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N-13 (n13-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-13 (n13-il)
Reynolds number: 100,000
Max Cl/Cd: 41.3 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n13-il-100000.txt
Download as CSV file: xf-n13-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-13                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4885   0.12853   0.12337  -0.0203   1.0000   0.1412
 -12.500  -0.6828   0.10267   0.09735  -0.0307   1.0000   0.0743
 -12.250  -0.7899   0.07893   0.07337  -0.0477   1.0000   0.0623
 -12.000  -0.8126   0.07348   0.06783  -0.0491   1.0000   0.0620
 -11.750  -0.8342   0.06870   0.06295  -0.0492   1.0000   0.0616
 -11.500  -0.8585   0.06472   0.05881  -0.0478   1.0000   0.0615
 -11.250  -0.8779   0.06108   0.05503  -0.0452   1.0000   0.0609
 -11.000  -0.9013   0.05800   0.05176  -0.0409   1.0000   0.0608
 -10.750  -0.9206   0.05496   0.04849  -0.0364   1.0000   0.0609
 -10.500  -0.9357   0.05180   0.04501  -0.0320   1.0000   0.0612
 -10.250  -0.9481   0.04873   0.04155  -0.0274   1.0000   0.0617
 -10.000  -0.9549   0.04573   0.03812  -0.0231   1.0000   0.0622
  -9.750  -0.9557   0.04226   0.03427  -0.0195   1.0000   0.0629
  -9.500  -0.9460   0.03936   0.03126  -0.0174   1.0000   0.0648
  -9.250  -0.9349   0.03756   0.02934  -0.0150   1.0000   0.0675
  -9.000  -0.9257   0.03569   0.02717  -0.0121   1.0000   0.0712
  -8.750  -0.9145   0.03350   0.02468  -0.0094   1.0000   0.0750
  -8.500  -0.8993   0.03225   0.02343  -0.0074   1.0000   0.0800
  -8.250  -0.8863   0.03070   0.02159  -0.0047   1.0000   0.0865
  -8.000  -0.8716   0.02973   0.02061  -0.0026   1.0000   0.0940
  -7.750  -0.8560   0.02830   0.01908  -0.0005   1.0000   0.1023
  -7.500  -0.8425   0.02744   0.01800   0.0022   1.0000   0.1116
  -7.250  -0.8248   0.02609   0.01676   0.0037   1.0000   0.1217
  -7.000  -0.8078   0.02490   0.01555   0.0055   1.0000   0.1324
  -6.750  -0.7909   0.02384   0.01443   0.0074   1.0000   0.1440
  -6.500  -0.7735   0.02278   0.01340   0.0094   1.0000   0.1571
  -6.250  -0.7577   0.02173   0.01250   0.0115   1.0000   0.1738
  -6.000  -0.7439   0.02082   0.01170   0.0140   1.0000   0.1967
  -5.500  -0.7151   0.01915   0.01025   0.0188   1.0000   0.2418
  -5.250  -0.7011   0.01839   0.00967   0.0213   1.0000   0.2668
  -5.000  -0.6885   0.01764   0.00918   0.0240   1.0000   0.3035
  -4.750  -0.6778   0.01687   0.00880   0.0271   1.0000   0.3616
  -4.500  -0.6685   0.01614   0.00851   0.0306   1.0000   0.4418
  -4.250  -0.6573   0.01567   0.00839   0.0341   1.0000   0.5134
  -4.000  -0.6435   0.01542   0.00833   0.0371   1.0000   0.5706
  -3.750  -0.6286   0.01529   0.00832   0.0400   1.0000   0.6184
  -3.500  -0.6135   0.01520   0.00830   0.0429   1.0000   0.6628
  -3.250  -0.5965   0.01514   0.00836   0.0456   1.0000   0.7033
  -3.000  -0.5785   0.01510   0.00839   0.0480   1.0000   0.7407
  -2.750  -0.5557   0.01516   0.00852   0.0496   1.0000   0.7748
  -2.500  -0.5299   0.01529   0.00867   0.0504   1.0000   0.8052
  -2.250  -0.5000   0.01556   0.00895   0.0505   1.0000   0.8344
  -2.000  -0.4635   0.01604   0.00940   0.0493   1.0000   0.8622
  -1.750  -0.4201   0.01668   0.00997   0.0468   1.0000   0.8855
  -1.500  -0.3785   0.01733   0.01054   0.0445   1.0000   0.9087
  -1.250  -0.3145   0.01829   0.01139   0.0381   1.0000   0.9268
  -1.000  -0.2492   0.01910   0.01210   0.0312   1.0000   0.9425
