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USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 29 AIRFOIL (usa29-il)
Reynolds number: 100,000
Max Cl/Cd: 52.39 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa29-il-100000-n5.txt
Download as CSV file: xf-usa29-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 29 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1890   0.10105   0.09638  -0.0634   0.9753   0.0588
 -10.250  -0.1759   0.09736   0.09266  -0.0659   0.9726   0.0603
 -10.000  -0.1690   0.09387   0.08916  -0.0676   0.9671   0.0623
  -9.750  -0.1643   0.08928   0.08455  -0.0705   0.9631   0.0633
  -9.500  -0.2994   0.09181   0.08698  -0.0656   0.9771   0.0577
  -9.250  -0.2734   0.09067   0.08580  -0.0669   0.9735   0.0599
  -9.000  -0.2689   0.08624   0.08135  -0.0706   0.9663   0.0602
  -8.750  -0.2642   0.08082   0.07592  -0.0762   0.9603   0.0605
  -8.500  -0.2676   0.07602   0.07113  -0.0803   0.9501   0.0608
  -8.250  -0.2684   0.07141   0.06649  -0.0843   0.9410   0.0618
  -8.000  -0.2692   0.06511   0.06013  -0.0899   0.9313   0.0631
  -7.750  -0.2857   0.05641   0.05130  -0.0947   0.9184   0.0634
  -7.500  -0.3240   0.04259   0.03670  -0.0990   0.9036   0.0634
  -7.250  -0.3183   0.03775   0.03123  -0.0992   0.8962   0.0641
  -7.000  -0.3092   0.03492   0.02791  -0.0976   0.8872   0.0652
  -6.750  -0.2913   0.03247   0.02492  -0.0970   0.8806   0.0670
  -6.500  -0.2742   0.03063   0.02256  -0.0956   0.8723   0.0682
  -6.250  -0.2437   0.02889   0.02063  -0.0966   0.8683   0.0693
  -6.000  -0.2270   0.02786   0.01946  -0.0947   0.8582   0.0702
  -5.750  -0.1948   0.02662   0.01803  -0.0957   0.8537   0.0716
  -5.500  -0.1756   0.02577   0.01703  -0.0941   0.8438   0.0728
  -5.250  -0.1429   0.02470   0.01576  -0.0950   0.8387   0.0746
  -5.000  -0.1217   0.02402   0.01490  -0.0936   0.8287   0.0769
  -4.750  -0.0883   0.02311   0.01374  -0.0945   0.8232   0.0795
  -4.500  -0.0670   0.02252   0.01313  -0.0932   0.8127   0.0814
  -4.250  -0.0334   0.02177   0.01229  -0.0942   0.8069   0.0839
  -4.000  -0.0124   0.02132   0.01175  -0.0927   0.7957   0.0865
  -3.750   0.0159   0.02077   0.01106  -0.0926   0.7874   0.0900
  -3.500   0.0422   0.02026   0.01047  -0.0921   0.7779   0.0941
  -3.250   0.0667   0.01986   0.01002  -0.0914   0.7678   0.1012
  -3.000   0.0971   0.01931   0.00940  -0.0917   0.7600   0.1116
  -2.750   0.1199   0.01891   0.00898  -0.0907   0.7488   0.1250
  -2.500   0.1486   0.01846   0.00859  -0.0908   0.7400   0.1463
  -2.250   0.1769   0.01816   0.00833  -0.0908   0.7306   0.1761
  -2.000   0.2030   0.01800   0.00818  -0.0904   0.7207   0.2066
  -1.750   0.2330   0.01786   0.00806  -0.0907   0.7128   0.2390
  -1.500   0.2562   0.01791   0.00810  -0.0897   0.7026   0.2619
  -1.250   0.2835   0.01795   0.00808  -0.0894   0.6944   0.2797
  -1.000   0.3090   0.01805   0.00809  -0.0888   0.6855   0.2961
  -0.750   0.3340   0.01825   0.00819  -0.0880   0.6774   0.3157
  -0.500   0.3593   0.01842   0.00824  -0.0873   0.6695   0.3330
  -0.250   0.3845   0.01855   0.00826  -0.0867   0.6617   0.3465
   0.000   0.4107   0.01861   0.00822  -0.0863   0.6541   0.3581
   0.250   0.4372   0.01867   0.00816  -0.0859   0.6469   0.3688
   0.500   0.4628   0.01874   0.00813  -0.0855   0.6395   0.3800
   0.750   0.4912   0.01873   0.00806  -0.0856   0.6331   0.3912
   1.000   0.5180   0.01874   0.00806  -0.0855   0.6256   0.4007
   1.250   0.5510   0.01873   0.00796  -0.0865   0.6198   0.4106
