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USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 35 AIRFOIL (usa35-il)
Reynolds number: 200,000
Max Cl/Cd: 67 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35-il-200000-n5.txt
Download as CSV file: xf-usa35-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0003   0.09393   0.08935  -0.0888   0.8092   0.0417
  -9.500   0.0029   0.09041   0.08578  -0.0903   0.7994   0.0415
  -9.250   0.0049   0.08673   0.08206  -0.0921   0.7900   0.0414
  -9.000   0.0059   0.08290   0.07819  -0.0940   0.7800   0.0418
  -8.750   0.0041   0.07853   0.07378  -0.0965   0.7709   0.0422
  -8.500  -0.0006   0.07356   0.06878  -0.0996   0.7610   0.0424
  -8.250  -0.1779   0.03067   0.02408  -0.1330   0.7575   0.0432
  -8.000  -0.1574   0.02955   0.02283  -0.1327   0.7484   0.0436
  -7.750  -0.1349   0.02885   0.02204  -0.1324   0.7379   0.0440
  -7.500  -0.1124   0.02803   0.02107  -0.1321   0.7281   0.0445
  -7.250  -0.0904   0.02703   0.01989  -0.1317   0.7170   0.0453
  -7.000  -0.0689   0.02572   0.01828  -0.1314   0.7072   0.0462
  -6.750  -0.0476   0.02416   0.01634  -0.1309   0.6966   0.0472
  -6.500  -0.0240   0.02312   0.01502  -0.1305   0.6869   0.0479
  -6.250   0.0012   0.02261   0.01444  -0.1302   0.6761   0.0485
  -6.000   0.0266   0.02209   0.01380  -0.1298   0.6666   0.0492
  -5.750   0.0520   0.02151   0.01309  -0.1295   0.6562   0.0500
  -5.500   0.0775   0.02089   0.01225  -0.1291   0.6468   0.0511
  -5.250   0.1032   0.02025   0.01137  -0.1287   0.6369   0.0525
  -4.750   0.1559   0.01965   0.01068  -0.1282   0.6198   0.0547
  -4.500   0.1823   0.01927   0.01015  -0.1279   0.6123   0.0562
  -4.250   0.2090   0.01884   0.00954  -0.1275   0.6057   0.0576
  -4.000   0.2357   0.01855   0.00926  -0.1273   0.5987   0.0587
  -3.750   0.2625   0.01831   0.00895  -0.1270   0.5921   0.0602
  -3.500   0.2895   0.01808   0.00858  -0.1268   0.5866   0.0623
  -3.250   0.3164   0.01783   0.00833  -0.1266   0.5802   0.0641
  -3.000   0.3431   0.01765   0.00810  -0.1263   0.5731   0.0660
  -2.750   0.3697   0.01749   0.00780  -0.1259   0.5664   0.0683
  -2.500   0.3964   0.01727   0.00761  -0.1257   0.5595   0.0703
  -2.250   0.4232   0.01714   0.00744  -0.1254   0.5536   0.0729
  -2.000   0.4503   0.01702   0.00723  -0.1251   0.5490   0.0757
  -1.750   0.4774   0.01689   0.00711  -0.1250   0.5448   0.0784
  -1.500   0.5047   0.01678   0.00699  -0.1248   0.5404   0.0819
  -1.250   0.5318   0.01665   0.00689  -0.1247   0.5360   0.0851
  -1.000   0.5590   0.01659   0.00679  -0.1245   0.5316   0.0892
  -0.750   0.5861   0.01652   0.00670  -0.1243   0.5275   0.0935
  -0.250   0.6404   0.01640   0.00662  -0.1240   0.5194   0.1053
   0.000   0.6675   0.01634   0.00661  -0.1238   0.5153   0.1142
   0.250   0.6944   0.01629   0.00660  -0.1236   0.5113   0.1288
   0.500   0.7214   0.01623   0.00664  -0.1235   0.5073   0.1612
   0.750   0.7483   0.01617   0.00671  -0.1234   0.5035   0.2134
   1.000   0.7744   0.01607   0.00682  -0.1232   0.4991   0.2699
   1.250   0.8001   0.01592   0.00694  -0.1230   0.4945   0.3480
   1.500   0.8253   0.01572   0.00708  -0.1226   0.4902   0.4656
   1.750   0.8487   0.01544   0.00725  -0.1217   0.4864   0.6170
   2.000   0.8661   0.01507   0.00745  -0.1188   0.4829   0.8408
   2.250   0.9045   0.01507   0.00755  -0.1207   0.4781   1.0000
   2.500   0.9295   0.01524   0.00766  -0.1202   0.4733   1.0000
   2.750   0.9545   0.01543   0.00776  -0.1197   0.4685   1.0000
   3.000   0.9796   0.01565   0.00785  -0.1192   0.4642   1.0000
   3.250   1.0038   0.01583   0.00803  -0.1186   0.4590   1.0000
   3.500   1.0279   0.01603   0.00820  -0.1179   0.4537   1.0000
   3.750   1.0518   0.01624   0.00834  -0.1172   0.4488   1.0000
   4.000   1.0757   0.01647   0.00848  -0.1166   0.4445   1.0000
   4.250   1.0989   0.01669   0.00872  -0.1158   0.4389   1.0000
