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USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 35 A AIRFOIL (usa35a-il)
Reynolds number: 200,000
Max Cl/Cd: 67.06 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35a-il-200000-n5.txt
Download as CSV file: xf-usa35a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 A 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   0.0000   0.09385   0.08927  -0.0888   0.8087   0.0410
  -9.500   0.0026   0.09032   0.08569  -0.0904   0.7987   0.0410
  -9.250   0.0041   0.08660   0.08193  -0.0922   0.7895   0.0414
  -9.000   0.0040   0.08250   0.07780  -0.0944   0.7797   0.0417
  -8.750   0.0024   0.07818   0.07342  -0.0967   0.7708   0.0418
  -8.500  -0.0004   0.07355   0.06878  -0.0995   0.7611   0.0417
  -8.250  -0.1813   0.02982   0.02314  -0.1332   0.7571   0.0426
  -8.000  -0.1600   0.02881   0.02199  -0.1329   0.7482   0.0431
  -7.750  -0.1370   0.02816   0.02128  -0.1326   0.7380   0.0435
  -7.250  -0.0921   0.02633   0.01912  -0.1319   0.7181   0.0448
  -7.000  -0.0701   0.02509   0.01757  -0.1315   0.7081   0.0456
  -6.750  -0.0481   0.02370   0.01585  -0.1311   0.6971   0.0465
  -6.500  -0.0246   0.02262   0.01445  -0.1307   0.6868   0.0473
  -6.250   0.0008   0.02213   0.01392  -0.1303   0.6759   0.0479
  -6.000   0.0263   0.02166   0.01332  -0.1300   0.6661   0.0485
  -5.750   0.0519   0.02112   0.01267  -0.1296   0.6559   0.0494
  -5.500   0.0775   0.02054   0.01189  -0.1293   0.6466   0.0506
  -5.250   0.1034   0.01995   0.01109  -0.1289   0.6375   0.0520
  -5.000   0.1297   0.01968   0.01079  -0.1286   0.6284   0.0530
  -4.750   0.1562   0.01939   0.01041  -0.1283   0.6201   0.0543
  -4.500   0.1826   0.01900   0.00989  -0.1280   0.6120   0.0558
  -4.250   0.2092   0.01862   0.00935  -0.1277   0.6053   0.0573
  -4.000   0.2361   0.01836   0.00910  -0.1275   0.5989   0.0585
  -3.750   0.2630   0.01811   0.00878  -0.1272   0.5923   0.0603
  -3.500   0.2900   0.01787   0.00840  -0.1270   0.5863   0.0625
  -3.250   0.3169   0.01770   0.00823  -0.1268   0.5803   0.0644
  -3.000   0.3437   0.01751   0.00798  -0.1265   0.5732   0.0668
  -2.750   0.3702   0.01733   0.00770  -0.1261   0.5660   0.0690
  -2.500   0.3970   0.01719   0.00754  -0.1258   0.5596   0.0715
  -2.250   0.4241   0.01706   0.00734  -0.1256   0.5538   0.0746
  -2.000   0.4511   0.01692   0.00722  -0.1254   0.5490   0.0773
  -1.750   0.4783   0.01684   0.00706  -0.1252   0.5445   0.0810
  -1.500   0.5054   0.01673   0.00695  -0.1250   0.5403   0.0843
  -1.250   0.5327   0.01664   0.00686  -0.1249   0.5359   0.0884
  -1.000   0.5599   0.01653   0.00679  -0.1247   0.5317   0.0926
  -0.750   0.5871   0.01649   0.00670  -0.1245   0.5275   0.0976
  -0.500   0.6142   0.01643   0.00663  -0.1244   0.5235   0.1032
  -0.250   0.6415   0.01640   0.00659  -0.1242   0.5196   0.1101
   0.000   0.6684   0.01632   0.00659  -0.1240   0.5153   0.1195
   0.250   0.6952   0.01625   0.00660  -0.1239   0.5109   0.1350
   0.500   0.7220   0.01618   0.00667  -0.1237   0.5069   0.1703
   0.750   0.7489   0.01614   0.00672  -0.1236   0.5031   0.2177
   1.000   0.7760   0.01612   0.00678  -0.1235   0.4995   0.2664
   1.250   0.8016   0.01593   0.00694  -0.1233   0.4952   0.3503
   1.500   0.8266   0.01574   0.00711  -0.1229   0.4906   0.4677
   1.750   0.8504   0.01551   0.00725  -0.1221   0.4861   0.5823
   2.000   0.8674   0.01510   0.00745  -0.1193   0.4821   0.8172
   2.250   0.9055   0.01509   0.00751  -0.1210   0.4778   1.0000
   2.500   0.9304   0.01525   0.00766  -0.1204   0.4732   1.0000
   2.750   0.9554   0.01543   0.00779  -0.1199   0.4684   1.0000
   3.000   0.9803   0.01563   0.00790  -0.1194   0.4639   1.0000
   3.250   1.0053   0.01585   0.00800  -0.1189   0.4597   1.0000
   3.500   1.0293   0.01604   0.00819  -0.1182   0.4545   1.0000
   3.750   1.0530   0.01624   0.00837  -0.1175   0.4488   1.0000
