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N-13 (n13-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-13 (n13-il)
Reynolds number: 100,000
Max Cl/Cd: 37.18 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n13-il-100000-n5.txt
Download as CSV file: xf-n13-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7458   0.10147   0.09602  -0.0276   1.0000   0.0267
 -13.750  -0.8421   0.07702   0.07109  -0.0435   1.0000   0.0243
 -13.500  -0.8700   0.06933   0.06313  -0.0477   1.0000   0.0241
 -13.250  -0.8886   0.06384   0.05742  -0.0499   1.0000   0.0240
 -13.000  -0.9008   0.05970   0.05313  -0.0509   1.0000   0.0243
 -12.750  -0.9115   0.05603   0.04929  -0.0512   1.0000   0.0245
 -12.500  -0.9194   0.05303   0.04615  -0.0509   1.0000   0.0250
 -12.250  -0.9272   0.05003   0.04297  -0.0499   1.0000   0.0252
 -12.000  -0.9322   0.04778   0.04057  -0.0485   1.0000   0.0261
 -11.750  -0.9368   0.04556   0.03816  -0.0465   1.0000   0.0270
 -11.500  -0.9399   0.04339   0.03576  -0.0441   1.0000   0.0278
 -11.250  -0.9416   0.04125   0.03334  -0.0414   1.0000   0.0290
 -11.000  -0.9408   0.03932   0.03118  -0.0385   1.0000   0.0302
 -10.750  -0.9387   0.03790   0.02972  -0.0356   1.0000   0.0312
 -10.500  -0.9359   0.03655   0.02829  -0.0325   1.0000   0.0325
 -10.250  -0.9313   0.03515   0.02674  -0.0294   1.0000   0.0341
 -10.000  -0.9237   0.03375   0.02509  -0.0265   1.0000   0.0367
  -9.750  -0.9171   0.03238   0.02364  -0.0237   1.0000   0.0392
  -9.500  -0.9091   0.03117   0.02235  -0.0210   1.0000   0.0426
  -9.250  -0.8980   0.02995   0.02087  -0.0184   1.0000   0.0466
  -9.000  -0.8917   0.02846   0.01943  -0.0153   1.0000   0.0506
  -8.750  -0.8816   0.02739   0.01825  -0.0126   1.0000   0.0562
  -8.500  -0.8720   0.02629   0.01712  -0.0098   1.0000   0.0612
  -8.250  -0.8606   0.02546   0.01629  -0.0073   1.0000   0.0668
  -8.000  -0.8479   0.02477   0.01561  -0.0049   1.0000   0.0728
  -7.750  -0.8327   0.02432   0.01509  -0.0028   1.0000   0.0814
  -7.500  -0.8173   0.02389   0.01457  -0.0007   1.0000   0.0906
  -7.250  -0.8033   0.02330   0.01395   0.0016   1.0000   0.0985
  -7.000  -0.7884   0.02267   0.01319   0.0039   1.0000   0.1067
  -6.750  -0.7764   0.02189   0.01244   0.0066   1.0000   0.1141
  -6.500  -0.7625   0.02127   0.01174   0.0090   1.0000   0.1231
  -6.250  -0.7494   0.02064   0.01110   0.0116   1.0000   0.1334
  -6.000  -0.7356   0.02008   0.01057   0.0139   1.0000   0.1447
  -5.750  -0.7207   0.01960   0.01009   0.0162   1.0000   0.1566
  -5.500  -0.7051   0.01916   0.00964   0.0183   1.0000   0.1690
  -5.250  -0.6891   0.01874   0.00923   0.0203   1.0000   0.1839
  -5.000  -0.6730   0.01832   0.00881   0.0224   1.0000   0.2011
  -4.750  -0.6570   0.01789   0.00843   0.0244   1.0000   0.2221
  -4.500  -0.6416   0.01741   0.00808   0.0265   1.0000   0.2501
  -4.250  -0.6270   0.01689   0.00779   0.0286   1.0000   0.2921
  -4.000  -0.6128   0.01639   0.00757   0.0309   1.0000   0.3527
  -3.750  -0.5953   0.01602   0.00737   0.0327   0.9995   0.4058
  -3.500  -0.5634   0.01576   0.00729   0.0315   0.9944   0.4572
  -3.250  -0.5331   0.01548   0.00724   0.0308   0.9888   0.5136
  -3.000  -0.5012   0.01534   0.00725   0.0299   0.9835   0.5648
  -2.750  -0.4699   0.01522   0.00723   0.0292   0.9774   0.6079
  -2.500  -0.4376   0.01513   0.00722   0.0283   0.9715   0.6451
  -2.250  -0.4044   0.01505   0.00719   0.0272   0.9654   0.6784
  -2.000  -0.3713   0.01499   0.00719   0.0263   0.9592   0.7094
  -1.750  -0.3351   0.01495   0.00723   0.0248   0.9535   0.7410
  -1.500  -0.2957   0.01498   0.00735   0.0227   0.9488   0.7738
  -1.250  -0.2560   0.01507   0.00752   0.0207   0.9432   0.8036
  -1.000  -0.2104   0.01522   0.00770   0.0174   0.9392   0.8278
  -0.750  -0.1642   0.01534   0.00783   0.0139   0.9333   0.8458
