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USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 35 A AIRFOIL (usa35a-il)
Reynolds number: 200,000
Max Cl/Cd: 66.54 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35a-il-200000.txt
Download as CSV file: xf-usa35a-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0583   0.09521   0.09134  -0.0961   0.8894   0.0757
  -9.000   0.0648   0.09282   0.08890  -0.0961   0.8782   0.0773
  -8.750   0.0366   0.08779   0.08385  -0.1040   0.8635   0.0805
  -8.500   0.0547   0.08570   0.08172  -0.1015   0.8531   0.0810
  -8.250   0.0690   0.08372   0.07969  -0.1001   0.8412   0.0816
  -8.000   0.0801   0.08163   0.07757  -0.0997   0.8293   0.0827
  -7.750   0.0875   0.07925   0.07511  -0.1001   0.8179   0.0843
  -7.500   0.0535   0.07238   0.06824  -0.1118   0.8036   0.0882
  -7.250   0.0741   0.07095   0.06673  -0.1084   0.7935   0.0888
  -7.000   0.0886   0.06932   0.06509  -0.1071   0.7806   0.0896
  -6.750   0.0655   0.05955   0.05500  -0.1260   0.7697   0.0965
  -6.500   0.0850   0.05821   0.05371  -0.1234   0.7577   0.0969
  -6.250   0.1026   0.05708   0.05257  -0.1213   0.7463   0.0976
  -6.000   0.1194   0.05580   0.05123  -0.1201   0.7351   0.0990
  -5.750   0.1233   0.04941   0.04451  -0.1282   0.7254   0.1065
  -5.500   0.1059   0.03073   0.02400  -0.1340   0.7198   0.0738
  -5.250   0.1281   0.02848   0.02127  -0.1337   0.7116   0.0733
  -5.000   0.1501   0.02664   0.01915  -0.1333   0.7017   0.0738
  -4.750   0.1767   0.02609   0.01871  -0.1332   0.6931   0.0753
  -4.500   0.2018   0.02512   0.01754  -0.1330   0.6848   0.0769
  -4.250   0.2269   0.02387   0.01598  -0.1326   0.6764   0.0782
  -4.000   0.2541   0.02274   0.01443  -0.1324   0.6700   0.0794
  -3.750   0.2799   0.02180   0.01324  -0.1320   0.6626   0.0809
  -3.500   0.3067   0.02117   0.01263  -0.1319   0.6552   0.0829
  -3.000   0.3611   0.02014   0.01122  -0.1313   0.6406   0.0885
  -2.750   0.3881   0.01959   0.01067  -0.1311   0.6334   0.0912
  -2.500   0.4171   0.01925   0.01015  -0.1310   0.6276   0.0946
  -2.250   0.4432   0.01880   0.00972  -0.1307   0.6214   0.0982
  -2.000   0.4706   0.01850   0.00943  -0.1305   0.6156   0.1025
  -1.750   0.4988   0.01815   0.00898  -0.1304   0.6106   0.1068
  -1.500   0.5268   0.01794   0.00879  -0.1304   0.6058   0.1122
  -1.250   0.5530   0.01766   0.00855  -0.1300   0.6002   0.1177
  -1.000   0.5802   0.01746   0.00838  -0.1298   0.5948   0.1245
  -0.750   0.6083   0.01724   0.00816  -0.1298   0.5901   0.1322
  -0.500   0.6363   0.01714   0.00808  -0.1297   0.5855   0.1422
  -0.250   0.6623   0.01702   0.00808  -0.1294   0.5804   0.1556
   0.000   0.6894   0.01688   0.00806  -0.1292   0.5753   0.1797
   0.250   0.7169   0.01653   0.00799  -0.1292   0.5706   0.2543
   0.500   0.7430   0.01605   0.00815  -0.1292   0.5660   0.4555
   0.750   0.7607   0.01545   0.00842  -0.1271   0.5609   0.6881
   1.000   0.8028   0.01506   0.00850  -0.1287   0.5552   0.9970
   1.250   0.8308   0.01525   0.00851  -0.1286   0.5504   1.0000
   1.500   0.8593   0.01555   0.00862  -0.1287   0.5458   1.0000
   1.750   0.8824   0.01575   0.00881  -0.1279   0.5405   1.0000
   2.000   0.9078   0.01594   0.00892  -0.1274   0.5350   1.0000
   2.250   0.9353   0.01614   0.00897  -0.1273   0.5298   1.0000
   2.500   0.9632   0.01645   0.00914  -0.1273   0.5247   1.0000
   2.750   0.9857   0.01666   0.00937  -0.1263   0.5187   1.0000
   3.000   1.0114   0.01686   0.00949  -0.1259   0.5130   1.0000
   3.250   1.0396   0.01709   0.00958  -0.1260   0.5080   1.0000
   3.500   1.0646   0.01741   0.00986  -0.1255   0.5026   1.0000
   3.750   1.0874   0.01764   0.01010  -0.1246   0.4964   1.0000
   4.000   1.1135   0.01784   0.01022  -0.1243   0.4908   1.0000
   4.250   1.1434   0.01816   0.01037  -0.1247   0.4856   1.0000