   4.500   1.1216   0.01692   0.00892  -0.1150   0.4334   1.0000
   4.750   1.1436   0.01717   0.00910  -0.1140   0.4282   1.0000
   5.000   1.1651   0.01742   0.00934  -0.1130   0.4221   1.0000
   5.250   1.1853   0.01769   0.00959  -0.1118   0.4154   1.0000
   5.500   1.2033   0.01798   0.00979  -0.1101   0.4094   1.0000
   5.750   1.2216   0.01828   0.01011  -0.1086   0.4025   1.0000
   6.000   1.2389   0.01863   0.01042  -0.1069   0.3958   1.0000
   6.250   1.2565   0.01902   0.01076  -0.1054   0.3898   1.0000
   6.500   1.2744   0.01942   0.01116  -0.1040   0.3833   1.0000
   6.750   1.2911   0.01988   0.01157  -0.1024   0.3775   1.0000
   7.000   1.3081   0.02036   0.01202  -0.1010   0.3717   1.0000
   7.250   1.3247   0.02088   0.01253  -0.0995   0.3654   1.0000
   7.500   1.3401   0.02146   0.01305  -0.0980   0.3598   1.0000
   7.750   1.3564   0.02204   0.01363  -0.0966   0.3545   1.0000
   8.000   1.3720   0.02266   0.01425  -0.0952   0.3487   1.0000
   8.250   1.3866   0.02336   0.01491  -0.0937   0.3436   1.0000
   8.500   1.4023   0.02404   0.01557  -0.0924   0.3396   1.0000
   8.750   1.4185   0.02472   0.01630  -0.0913   0.3355   1.0000
   9.000   1.4337   0.02546   0.01705  -0.0901   0.3313   1.0000
   9.250   1.4477   0.02627   0.01785  -0.0888   0.3272   1.0000
   9.500   1.4616   0.02712   0.01866  -0.0875   0.3235   1.0000
   9.750   1.4761   0.02797   0.01958  -0.0864   0.3195   1.0000
  10.000   1.4893   0.02889   0.02054  -0.0852   0.3152   1.0000
  10.250   1.5015   0.02989   0.02155  -0.0839   0.3112   1.0000
  10.500   1.5135   0.03092   0.02255  -0.0826   0.3075   1.0000
  10.750   1.5260   0.03196   0.02366  -0.0816   0.3040   1.0000
  11.000   1.5375   0.03309   0.02486  -0.0805   0.3000   1.0000
  11.250   1.5478   0.03431   0.02612  -0.0793   0.2961   1.0000
  11.500   1.5577   0.03556   0.02738  -0.0781   0.2924   1.0000
  11.750   1.5673   0.03686   0.02869  -0.0770   0.2889   1.0000
  12.000   1.5761   0.03831   0.03025  -0.0760   0.2848   1.0000
  12.250   1.5833   0.03988   0.03189  -0.0750   0.2804   1.0000
  12.500   1.5900   0.04150   0.03353  -0.0739   0.2762   1.0000
  12.750   1.5964   0.04321   0.03527  -0.0730   0.2722   1.0000
  13.000   1.6014   0.04516   0.03733  -0.0721   0.2675   1.0000
  13.250   1.6055   0.04718   0.03940  -0.0713   0.2627   1.0000
  13.500   1.6093   0.04922   0.04144  -0.0704   0.2585   1.0000
  13.750   1.6124   0.05150   0.04384  -0.0698   0.2538   1.0000
  14.000   1.6141   0.05394   0.04636  -0.0692   0.2488   1.0000
  14.250   1.6153   0.05642   0.04886  -0.0685   0.2442   1.0000
  14.500   1.6160   0.05908   0.05161  -0.0681   0.2393   1.0000
  14.750   1.6153   0.06193   0.05453  -0.0677   0.2341   1.0000
  15.000   1.6144   0.06477   0.05738  -0.0673   0.2295   1.0000
  15.250   1.6129   0.06782   0.06054  -0.0671   0.2244   1.0000
  15.500   1.6106   0.07096   0.06373  -0.0669   0.2193   1.0000
  15.750   1.6091   0.07397   0.06673  -0.0667   0.2150   1.0000
  16.000   1.6063   0.07726   0.07014  -0.0666   0.2103   1.0000
  16.250   1.6045   0.08041   0.07333  -0.0666   0.2060   1.0000
  16.500   1.6039   0.08336   0.07626  -0.0665   0.2025   1.0000
  16.750   1.6036   0.08636   0.07936  -0.0666   0.1991   1.0000
  17.000   1.6026   0.08945   0.08252  -0.0667   0.1958   1.0000
  17.250   1.6027   0.09237   0.08547  -0.0668   0.1928   1.0000
  17.500   1.6058   0.09484   0.08793  -0.0669   0.1901   1.0000
  17.750   1.6056   0.09787   0.09103  -0.0671   0.1874   1.0000
  18.000   1.6039   0.10113   0.09438  -0.0675   0.1844   1.0000
  18.250   1.6034   0.10420   0.09750  -0.0679   0.1814   1.0000
  18.500   1.6065   0.10670   0.09999  -0.0682   0.1786   1.0000
  18.750   1.6095   0.10922   0.10253  -0.0686   0.1760   1.0000
  19.000   1.6049   0.11298   0.10642  -0.0694   0.1732   1.0000
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