  -0.500  -0.1139   0.01540   0.00790   0.0098   0.9263   0.8619
  -0.250  -0.0633   0.01541   0.00790   0.0056   0.9184   0.8763
   0.000  -0.0133   0.01540   0.00788   0.0015   0.9113   0.8884
   0.250   0.0308   0.01542   0.00791  -0.0016   0.9031   0.9003
   0.500   0.0837   0.01540   0.00791  -0.0065   0.8964   0.9060
   0.750   0.1240   0.01538   0.00791  -0.0088   0.8849   0.9159
   1.000   0.1719   0.01535   0.00791  -0.0127   0.8730   0.9214
   1.250   0.2104   0.01532   0.00792  -0.0145   0.8566   0.9314
   1.500   0.2567   0.01524   0.00789  -0.0179   0.8361   0.9377
   1.750   0.2922   0.01519   0.00787  -0.0191   0.8083   0.9478
   2.000   0.3363   0.01504   0.00773  -0.0220   0.7763   0.9539
   2.250   0.3772   0.01493   0.00757  -0.0242   0.7439   0.9605
   2.500   0.4223   0.01487   0.00741  -0.0273   0.7087   0.9642
   2.750   0.4600   0.01495   0.00739  -0.0291   0.6703   0.9703
   3.000   0.4943   0.01508   0.00742  -0.0303   0.6184   0.9766
   3.250   0.5253   0.01529   0.00742  -0.0309   0.5491   0.9840
   3.500   0.5569   0.01562   0.00735  -0.0317   0.4631   0.9901
   3.750   0.5880   0.01607   0.00747  -0.0328   0.3986   0.9967
   4.000   0.6123   0.01649   0.00767  -0.0325   0.3482   1.0000
   4.250   0.6269   0.01686   0.00790  -0.0302   0.3080   1.0000
   4.500   0.6411   0.01728   0.00818  -0.0279   0.2690   1.0000
   4.750   0.6556   0.01773   0.00848  -0.0256   0.2334   1.0000
   5.000   0.6702   0.01822   0.00883  -0.0233   0.2034   1.0000
   5.250   0.6847   0.01874   0.00924  -0.0210   0.1777   1.0000
   5.500   0.6995   0.01927   0.00969  -0.0187   0.1555   1.0000
   5.750   0.7141   0.01983   0.01022  -0.0164   0.1390   1.0000
   6.000   0.7288   0.02041   0.01077  -0.0141   0.1259   1.0000
   6.250   0.7433   0.02101   0.01136  -0.0117   0.1152   1.0000
   6.750   0.7718   0.02229   0.01266  -0.0070   0.0998   1.0000
   7.000   0.7854   0.02300   0.01340  -0.0045   0.0947   1.0000
   7.250   0.7996   0.02378   0.01423  -0.0021   0.0898   1.0000
   7.500   0.8143   0.02449   0.01501   0.0002   0.0843   1.0000
   7.750   0.8270   0.02538   0.01586   0.0026   0.0798   1.0000
   8.000   0.8427   0.02621   0.01685   0.0047   0.0757   1.0000
   8.250   0.8570   0.02700   0.01774   0.0069   0.0709   1.0000
   8.500   0.8690   0.02796   0.01864   0.0093   0.0666   1.0000
   8.750   0.8833   0.02885   0.01979   0.0115   0.0623   1.0000
   9.000   0.8954   0.02969   0.02075   0.0139   0.0579   1.0000
   9.250   0.9059   0.03070   0.02174   0.0164   0.0546   1.0000
   9.500   0.9173   0.03186   0.02315   0.0190   0.0508   1.0000
   9.750   0.9272   0.03296   0.02442   0.0216   0.0474   1.0000
  10.000   0.9351   0.03395   0.02544   0.0244   0.0447   1.0000
  10.250   0.9420   0.03537   0.02695   0.0271   0.0424   1.0000
  10.500   0.9470   0.03684   0.02873   0.0303   0.0397   1.0000
  10.750   0.9487   0.03819   0.03027   0.0338   0.0376   1.0000
  11.000   0.9497   0.03943   0.03160   0.0373   0.0361   1.0000
  11.250   0.9506   0.04068   0.03286   0.0403   0.0348   1.0000
  11.500   0.9476   0.04266   0.03505   0.0436   0.0336   1.0000
  11.750   0.9404   0.04501   0.03773   0.0467   0.0324   1.0000
  12.000   0.9320   0.04738   0.04036   0.0493   0.0312   1.0000
  12.250   0.9226   0.04994   0.04314   0.0514   0.0302   1.0000
  12.500   0.9119   0.05282   0.04621   0.0528   0.0296   1.0000
  12.750   0.8984   0.05629   0.04989   0.0534   0.0293   1.0000
  13.000   0.8832   0.06023   0.05400   0.0530   0.0289   1.0000
  13.250   0.8603   0.06575   0.05976   0.0513   0.0290   1.0000
  13.500   0.8347   0.07233   0.06655   0.0479   0.0289   1.0000
  13.750   0.7768   0.08659   0.08113   0.0384   0.0303   1.0000
  14.000   0.6990   0.10907   0.10366   0.0250   0.0329   1.0000
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