   4.500   1.1622   0.01840   0.01070  -0.1232   0.4791   1.0000
   4.750   1.1860   0.01861   0.01087  -0.1225   0.4730   1.0000
   5.000   1.2134   0.01882   0.01096  -0.1225   0.4678   1.0000
   5.250   1.2348   0.01914   0.01130  -0.1214   0.4616   1.0000
   5.500   1.2559   0.01935   0.01152  -0.1203   0.4551   1.0000
   5.750   1.2811   0.01952   0.01158  -0.1199   0.4495   1.0000
   6.000   1.3028   0.01982   0.01187  -0.1189   0.4435   1.0000
   6.250   1.3217   0.02007   0.01215  -0.1175   0.4370   1.0000
   6.500   1.3447   0.02027   0.01228  -0.1167   0.4316   1.0000
   6.750   1.3679   0.02060   0.01255  -0.1161   0.4264   1.0000
   7.000   1.3837   0.02093   0.01295  -0.1142   0.4202   1.0000
   7.250   1.4035   0.02117   0.01316  -0.1130   0.4147   1.0000
   7.500   1.4280   0.02146   0.01334  -0.1125   0.4097   1.0000
   7.750   1.4399   0.02190   0.01388  -0.1101   0.4042   1.0000
   8.000   1.4559   0.02227   0.01426  -0.1083   0.3994   1.0000
   8.250   1.4774   0.02260   0.01452  -0.1074   0.3951   1.0000
   8.500   1.4961   0.02308   0.01499  -0.1062   0.3906   1.0000
   8.750   1.5075   0.02363   0.01563  -0.1039   0.3857   1.0000
   9.000   1.5233   0.02410   0.01610  -0.1023   0.3810   1.0000
   9.250   1.5468   0.02447   0.01637  -0.1019   0.3767   1.0000
   9.500   1.5589   0.02515   0.01711  -0.0999   0.3722   1.0000
   9.750   1.5697   0.02583   0.01787  -0.0978   0.3674   1.0000
  10.000   1.5854   0.02640   0.01844  -0.0964   0.3630   1.0000
  10.250   1.6124   0.02678   0.01869  -0.0965   0.3587   1.0000
  10.500   1.6174   0.02774   0.01979  -0.0939   0.3545   1.0000
  10.750   1.6267   0.02860   0.02073  -0.0919   0.3499   1.0000
  11.000   1.6414   0.02929   0.02141  -0.0906   0.3455   1.0000
  11.250   1.6673   0.02972   0.02172  -0.0906   0.3410   1.0000
  11.500   1.6657   0.03106   0.02324  -0.0876   0.3364   1.0000
  11.750   1.6728   0.03212   0.02437  -0.0857   0.3316   1.0000
  12.000   1.6897   0.03278   0.02498  -0.0848   0.3269   1.0000
  12.250   1.7002   0.03385   0.02608  -0.0833   0.3221   1.0000
  12.500   1.6989   0.03546   0.02783  -0.0809   0.3171   1.0000
  12.750   1.7077   0.03658   0.02896  -0.0795   0.3122   1.0000
  13.000   1.7300   0.03709   0.02936  -0.0792   0.3073   1.0000
  13.250   1.7186   0.03946   0.03195  -0.0764   0.3022   1.0000
  13.500   1.7214   0.04106   0.03360  -0.0748   0.2969   1.0000
  13.750   1.7451   0.04138   0.03377  -0.0745   0.2918   1.0000
  14.000   1.7283   0.04445   0.03708  -0.0720   0.2864   1.0000
  14.250   1.7275   0.04650   0.03920  -0.0706   0.2809   1.0000
  14.500   1.7488   0.04689   0.03944  -0.0701   0.2759   1.0000
  14.750   1.7296   0.05063   0.04342  -0.0682   0.2703   1.0000
  15.000   1.7285   0.05298   0.04582  -0.0672   0.2650   1.0000
  15.250   1.7485   0.05339   0.04610  -0.0667   0.2605   1.0000
  15.500   1.7311   0.05745   0.05039  -0.0655   0.2555   1.0000
  15.750   1.7284   0.06019   0.05321  -0.0648   0.2508   1.0000
  16.000   1.7405   0.06139   0.05436  -0.0643   0.2471   1.0000
  16.250   1.7453   0.06343   0.05644  -0.0637   0.2433   1.0000
  16.500   1.7314   0.06757   0.06076  -0.0632   0.2392   1.0000
  16.750   1.7328   0.07004   0.06330  -0.0628   0.2355   1.0000
  17.000   1.7471   0.07099   0.06418  -0.0625   0.2323   1.0000
  17.250   1.7469   0.07368   0.06695  -0.0622   0.2288   1.0000
  17.500   1.7280   0.07873   0.07220  -0.0622   0.2251   1.0000
  17.750   1.7267   0.08164   0.07517  -0.0623   0.2216   1.0000
  18.000   1.7398   0.08271   0.07620  -0.0621   0.2186   1.0000
  18.250   1.7508   0.08405   0.07753  -0.0618   0.2158   1.0000
  18.500   1.7226   0.09056   0.08430  -0.0625   0.2128   1.0000
  18.750   1.7090   0.09526   0.08914  -0.0631   0.2099   1.0000
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