  -0.0402   0.9999   0.0681
 -10.000  -0.3338   0.07792   0.07486  -0.0369   0.9999   0.0707
  -9.750  -0.3338   0.07673   0.07372  -0.0332   0.9999   0.0720
  -9.500  -0.4716   0.07943   0.07613  -0.0448   0.9999   0.0689
  -9.250  -0.4723   0.07549   0.07235  -0.0404   0.9999   0.0699
  -9.000  -0.4722   0.07427   0.07118  -0.0361   0.9999   0.0706
  -8.750  -0.4630   0.07260   0.06953  -0.0344   0.9988   0.0720
  -8.500  -0.4363   0.06899   0.06586  -0.0390   0.9948   0.0760
  -8.250  -0.4120   0.05726   0.05370  -0.0560   0.9863   0.0837
  -8.000  -0.3822   0.05498   0.05146  -0.0578   0.9835   0.0859
  -7.750  -0.3553   0.04836   0.04407  -0.0664   0.9747   0.0970
  -7.500  -0.3250   0.04514   0.04105  -0.0682   0.9721   0.0992
  -7.250  -0.3012   0.03156   0.02603  -0.0722   0.9650   0.0660
  -7.000  -0.2681   0.02759   0.02152  -0.0743   0.9609   0.0636
  -6.750  -0.2290   0.02512   0.01861  -0.0768   0.9581   0.0644
  -6.500  -0.1970   0.02310   0.01622  -0.0777   0.9511   0.0644
  -6.250  -0.1565   0.02134   0.01412  -0.0800   0.9466   0.0651
  -6.000  -0.1113   0.02007   0.01258  -0.0832   0.9438   0.0674
  -5.750  -0.0772   0.01919   0.01151  -0.0840   0.9360   0.0687
  -5.500  -0.0383   0.01751   0.00975  -0.0861   0.9318   0.0708
  -5.250   0.0023   0.01647   0.00874  -0.0884   0.9284   0.0739
  -5.000   0.0319   0.01586   0.00810  -0.0884   0.9185   0.0779
  -4.750   0.0698   0.01503   0.00723  -0.0899   0.9135   0.0830
  -4.500   0.0975   0.01431   0.00658  -0.0896   0.9028   0.0896
  -4.250   0.1285   0.01359   0.00589  -0.0899   0.8943   0.1012
  -4.000   0.1581   0.01274   0.00521  -0.0900   0.8850   0.1371
  -3.750   0.1848   0.01205   0.00498  -0.0897   0.8734   0.2508
  -3.500   0.2122   0.01156   0.00473  -0.0894   0.8622   0.3257
  -3.250   0.2391   0.01097   0.00456  -0.0891   0.8523   0.4458
  -3.000   0.2598   0.01027   0.00454  -0.0873   0.8402   0.6329
  -2.750   0.2919   0.00964   0.00467  -0.0861   0.8306   0.9352
  -2.500   0.3570   0.00957   0.00442  -0.0935   0.8219   1.0001
  -2.250   0.3813   0.00961   0.00432  -0.0927   0.8094   1.0001
  -2.000   0.4061   0.00966   0.00423  -0.0919   0.7973   1.0001
  -1.750   0.4311   0.00970   0.00414  -0.0911   0.7856   1.0001
  -1.500   0.4564   0.00975   0.00405  -0.0904   0.7737   1.0001
  -1.250   0.4808   0.00980   0.00400  -0.0895   0.7601   1.0001
  -1.000   0.5056   0.00985   0.00396  -0.0888   0.7464   1.0001
  -0.750   0.5306   0.00990   0.00392  -0.0880   0.7326   1.0001
  -0.500   0.5558   0.00995   0.00388  -0.0873   0.7180   1.0001
  -0.250   0.5811   0.01001   0.00384  -0.0866   0.7023   1.0001
   0.000   0.6063   0.01009   0.00382  -0.0859   0.6853   1.0001
   0.250   0.6314   0.01020   0.00380  -0.0852   0.6670   1.0001
   0.500   0.6562   0.01035   0.00382  -0.0844   0.6460   1.0001
   0.750   0.6805   0.01054   0.00387  -0.0836   0.6221   1.0001
   1.000   0.7042   0.01077   0.00395  -0.0826   0.5937   1.0001
   1.250   0.7274   0.01101   0.00404  -0.0816   0.5615   1.0001
   1.500   0.7504   0.01128   0.00414  -0.0806   0.5282   1.0001
   1.750   0.7735   0.01158   0.00427  -0.0798   0.4985   1.0001
   2.000   0.7970   0.01192   0.00444  -0.0790   0.4763   1.0001
   2.250   0.8212   0.01228   0.00466  -0.0784   0.4596   1.0001
   2.500   0.8457   0.01264   0.00491  -0.0779   0.4465   1.0001
   2.750   0.8705   0.01302   0.00518  -0.0775   0.4353   1.0001
   3.000   0.8959   0.01334   0.00548  -0.0772   0.4254   1.0001
   3.250   0.9212   0.01374   0.00580  -0.0769   0.4170   1.0001
   3.500   0.9468   0.01405   0.00612  -0.0767   0.4087   1.0001
   3.750   0.9722   0.01444   0.00646  -0.0764   0.4009   1.0001
   4.000   0.9972   0.01475   0.00679  -0.0761   0.3922   1.0001
