Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

N-10 (n10-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 100,000
Max Cl/Cd: 52.62 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n10-il-100000-n5.txt
Download as CSV file: xf-n10-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3956   0.09320   0.08811  -0.0409   0.9999   0.0442
 -10.750  -0.4002   0.08934   0.08431  -0.0418   0.9999   0.0440
 -10.500  -0.4088   0.08544   0.08050  -0.0426   0.9999   0.0440
 -10.250  -0.4234   0.08159   0.07675  -0.0431   0.9999   0.0441
 -10.000  -0.4411   0.07753   0.07280  -0.0440   0.9999   0.0441
  -9.750  -0.4574   0.07238   0.06771  -0.0463   0.9999   0.0442
  -9.500  -0.4747   0.06649   0.06180  -0.0484   0.9999   0.0443
  -9.250  -0.4911   0.06025   0.05545  -0.0496   0.9999   0.0445
  -9.000  -0.4840   0.05056   0.04516  -0.0572   0.9937   0.0449
  -8.750  -0.4646   0.04399   0.03799  -0.0620   0.9868   0.0457
  -8.500  -0.4368   0.04218   0.03614  -0.0640   0.9816   0.0473
  -8.250  -0.4080   0.03983   0.03356  -0.0663   0.9760   0.0492
  -8.000  -0.3818   0.03613   0.02935  -0.0685   0.9696   0.0504
  -7.750  -0.3525   0.03288   0.02554  -0.0705   0.9642   0.0515
  -7.500  -0.3229   0.03050   0.02262  -0.0719   0.9584   0.0535
  -7.250  -0.2917   0.02852   0.02009  -0.0731   0.9524   0.0553
  -7.000  -0.2567   0.02661   0.01783  -0.0749   0.9487   0.0563
  -6.750  -0.2285   0.02525   0.01633  -0.0753   0.9412   0.0575
  -6.500  -0.1941   0.02407   0.01501  -0.0768   0.9366   0.0590
  -6.250  -0.1600   0.02314   0.01394  -0.0782   0.9319   0.0614
  -6.000  -0.1297   0.02235   0.01299  -0.0787   0.9247   0.0645
  -5.750  -0.0942   0.02144   0.01191  -0.0801   0.9202   0.0668
  -5.500  -0.0642   0.02057   0.01100  -0.0805   0.9127   0.0689
  -5.250  -0.0303   0.01979   0.01023  -0.0816   0.9061   0.0721
  -5.000   0.0012   0.01915   0.00953  -0.0821   0.8976   0.0763
  -4.750   0.0359   0.01845   0.00879  -0.0832   0.8897   0.0830
  -4.500   0.0661   0.01791   0.00821  -0.0834   0.8788   0.0934
  -4.250   0.0981   0.01724   0.00754  -0.0840   0.8691   0.1088
  -4.000   0.1296   0.01655   0.00704  -0.0845   0.8595   0.1378
  -3.750   0.1582   0.01607   0.00681  -0.0845   0.8481   0.2076
  -3.500   0.1875   0.01560   0.00653  -0.0847   0.8371   0.2755
  -3.250   0.2167   0.01496   0.00631  -0.0848   0.8261   0.3797
  -3.000   0.2421   0.01432   0.00618  -0.0840   0.8137   0.5292
  -2.750   0.2625   0.01361   0.00619  -0.0814   0.8017   0.7343
  -2.500   0.3163   0.01325   0.00604  -0.0853   0.7920   0.9652
  -2.250   0.3563   0.01321   0.00579  -0.0876   0.7809   1.0001
  -2.000   0.3811   0.01327   0.00569  -0.0869   0.7677   1.0001
  -1.750   0.4063   0.01333   0.00560  -0.0863   0.7547   1.0001
  -1.500   0.4318   0.01339   0.00552  -0.0857   0.7417   1.0001
  -1.250   0.4575   0.01345   0.00546  -0.0851   0.7284   1.0001
  -1.000   0.4831   0.01352   0.00540  -0.0845   0.7142   1.0001
  -0.750   0.5088   0.01359   0.00535  -0.0839   0.6993   1.0001
  -0.500   0.5345   0.01367   0.00530  -0.0833   0.6836   1.0001
  -0.250   0.5603   0.01377   0.00527  -0.0827   0.6675   1.0001
   0.000   0.5861   0.01388   0.00526  -0.0821   0.6510   1.0001
   0.250   0.6117   0.01403   0.00529  -0.0816   0.6342   1.0001
   0.500   0.6372   0.01420   0.00534  -0.0810   0.6167   1.0001