  -0.750  -0.1900   0.01960   0.01253   0.0248   1.0000   0.9573
  -0.500  -0.1283   0.01996   0.01284   0.0177   1.0000   0.9716
  -0.250  -0.0682   0.02013   0.01298   0.0104   1.0000   0.9845
   0.000  -0.0099   0.02016   0.01300   0.0032   1.0000   0.9962
   0.250   0.0003   0.02013   0.01297   0.0037   1.0000   1.0000
   0.500   0.0319   0.02013   0.01299   0.0008   0.9931   1.0000
   0.750   0.0891   0.02008   0.01297  -0.0062   0.9808   1.0000
   1.000   0.1442   0.01990   0.01284  -0.0125   0.9674   1.0000
   1.250   0.2002   0.01958   0.01260  -0.0186   0.9532   1.0000
   1.500   0.2608   0.01909   0.01220  -0.0251   0.9384   1.0000
   1.750   0.3258   0.01839   0.01164  -0.0320   0.9242   1.0000
   2.000   0.3966   0.01754   0.01095  -0.0397   0.9106   1.0000
   2.250   0.4626   0.01672   0.01030  -0.0463   0.8926   1.0000
   2.500   0.5109   0.01608   0.00978  -0.0495   0.8637   1.0000
   2.750   0.5391   0.01560   0.00935  -0.0487   0.8230   1.0000
   3.000   0.5643   0.01514   0.00888  -0.0472   0.7735   1.0000
   3.250   0.5937   0.01488   0.00842  -0.0464   0.7182   1.0000
   3.500   0.6141   0.01499   0.00830  -0.0442   0.6600   1.0000
   3.750   0.6273   0.01519   0.00832  -0.0409   0.5975   1.0000
   4.000   0.6384   0.01547   0.00832  -0.0373   0.5249   1.0000
   4.250   0.6484   0.01597   0.00840  -0.0336   0.4522   1.0000
   4.500   0.6585   0.01666   0.00869  -0.0302   0.3889   1.0000
   4.750   0.6685   0.01737   0.00908  -0.0269   0.3299   1.0000
   5.000   0.6783   0.01817   0.00954  -0.0236   0.2755   1.0000
   5.250   0.6893   0.01906   0.01012  -0.0205   0.2317   1.0000
   5.500   0.7019   0.01999   0.01080  -0.0178   0.2003   1.0000
   5.750   0.7171   0.02098   0.01162  -0.0155   0.1787   1.0000
   6.000   0.7335   0.02189   0.01246  -0.0134   0.1616   1.0000
   6.250   0.7515   0.02291   0.01342  -0.0116   0.1486   1.0000
   6.500   0.7713   0.02408   0.01441  -0.0102   0.1375   1.0000
   6.750   0.7886   0.02491   0.01544  -0.0081   0.1277   1.0000
   7.000   0.8089   0.02625   0.01679  -0.0067   0.1199   1.0000
   7.250   0.8266   0.02727   0.01788  -0.0049   0.1120   1.0000
   7.500   0.8452   0.02883   0.01958  -0.0032   0.1055   1.0000
   7.750   0.8613   0.02996   0.02081  -0.0012   0.0987   1.0000
   8.000   0.8781   0.03192   0.02290   0.0006   0.0936   1.0000
   8.250   0.8901   0.03337   0.02467   0.0035   0.0884   1.0000
   8.500   0.9062   0.03508   0.02636   0.0051   0.0835   1.0000
   8.750   0.9131   0.03759   0.02926   0.0084   0.0806   1.0000
   9.000   0.9158   0.03962   0.03175   0.0125   0.0775   1.0000
   9.250   0.9222   0.04151   0.03386   0.0157   0.0741   1.0000
   9.500   0.9315   0.04370   0.03616   0.0181   0.0719   1.0000
   9.750   0.9358   0.04691   0.03951   0.0208   0.0703   1.0000
  10.000   0.9284   0.05065   0.04355   0.0249   0.0694   1.0000
  10.250   0.9159   0.05335   0.04662   0.0297   0.0690   1.0000
  10.500   0.8990   0.05622   0.04982   0.0346   0.0686   1.0000
  10.750   0.8787   0.05927   0.05312   0.0393   0.0684   1.0000
  11.000   0.8560   0.06220   0.05622   0.0440   0.0686   1.0000
  11.250   0.8293   0.06527   0.05945   0.0479   0.0685   1.0000
  11.500   0.8072   0.06927   0.06357   0.0497   0.0689   1.0000
  11.750   0.7868   0.07391   0.06829   0.0501   0.0693   1.0000
  12.000   0.5998   0.12223   0.11681   0.0191   0.1517   1.0000
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