   4.250   1.0227   0.01514   0.00716  -0.0759   0.3852   1.0001
   4.500   1.0479   0.01544   0.00753  -0.0757   0.3782   1.0001
   4.750   1.0736   0.01589   0.00791  -0.0755   0.3719   1.0001
   5.000   1.0981   0.01615   0.00832  -0.0751   0.3648   1.0001
   5.250   1.1230   0.01654   0.00870  -0.0749   0.3578   1.0001
   5.500   1.1471   0.01686   0.00913  -0.0745   0.3502   1.0001
   5.750   1.1711   0.01723   0.00951  -0.0740   0.3419   1.0001
   6.000   1.1931   0.01748   0.00989  -0.0732   0.3312   1.0001
   6.250   1.2141   0.01776   0.01023  -0.0723   0.3185   1.0001
   6.500   1.2341   0.01802   0.01054  -0.0711   0.3041   1.0001
   6.750   1.2536   0.01828   0.01089  -0.0699   0.2884   1.0001
   7.000   1.2722   0.01854   0.01121  -0.0686   0.2689   1.0001
   7.250   1.2900   0.01889   0.01158  -0.0672   0.2453   1.0001
   7.500   1.3060   0.01941   0.01203  -0.0656   0.2171   1.0001
   7.750   1.3191   0.02018   0.01265  -0.0637   0.1931   1.0001
   8.000   1.3317   0.02104   0.01344  -0.0617   0.1769   1.0001
   8.250   1.3414   0.02195   0.01430  -0.0592   0.1644   1.0001
   8.500   1.3513   0.02290   0.01523  -0.0569   0.1530   1.0001
   8.750   1.3631   0.02377   0.01615  -0.0550   0.1419   1.0001
   9.000   1.3737   0.02473   0.01715  -0.0530   0.1291   1.0001
   9.250   1.3814   0.02589   0.01830  -0.0509   0.1112   1.0001
   9.500   1.3850   0.02750   0.01966  -0.0484   0.0653   1.0001
   9.750   1.3771   0.02999   0.02194  -0.0451   0.0469   1.0001
  10.000   1.3756   0.03213   0.02413  -0.0426   0.0409   1.0001
  10.250   1.3729   0.03450   0.02656  -0.0405   0.0375   1.0001
  10.500   1.3724   0.03680   0.02898  -0.0389   0.0353   1.0001
  10.750   1.3724   0.03916   0.03147  -0.0376   0.0334   1.0001
  11.000   1.3699   0.04187   0.03429  -0.0365   0.0319   1.0001
  11.250   1.3632   0.04515   0.03767  -0.0357   0.0308   1.0001
  11.500   1.3536   0.04889   0.04150  -0.0350   0.0300   1.0001
  11.750   1.3510   0.05202   0.04478  -0.0347   0.0294   1.0001
  12.000   1.3474   0.05535   0.04825  -0.0345   0.0288   1.0001
  12.250   1.3434   0.05881   0.05182  -0.0345   0.0282   1.0001
  12.500   1.3395   0.06230   0.05542  -0.0345   0.0277   1.0001
  12.750   1.3361   0.06579   0.05901  -0.0346   0.0272   1.0001
  13.000   1.3333   0.06922   0.06253  -0.0347   0.0267   1.0001
  13.250   1.3313   0.07257   0.06595  -0.0348   0.0262   1.0001
  13.500   1.3303   0.07579   0.06921  -0.0349   0.0256   1.0001
  13.750   1.3304   0.07872   0.07217  -0.0346   0.0250   1.0001
  14.000   1.3348   0.08075   0.07420  -0.0331   0.0243   1.0001
  14.250   1.3338   0.08430   0.07793  -0.0338   0.0240   1.0001
  14.500   1.3331   0.08781   0.08159  -0.0344   0.0236   1.0001
  14.750   1.3325   0.09130   0.08523  -0.0349   0.0233   1.0001
  15.000   1.3313   0.09495   0.08904  -0.0355   0.0231   1.0001
  15.250   1.3282   0.09895   0.09320  -0.0364   0.0229   1.0001
  15.500   1.3239   0.10327   0.09770  -0.0376   0.0227   1.0001
  15.750   1.3179   0.10798   0.10259  -0.0392   0.0226   1.0001
  16.000   1.3102   0.11312   0.10792  -0.0412   0.0226   1.0001
  16.250   1.3004   0.11877   0.11377  -0.0437   0.0225   1.0001
  16.500   1.2887   0.12497   0.12018  -0.0468   0.0226   1.0001
  16.750   1.2752   0.13178   0.12719  -0.0505   0.0226   1.0001
  17.000   1.2599   0.13920   0.13482  -0.0547   0.0228   1.0001
  17.250   1.2423   0.14744   0.14327  -0.0598   0.0229   1.0001
  17.500   1.2229   0.15646   0.15249  -0.0654   0.0231   1.0001
  17.750   1.2009   0.16665   0.16287  -0.0720   0.0234   1.0001
  18.000   1.1757   0.17843   0.17483  -0.0797   0.0238   1.0001
  18.250   1.1502   0.19117   0.18769  -0.0876   0.0243   1.0001
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