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USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 29 AIRFOIL (usa29-il)
Reynolds number: 500,000
Max Cl/Cd: 89.96 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa29-il-500000.txt
Download as CSV file: xf-usa29-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2422   0.10995   0.10765  -0.0622   0.9896   0.0370
 -11.000  -0.5381   0.03603   0.03303  -0.1216   0.9659   0.0323
 -10.750  -0.5242   0.03305   0.02963  -0.1241   0.9602   0.0333
 -10.500  -0.5089   0.02949   0.02585  -0.1262   0.9571   0.0345
 -10.250  -0.4736   0.02934   0.02573  -0.1283   0.9557   0.0355
 -10.000  -0.4516   0.02898   0.02536  -0.1278   0.9498   0.0365
  -9.750  -0.4298   0.02772   0.02394  -0.1281   0.9448   0.0376
  -9.500  -0.4059   0.02632   0.02228  -0.1287   0.9409   0.0390
  -9.250  -0.3894   0.02575   0.02149  -0.1271   0.9334   0.0399
  -9.000  -0.3784   0.02337   0.01877  -0.1256   0.9268   0.0411
  -8.750  -0.3594   0.02217   0.01752  -0.1246   0.9209   0.0422
  -8.500  -0.3396   0.02153   0.01680  -0.1235   0.9140   0.0432
  -8.250  -0.3134   0.02097   0.01618  -0.1235   0.9093   0.0446
  -8.000  -0.2960   0.02031   0.01539  -0.1216   0.9014   0.0456
  -7.750  -0.2735   0.01956   0.01447  -0.1208   0.8953   0.0468
  -7.500  -0.2526   0.01898   0.01373  -0.1195   0.8882   0.0477
  -7.250  -0.2300   0.01851   0.01310  -0.1185   0.8812   0.0484
  -7.000  -0.2067   0.01809   0.01252  -0.1175   0.8743   0.0489
  -6.750  -0.1907   0.01605   0.01026  -0.1157   0.8662   0.0503
  -6.500  -0.1678   0.01520   0.00933  -0.1148   0.8590   0.0515
  -6.250  -0.1453   0.01462   0.00866  -0.1138   0.8506   0.0524
  -6.000  -0.1214   0.01410   0.00805  -0.1130   0.8426   0.0533
  -5.750  -0.0977   0.01362   0.00747  -0.1120   0.8338   0.0543
  -5.500  -0.0742   0.01322   0.00699  -0.1111   0.8247   0.0554
  -5.250  -0.0492   0.01285   0.00650  -0.1104   0.8157   0.0566
  -5.000  -0.0264   0.01248   0.00606  -0.1093   0.8051   0.0574
  -4.750  -0.0025   0.01215   0.00563  -0.1083   0.7947   0.0582
  -4.500   0.0219   0.01189   0.00526  -0.1075   0.7835   0.0588
  -4.250   0.0439   0.01148   0.00476  -0.1061   0.7705   0.0600
  -4.000   0.0661   0.01111   0.00431  -0.1049   0.7567   0.0616
  -3.750   0.0890   0.01085   0.00398  -0.1037   0.7419   0.0637
  -3.500   0.1121   0.01067   0.00372  -0.1026   0.7263   0.0659
  -3.250   0.1354   0.01053   0.00347  -0.1016   0.7106   0.0679
  -3.000   0.1588   0.01042   0.00326  -0.1005   0.6955   0.0699
  -2.750   0.1822   0.01029   0.00307  -0.0995   0.6817   0.0742
  -2.500   0.2060   0.01020   0.00294  -0.0986   0.6695   0.0815
  -2.250   0.2299   0.01010   0.00283  -0.0977   0.6590   0.1002
  -2.000   0.2543   0.00996   0.00272  -0.0970   0.6493   0.1235
  -1.750   0.2783   0.00980   0.00264  -0.0962   0.6407   0.1580
  -1.500   0.3024   0.00971   0.00263  -0.0955   0.6322   0.1962
  -1.250   0.3267   0.00969   0.00261  -0.0947   0.6250   0.2195
  -1.000   0.3509   0.00965   0.00263  -0.0940   0.6178   0.2411
  -0.750   0.3752   0.00970   0.00265  -0.0932   0.6112   0.2612
  -0.500   0.3997   0.00971   0.00272  -0.0925   0.6046   0.2815
  -0.250   0.4242   0.00980   0.00281  -0.0917   0.5981   0.2992
   0.000   0.4493   0.00992   0.00290  -0.0911   0.5922   0.3135
   0.250   0.4741   0.01001   0.00297  -0.0904   0.5860   0.3246
   0.500   0.4988   0.01014   0.00306  -0.0897   0.5802   0.3324
   0.750   0.5235   0.01026   0.00314  -0.0890   0.5743   0.3413
   1.000   0.5477   0.01034   0.00322  -0.0882   0.5686   0.3474
   1.250   0.5725   0.01050   0.00331  -0.0875   0.5633   0.3546
   1.500   0.5964   0.01056   0.00339  -0.0867   0.5577   0.3609
   1.750   0.6200   0.01066   0.00348  -0.0858   0.5519   0.3679
   2.000   0.6444   0.01080   0.00355  -0.0851   0.5467   0.3740
   2.250   0.6680   0.01080   0.00361  -0.0842   0.5413   0.3784
   2.500   0.6915   0.01087   0.00367  -0.0833   0.5358   0.3831
   2.750   0.7157   0.01101   0.00373  -0.0826   0.5307   0.3870
   3.000   0.7386   0.01098   0.00377  -0.0816   0.5253   0.3906
   3.250   0.7618   0.01102   0.00383  -0.0807   0.5201   0.3943