   4.000   1.0764   0.01646   0.00851  -0.1168   0.4436   1.0000
   4.250   1.0997   0.01669   0.00868  -0.1160   0.4388   1.0000
   4.500   1.1225   0.01692   0.00892  -0.1152   0.4331   1.0000
   4.750   1.1447   0.01717   0.00913  -0.1143   0.4276   1.0000
   5.000   1.1661   0.01743   0.00932  -0.1132   0.4225   1.0000
   5.250   1.1870   0.01770   0.00960  -0.1121   0.4160   1.0000
   5.500   1.2052   0.01798   0.00984  -0.1105   0.4092   1.0000
   5.750   1.2225   0.01829   0.01010  -0.1088   0.4029   1.0000
   6.000   1.2403   0.01863   0.01044  -0.1073   0.3957   1.0000
   6.250   1.2572   0.01902   0.01077  -0.1056   0.3893   1.0000
   6.500   1.2752   0.01943   0.01116  -0.1042   0.3833   1.0000
   6.750   1.2924   0.01988   0.01159  -0.1027   0.3769   1.0000
   7.000   1.3085   0.02038   0.01203  -0.1011   0.3713   1.0000
   7.250   1.3258   0.02089   0.01253  -0.0998   0.3656   1.0000
   7.500   1.3421   0.02144   0.01307  -0.0984   0.3598   1.0000
   7.750   1.3569   0.02206   0.01364  -0.0968   0.3543   1.0000
   8.000   1.3732   0.02267   0.01425  -0.0955   0.3492   1.0000
   8.250   1.3889   0.02332   0.01491  -0.0941   0.3440   1.0000
   8.500   1.4037   0.02403   0.01559  -0.0927   0.3393   1.0000
   8.750   1.4184   0.02478   0.01630  -0.0914   0.3352   1.0000
   9.000   1.4342   0.02550   0.01707  -0.0902   0.3310   1.0000
   9.250   1.4489   0.02628   0.01788  -0.0890   0.3268   1.0000
   9.500   1.4628   0.02712   0.01872  -0.0878   0.3229   1.0000
   9.750   1.4762   0.02801   0.01958  -0.0865   0.3193   1.0000
  10.000   1.4906   0.02889   0.02051  -0.0854   0.3157   1.0000
  10.250   1.5037   0.02984   0.02152  -0.0843   0.3118   1.0000
  10.500   1.5157   0.03088   0.02259  -0.0830   0.3078   1.0000
  10.750   1.5269   0.03198   0.02367  -0.0818   0.3039   1.0000
  11.000   1.5384   0.03309   0.02480  -0.0806   0.3003   1.0000
  11.250   1.5488   0.03432   0.02613  -0.0795   0.2961   1.0000
  11.500   1.5583   0.03562   0.02748  -0.0784   0.2919   1.0000
  11.750   1.5670   0.03699   0.02886  -0.0772   0.2880   1.0000
  12.000   1.5761   0.03834   0.03020  -0.0761   0.2844   1.0000
  12.250   1.5840   0.03990   0.03189  -0.0752   0.2804   1.0000
  12.500   1.5910   0.04155   0.03361  -0.0742   0.2760   1.0000
  12.750   1.5969   0.04329   0.03539  -0.0732   0.2718   1.0000
  13.000   1.6031   0.04503   0.03713  -0.0723   0.2680   1.0000
  13.250   1.6078   0.04707   0.03930  -0.0715   0.2634   1.0000
  13.500   1.6108   0.04925   0.04155  -0.0707   0.2586   1.0000
  13.750   1.6138   0.05143   0.04374  -0.0700   0.2541   1.0000
  14.000   1.6159   0.05385   0.04625  -0.0694   0.2493   1.0000
  14.250   1.6159   0.05653   0.04902  -0.0688   0.2439   1.0000
  14.500   1.6159   0.05918   0.05168  -0.0683   0.2390   1.0000
  14.750   1.6158   0.06197   0.05457  -0.0679   0.2339   1.0000
  15.000   1.6141   0.06499   0.05765  -0.0676   0.2287   1.0000
  15.250   1.6128   0.06791   0.06057  -0.0672   0.2242   1.0000
  15.500   1.6114   0.07100   0.06377  -0.0671   0.2192   1.0000
  15.750   1.6088   0.07419   0.06702  -0.0669   0.2145   1.0000
  16.000   1.6081   0.07711   0.06993  -0.0668   0.2106   1.0000
  16.250   1.6062   0.08031   0.07323  -0.0668   0.2065   1.0000
  16.500   1.6050   0.08341   0.07639  -0.0668   0.2026   1.0000
  16.750   1.6046   0.08637   0.07935  -0.0668   0.1992   1.0000
  17.000   1.6058   0.08911   0.08212  -0.0668   0.1962   1.0000
  17.250   1.6037   0.09237   0.08549  -0.0670   0.1929   1.0000
  17.500   1.6031   0.09543   0.08860  -0.0672   0.1897   1.0000
  17.750   1.6043   0.09820   0.09136  -0.0674   0.1868   1.0000
  18.000   1.6081   0.10059   0.09375  -0.0676   0.1842   1.0000
  18.250   1.6054   0.10403   0.09732  -0.0681   0.1814   1.0000
  18.500   1.6031   0.10739   0.10076  -0.0686   0.1785   1.0000
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