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

USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 29 AIRFOIL (usa29-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.1 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa29-il-1000000.txt
Download as CSV file: xf-usa29-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6833   0.08669   0.08468  -0.0713   1.0000   0.0183
 -15.250  -0.7507   0.07478   0.07267  -0.0767   1.0000   0.0181
 -15.000  -0.8135   0.06551   0.06332  -0.0797   1.0000   0.0176
 -14.750  -0.9479   0.04285   0.04031  -0.1014   0.9908   0.0161
 -14.500  -0.9656   0.03270   0.02981  -0.1109   0.9841   0.0163
 -14.250  -0.9535   0.02834   0.02525  -0.1144   0.9807   0.0169
 -14.000  -0.9348   0.02597   0.02275  -0.1158   0.9768   0.0176
 -13.750  -0.9096   0.02413   0.02076  -0.1176   0.9746   0.0183
 -13.500  -0.8841   0.02234   0.01881  -0.1193   0.9727   0.0193
 -13.250  -0.8543   0.02128   0.01771  -0.1210   0.9714   0.0204
 -13.000  -0.8213   0.02060   0.01698  -0.1228   0.9704   0.0215
 -12.750  -0.7915   0.01998   0.01627  -0.1239   0.9679   0.0225
 -12.500  -0.7685   0.01920   0.01541  -0.1238   0.9628   0.0235
 -12.250  -0.7377   0.01879   0.01500  -0.1249   0.9597   0.0246
 -12.000  -0.7043   0.01849   0.01467  -0.1264   0.9573   0.0255
 -11.750  -0.6710   0.01821   0.01433  -0.1278   0.9541   0.0265
 -11.500  -0.6484   0.01797   0.01402  -0.1269   0.9473   0.0272
 -11.250  -0.6201   0.01758   0.01352  -0.1274   0.9423   0.0278
 -11.000  -0.6002   0.01690   0.01280  -0.1264   0.9356   0.0289
 -10.750  -0.5760   0.01667   0.01253  -0.1258   0.9293   0.0296
 -10.500  -0.5454   0.01668   0.01251  -0.1264   0.9247   0.0304
 -10.250  -0.5235   0.01650   0.01229  -0.1253   0.9175   0.0311
 -10.000  -0.4981   0.01630   0.01202  -0.1249   0.9113   0.0319
  -9.750  -0.4728   0.01623   0.01187  -0.1245   0.9050   0.0327
  -9.500  -0.4491   0.01604   0.01160  -0.1237   0.8979   0.0331
  -9.250  -0.4283   0.01545   0.01088  -0.1225   0.8911   0.0337
  -9.000  -0.4115   0.01461   0.00994  -0.1207   0.8830   0.0347
  -8.750  -0.3877   0.01432   0.00960  -0.1200   0.8766   0.0354
  -8.500  -0.3634   0.01425   0.00950  -0.1193   0.8690   0.0362
  -8.000  -0.3156   0.01382   0.00894  -0.1178   0.8550   0.0378
  -7.750  -0.2918   0.01357   0.00860  -0.1170   0.8477   0.0385
  -7.500  -0.2682   0.01333   0.00829  -0.1161   0.8405   0.0392
  -7.250  -0.2438   0.01317   0.00804  -0.1153   0.8330   0.0398
  -7.000  -0.2195   0.01298   0.00778  -0.1146   0.8256   0.0401
  -6.750  -0.1974   0.01251   0.00721  -0.1134   0.8175   0.0406
  -6.500  -0.1788   0.01160   0.00620  -0.1117   0.8096   0.0420
  -6.250  -0.1560   0.01126   0.00579  -0.1107   0.8012   0.0428
  -6.000  -0.1325   0.01097   0.00546  -0.1098   0.7925   0.0434
  -5.750  -0.1090   0.01074   0.00515  -0.1088   0.7830   0.0441
  -5.500  -0.0853   0.01051   0.00486  -0.1079   0.7720   0.0449