   1.500   0.5793   0.01879   0.00803  -0.0868   0.6123   0.4194
   1.750   0.6132   0.01879   0.00800  -0.0881   0.6060   0.4280
   2.000   0.6433   0.01887   0.00805  -0.0887   0.5997   0.4357
   2.250   0.6719   0.01893   0.00814  -0.0890   0.5930   0.4427
   2.500   0.7029   0.01898   0.00815  -0.0897   0.5877   0.4510
   2.750   0.7250   0.01909   0.00835  -0.0888   0.5808   0.4583
   3.000   0.7501   0.01918   0.00847  -0.0883   0.5749   0.4675
   3.250   0.7758   0.01923   0.00856  -0.0880   0.5698   0.4778
   3.500   0.7951   0.01936   0.00882  -0.0865   0.5633   0.4898
   3.750   0.8185   0.01939   0.00897  -0.0857   0.5579   0.5101
   4.250   0.9758   0.01944   0.01009  -0.1078   0.5433   0.9921
   4.500   1.0146   0.01972   0.01034  -0.1104   0.5381   1.0000
   4.750   1.0319   0.02008   0.01079  -0.1085   0.5319   1.0000
   5.000   1.0534   0.02036   0.01107  -0.1074   0.5267   1.0000
   5.250   1.0752   0.02064   0.01135  -0.1063   0.5219   1.0000
   5.500   1.0915   0.02103   0.01183  -0.1042   0.5159   1.0000
   5.750   1.1126   0.02133   0.01216  -0.1030   0.5108   1.0000
   6.000   1.1337   0.02164   0.01250  -0.1018   0.5061   1.0000
   6.250   1.1485   0.02207   0.01305  -0.0995   0.5001   1.0000
   6.500   1.1690   0.02238   0.01341  -0.0982   0.4952   1.0000
   6.750   1.1895   0.02272   0.01381  -0.0969   0.4905   1.0000
   7.000   1.2027   0.02320   0.01443  -0.0944   0.4846   1.0000
   7.250   1.2225   0.02352   0.01481  -0.0930   0.4795   1.0000
   7.500   1.2346   0.02384   0.01521  -0.0901   0.4712   1.0000
   7.750   1.2464   0.02388   0.01523  -0.0869   0.4594   1.0000
   8.000   1.2524   0.02406   0.01545  -0.0828   0.4466   1.0000
   8.250   1.2532   0.02440   0.01585  -0.0778   0.4335   1.0000
   8.500   1.2529   0.02473   0.01623  -0.0727   0.4215   1.0000
   8.750   1.2551   0.02511   0.01664  -0.0683   0.4096   1.0000
   9.000   1.2567   0.02557   0.01713  -0.0639   0.3964   1.0000
   9.250   1.2562   0.02620   0.01780  -0.0594   0.3812   1.0000
   9.500   1.2540   0.02702   0.01865  -0.0550   0.3634   1.0000
   9.750   1.2506   0.02804   0.01967  -0.0507   0.3420   1.0000
  10.000   1.2441   0.02938   0.02093  -0.0465   0.3135   1.0000
  10.250   1.2319   0.03126   0.02264  -0.0420   0.2750   1.0000
  10.500   1.2151   0.03379   0.02491  -0.0378   0.2314   1.0000
  10.750   1.1942   0.03702   0.02786  -0.0339   0.1867   1.0000
  11.000   1.1636   0.04150   0.03195  -0.0304   0.1325   1.0000
  11.250   1.1381   0.04604   0.03622  -0.0280   0.0853   1.0000
  11.500   1.1147   0.05077   0.04072  -0.0262   0.0570   1.0000
  11.750   1.1036   0.05451   0.04445  -0.0251   0.0489   1.0000
  12.000   1.0975   0.05784   0.04786  -0.0243   0.0450   1.0000
  12.250   1.0895   0.06151   0.05160  -0.0236   0.0415   1.0000
  12.500   1.0826   0.06516   0.05533  -0.0231   0.0392   1.0000
  12.750   1.0784   0.06857   0.05888  -0.0227   0.0370   1.0000
  13.000   1.0746   0.07201   0.06246  -0.0225   0.0358   1.0000
  13.250   1.0688   0.07578   0.06635  -0.0223   0.0344   1.0000
  13.500   1.0640   0.07948   0.07018  -0.0223   0.0336   1.0000
  13.750   1.0583   0.08334   0.07415  -0.0224   0.0327   1.0000
  14.000   1.0518   0.08735   0.07825  -0.0225   0.0319   1.0000
  14.250   1.0483   0.09094   0.08193  -0.0226   0.0310   1.0000
  14.500   1.0490   0.09395   0.08506  -0.0225   0.0298   1.0000
  14.750   1.0508   0.09674   0.08798  -0.0224   0.0289   1.0000
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