   3.500   0.7854   0.01115   0.00391  -0.0799   0.5150   0.3988
   3.750   0.8078   0.01117   0.00399  -0.0788   0.5099   0.4033
   4.000   0.8297   0.01120   0.00405  -0.0776   0.5046   0.4081
   4.250   0.8530   0.01132   0.00414  -0.0767   0.4998   0.4122
   4.500   0.8746   0.01137   0.00424  -0.0755   0.4947   0.4159
   4.750   0.8957   0.01140   0.00431  -0.0742   0.4896   0.4194
   5.000   0.9176   0.01151   0.00441  -0.0731   0.4847   0.4227
   5.250   0.9380   0.01156   0.00453  -0.0716   0.4800   0.4262
   5.500   0.9572   0.01163   0.00463  -0.0699   0.4749   0.4304
   5.750   0.9760   0.01172   0.00472  -0.0681   0.4696   0.4352
   6.000   0.9916   0.01176   0.00483  -0.0656   0.4628   0.4394
   6.250   1.0064   0.01188   0.00494  -0.0630   0.4547   0.4435
   6.500   1.0225   0.01198   0.00510  -0.0608   0.4468   0.4467
   6.750   1.0377   0.01213   0.00525  -0.0583   0.4390   0.4506
   7.000   1.0549   0.01224   0.00544  -0.0563   0.4317   0.4554
   7.250   1.0700   0.01242   0.00563  -0.0540   0.4235   0.4612
   7.500   1.0860   0.01254   0.00585  -0.0518   0.4147   0.4737
   7.750   1.0931   0.01241   0.00608  -0.0479   0.4060   0.6589
   8.000   1.2613   0.01402   0.00794  -0.0814   0.2972   0.9998
   8.250   1.2439   0.01564   0.00908  -0.0739   0.2214   1.0000
   8.500   1.2142   0.01795   0.01084  -0.0649   0.1333   1.0000
   8.750   1.1880   0.02039   0.01286  -0.0573   0.0554   1.0000
   9.000   1.1835   0.02193   0.01431  -0.0530   0.0346   1.0000
   9.250   1.1887   0.02303   0.01545  -0.0502   0.0299   1.0000
   9.500   1.1954   0.02409   0.01656  -0.0477   0.0280   1.0000
   9.750   1.1977   0.02551   0.01803  -0.0449   0.0259   1.0000
  10.000   1.2027   0.02681   0.01941  -0.0425   0.0247   1.0000
  10.250   1.2085   0.02811   0.02078  -0.0404   0.0238   1.0000
  10.500   1.2131   0.02958   0.02231  -0.0383   0.0230   1.0000
  10.750   1.2152   0.03129   0.02409  -0.0362   0.0221   1.0000
  11.000   1.2163   0.03317   0.02603  -0.0343   0.0214   1.0000
  11.250   1.2118   0.03566   0.02860  -0.0322   0.0207   1.0000
  11.500   1.2035   0.03863   0.03167  -0.0302   0.0202   1.0000
  11.750   1.2072   0.04063   0.03375  -0.0290   0.0198   1.0000
  12.000   1.2100   0.04279   0.03598  -0.0279   0.0194   1.0000
  12.250   1.2118   0.04509   0.03835  -0.0269   0.0187   1.0000
  12.500   1.2106   0.04777   0.04111  -0.0259   0.0184   1.0000
  12.750   1.2081   0.05064   0.04405  -0.0250   0.0183   1.0000
  13.000   1.2102   0.05307   0.04654  -0.0244   0.0176   1.0000
  13.250   1.2085   0.05591   0.04943  -0.0236   0.0172   1.0000
  13.500   1.2064   0.05884   0.05241  -0.0230   0.0169   1.0000
  13.750   1.2038   0.06181   0.05543  -0.0223   0.0166   1.0000
  14.000   1.2013   0.06471   0.05838  -0.0215   0.0164   1.0000
  14.250   1.1983   0.06736   0.06105  -0.0201   0.0160   1.0000
  14.500   1.2036   0.06954   0.06330  -0.0197   0.0158   1.0000
  14.750   1.2089   0.07159   0.06540  -0.0190   0.0157   1.0000
  15.000   1.2144   0.07374   0.06762  -0.0185   0.0153   1.0000
  15.250   1.2193   0.07603   0.06999  -0.0183   0.0147   1.0000
  15.500   1.2265   0.07771   0.07171  -0.0174   0.0146   1.0000
  15.750   1.2315   0.07997   0.07402  -0.0172   0.0142   1.0000
  16.000   1.2386   0.08176   0.07586  -0.0166   0.0139   1.0000
  16.250   1.2451   0.08371   0.07784  -0.0161   0.0136   1.0000
  16.500   1.2526   0.08545   0.07961  -0.0155   0.0134   1.0000
  16.750   1.2613   0.08691   0.08109  -0.0147   0.0131   1.0000
  17.000   1.2905   0.08475   0.07886  -0.0107   0.0126   1.0000
  17.250   1.2951   0.08707   0.08130  -0.0104   0.0125   1.0000
  17.500   1.2962   0.08995   0.08432  -0.0104   0.0124   1.0000
  17.750   1.2953   0.09316   0.08769  -0.0107   0.0122   1.0000
  18.000   1.2990   0.09563   0.09028  -0.0104   0.0122   1.0000
  18.250   1.2989   0.09871   0.09352  -0.0104   0.0120   1.0000
  18.500   1.2993   0.10174   0.09670  -0.0104   0.0120   1.0000
  18.750   1.2944   0.10567   0.10081  -0.0110   0.0118   1.0000
  19.000   1.2909   0.10938   0.10467  -0.0115   0.0119   1.0000
  19.250   1.2823   0.11400   0.10947  -0.0127   0.0117   1.0000
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