  -5.250  -0.0616   0.01030   0.00459  -0.1070   0.7602   0.0457
  -5.000  -0.0382   0.01013   0.00434  -0.1060   0.7463   0.0466
  -4.750  -0.0154   0.00996   0.00407  -0.1048   0.7295   0.0473
  -4.500   0.0072   0.00985   0.00386  -0.1036   0.7101   0.0479
  -4.000   0.0520   0.00973   0.00351  -0.1011   0.6725   0.0488
  -3.750   0.0738   0.00952   0.00318  -0.0998   0.6572   0.0499
  -3.500   0.0967   0.00933   0.00290  -0.0987   0.6446   0.0515
  -3.250   0.1209   0.00920   0.00271  -0.0979   0.6346   0.0530
  -3.000   0.1449   0.00912   0.00256  -0.0970   0.6256   0.0547
  -2.750   0.1700   0.00903   0.00242  -0.0964   0.6175   0.0561
  -2.500   0.1944   0.00898   0.00231  -0.0956   0.6100   0.0575
  -2.250   0.2200   0.00891   0.00220  -0.0951   0.6033   0.0588
  -2.000   0.2446   0.00885   0.00210  -0.0943   0.5969   0.0620
  -1.750   0.2699   0.00875   0.00201  -0.0938   0.5911   0.0680
  -1.500   0.2947   0.00860   0.00196  -0.0931   0.5850   0.0953
  -1.250   0.3187   0.00855   0.00192  -0.0923   0.5789   0.1139
  -1.000   0.3441   0.00842   0.00187  -0.0918   0.5738   0.1323
  -0.750   0.3679   0.00827   0.00184  -0.0910   0.5682   0.1747
  -0.500   0.3913   0.00824   0.00184  -0.0900   0.5626   0.2005
  -0.250   0.4163   0.00817   0.00183  -0.0894   0.5575   0.2190
   0.000   0.4401   0.00813   0.00183  -0.0885   0.5521   0.2375
   0.250   0.4629   0.00813   0.00186  -0.0875   0.5467   0.2591
   0.500   0.4875   0.00809   0.00191  -0.0868   0.5419   0.2838
   0.750   0.5117   0.00812   0.00197  -0.0860   0.5363   0.3031
   1.000   0.5352   0.00820   0.00203  -0.0850   0.5308   0.3149
   1.250   0.5607   0.00824   0.00207  -0.0845   0.5261   0.3238
   1.500   0.5849   0.00830   0.00212  -0.0837   0.5206   0.3301
   1.750   0.6079   0.00839   0.00219  -0.0827   0.5152   0.3359
   2.000   0.6334   0.00845   0.00224  -0.0822   0.5102   0.3417
   2.250   0.6570   0.00851   0.00232  -0.0813   0.5049   0.3476
   2.500   0.6796   0.00863   0.00240  -0.0801   0.4996   0.3529
   2.750   0.7045   0.00868   0.00246  -0.0795   0.4948   0.3568
   3.000   0.7271   0.00873   0.00252  -0.0785   0.4895   0.3602
   3.250   0.7477   0.00882   0.00259  -0.0769   0.4842   0.3632
   3.500   0.7705   0.00886   0.00265  -0.0759   0.4797   0.3662
   3.750   0.7917   0.00892   0.00271  -0.0745   0.4745   0.3689
   4.000   0.8113   0.00903   0.00279  -0.0728   0.4694   0.3712
   4.250   0.8337   0.00909   0.00286  -0.0717   0.4651   0.3731
   4.500   0.8546   0.00912   0.00292  -0.0703   0.4601   0.3764
   4.750   0.8744   0.00924   0.00304  -0.0686   0.4551   0.3792
   5.000   0.8956   0.00933   0.00314  -0.0673   0.4506   0.3814
   5.250   0.9170   0.00943   0.00325  -0.0661   0.4442   0.3850
   5.500   0.9357   0.00959   0.00338  -0.0643   0.4367   0.3868
   5.750   0.9566   0.00966   0.00348  -0.0629   0.4292   0.3901
   6.000   0.9742   0.00983   0.00364  -0.0610   0.4217   0.3931