   0.750   0.6624   0.01439   0.00542  -0.0804   0.5983   1.0001
   1.000   0.6871   0.01461   0.00554  -0.0797   0.5783   1.0001
   1.250   0.7115   0.01483   0.00569  -0.0790   0.5561   1.0001
   1.500   0.7357   0.01508   0.00583  -0.0783   0.5337   1.0001
   1.750   0.7599   0.01534   0.00601  -0.0777   0.5111   1.0001
   2.000   0.7841   0.01563   0.00619  -0.0770   0.4915   1.0001
   2.250   0.8082   0.01595   0.00639  -0.0764   0.4742   1.0001
   2.500   0.8321   0.01630   0.00663  -0.0757   0.4585   1.0001
   2.750   0.8560   0.01668   0.00690  -0.0751   0.4436   1.0001
   3.000   0.8797   0.01707   0.00720  -0.0745   0.4296   1.0001
   3.250   0.9036   0.01747   0.00755  -0.0740   0.4170   1.0001
   3.500   0.9277   0.01788   0.00791  -0.0735   0.4065   1.0001
   3.750   0.9520   0.01829   0.00829  -0.0731   0.3981   1.0001
   4.000   0.9766   0.01868   0.00873  -0.0727   0.3899   1.0001
   4.250   1.0006   0.01913   0.00914  -0.0722   0.3816   1.0001
   4.500   1.0244   0.01952   0.00960  -0.0717   0.3722   1.0001
   4.750   1.0480   0.01997   0.01003  -0.0712   0.3638   1.0001
   5.000   1.0714   0.02037   0.01055  -0.0707   0.3551   1.0001
   5.250   1.0950   0.02083   0.01103  -0.0703   0.3478   1.0001
   5.500   1.1181   0.02125   0.01158  -0.0697   0.3398   1.0001
   5.750   1.1411   0.02173   0.01208  -0.0692   0.3326   1.0001
   6.000   1.1634   0.02216   0.01270  -0.0685   0.3238   1.0001
   6.250   1.1852   0.02264   0.01325  -0.0678   0.3157   1.0001
   6.500   1.2062   0.02310   0.01387  -0.0669   0.3058   1.0001
   6.750   1.2264   0.02358   0.01449  -0.0660   0.2954   1.0001
   7.000   1.2451   0.02407   0.01512  -0.0648   0.2833   1.0001
   7.250   1.2622   0.02456   0.01574  -0.0633   0.2681   1.0001
   7.500   1.2778   0.02507   0.01637  -0.0617   0.2491   1.0001
   7.750   1.2909   0.02569   0.01700  -0.0598   0.2277   1.0001
   8.000   1.3029   0.02643   0.01774  -0.0578   0.2049   1.0001
   8.250   1.3105   0.02737   0.01860  -0.0553   0.1874   1.0001
   8.500   1.3163   0.02849   0.01965  -0.0526   0.1727   1.0001
   9.000   1.3271   0.03113   0.02226  -0.0479   0.1472   1.0001
   9.250   1.3330   0.03252   0.02371  -0.0458   0.1358   1.0001
   9.500   1.3376   0.03406   0.02532  -0.0439   0.1238   1.0001
   9.750   1.3412   0.03574   0.02706  -0.0421   0.1122   1.0001
  10.000   1.3452   0.03749   0.02891  -0.0406   0.0983   1.0001
  10.250   1.3475   0.03950   0.03100  -0.0392   0.0734   1.0001
  10.500   1.3380   0.04264   0.03397  -0.0376   0.0543   1.0001
  10.750   1.3282   0.04605   0.03734  -0.0364   0.0446   1.0001
  11.000   1.3194   0.04957   0.04094  -0.0355   0.0390   1.0001
  11.250   1.3105   0.05332   0.04479  -0.0351   0.0357   1.0001
  11.500   1.3017   0.05728   0.04889  -0.0351   0.0334   1.0001
  11.750   1.2911   0.06166   0.05341  -0.0355   0.0317   1.0001
  12.000   1.2786   0.06650   0.05837  -0.0362   0.0306   1.0001
  12.250   1.2679   0.07132   0.06335  -0.0372   0.0296   1.0001
  12.500   1.2568   0.07640   0.06861  -0.0385   0.0287   1.0001
  12.750   1.2451   0.08179   0.07415  -0.0401   0.0279   1.0001
  13.000   1.2332   0.08739   0.07991  -0.0419   0.0272   1.0001
  13.250   1.2214   0.09312   0.08578  -0.0438   0.0266   1.0001
<< Back to N-10 (n10-il)

Polar data table (+)

Polar graphs


<< Back to N-10 (n10-il)