   6.250   0.9956   0.00992   0.00376  -0.0598   0.4144   0.3956
   6.500   1.0134   0.01011   0.00393  -0.0579   0.4061   0.3982
   6.750   1.0344   0.01024   0.00407  -0.0567   0.3987   0.4008
   7.000   1.0519   0.01043   0.00425  -0.0548   0.3897   0.4032
   7.250   1.0706   0.01059   0.00442  -0.0531   0.3798   0.4051
   7.500   1.0873   0.01082   0.00463  -0.0511   0.3663   0.4075
   7.750   1.1019   0.01113   0.00489  -0.0488   0.3491   0.4096
   8.000   1.1139   0.01156   0.00521  -0.0461   0.3251   0.4117
   8.250   1.1182   0.01227   0.00572  -0.0421   0.2866   0.4135
   8.500   1.1079   0.01360   0.00665  -0.0358   0.2204   0.4148
   8.750   1.0862   0.01546   0.00805  -0.0281   0.1433   0.4156
   9.000   1.0612   0.01763   0.00980  -0.0204   0.0638   0.4160
   9.250   1.0548   0.01913   0.01114  -0.0158   0.0286   0.4178
   9.500   1.0644   0.01990   0.01195  -0.0136   0.0241   0.4208
   9.750   1.0742   0.02071   0.01279  -0.0115   0.0217   0.4234
  10.000   1.0836   0.02158   0.01370  -0.0095   0.0199   0.4266
  10.250   1.0953   0.02235   0.01453  -0.0078   0.0192   0.4303
  10.500   1.1061   0.02322   0.01545  -0.0061   0.0183   0.4359
  10.750   1.1140   0.02430   0.01660  -0.0043   0.0170   0.4440
  11.000   1.1198   0.02559   0.01806  -0.0025   0.0160   0.4922
  11.250   1.3005   0.02803   0.02167  -0.0394   0.0136   1.0000
  11.500   1.3038   0.02961   0.02330  -0.0374   0.0132   1.0000
  11.750   1.2980   0.03203   0.02582  -0.0349   0.0127   1.0000
  12.000   1.2984   0.03408   0.02794  -0.0331   0.0126   1.0000
  12.250   1.3061   0.03557   0.02948  -0.0319   0.0123   1.0000
  12.500   1.3085   0.03761   0.03159  -0.0306   0.0121   1.0000
  12.750   1.3082   0.03999   0.03406  -0.0293   0.0121   1.0000
  13.000   1.3159   0.04166   0.03577  -0.0285   0.0115   1.0000
  13.250   1.3174   0.04399   0.03816  -0.0276   0.0112   1.0000
  13.500   1.3166   0.04663   0.04087  -0.0266   0.0110   1.0000
  13.750   1.3209   0.04876   0.04304  -0.0260   0.0108   1.0000
  14.000   1.3221   0.05127   0.04560  -0.0254   0.0106   1.0000
  14.250   1.3198   0.05421   0.04861  -0.0247   0.0104   1.0000
  14.500   1.3153   0.05741   0.05189  -0.0241   0.0103   1.0000
  14.750   1.3119   0.06056   0.05511  -0.0236   0.0101   1.0000
  15.000   1.2997   0.06476   0.05939  -0.0231   0.0098   1.0000
  15.250   1.2946   0.06816   0.06287  -0.0227   0.0096   1.0000
  15.500   1.2914   0.07137   0.06614  -0.0224   0.0096   1.0000
  15.750   1.2938   0.07399   0.06882  -0.0222   0.0095   1.0000
  16.000   1.2944   0.07686   0.07175  -0.0221   0.0094   1.0000
  16.250   1.2958   0.07963   0.07460  -0.0220   0.0092   1.0000
  16.500   1.2959   0.08256   0.07759  -0.0220   0.0091   1.0000
  16.750   1.2961   0.08549   0.08058  -0.0219   0.0089   1.0000
<< Back to USA 29 AIRFOIL (usa29-il)

Polar data table (+)

Polar graphs


<< Back to USA 29 AIRFOIL (usa29-il)