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20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: 20-32C AIRFOIL (2032c-il)
Reynolds number: 200,000
Max Cl/Cd: 75.32 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-2032c-il-200000.txt
Download as CSV file: xf-2032c-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 20-32C 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1581   0.09761   0.09467  -0.0262   1.0000   0.0240
  -8.500  -0.1536   0.09468   0.09178  -0.0262   1.0000   0.0244
  -8.250  -0.2407   0.10671   0.10359  -0.0219   1.0000   0.0232
  -8.000  -0.2303   0.10247   0.09935  -0.0213   1.0000   0.0237
  -7.750  -0.2229   0.09947   0.09639  -0.0215   1.0000   0.0241
  -7.500  -0.2174   0.09690   0.09388  -0.0218   1.0000   0.0245
  -7.250  -0.2150   0.09475   0.09180  -0.0215   1.0000   0.0249
  -7.000  -0.2194   0.09328   0.09042  -0.0198   1.0000   0.0252
  -6.750  -0.2314   0.09255   0.08980  -0.0166   1.0000   0.0254
  -6.500  -0.2233   0.09009   0.08738  -0.0186   0.9966   0.0259
  -6.250  -0.1900   0.08553   0.08281  -0.0268   0.9890   0.0270
  -6.000  -0.1523   0.08088   0.07814  -0.0361   0.9817   0.0284
  -5.750  -0.0972   0.07684   0.07404  -0.0523   0.9713   0.0304
  -5.500  -0.0417   0.07273   0.06982  -0.0675   0.9588   0.0309
  -5.250  -0.0078   0.06691   0.06397  -0.0749   0.9463   0.0313
  -5.000  -0.0001   0.06252   0.05960  -0.0718   0.9327   0.0327
  -4.750   0.0224   0.05945   0.05649  -0.0735   0.9160   0.0347
  -4.500   0.0512   0.05621   0.05317  -0.0777   0.8984   0.0368
  -4.250   0.0843   0.05296   0.04980  -0.0831   0.8792   0.0395
  -4.000   0.1492   0.05014   0.04662  -0.0960   0.8598   0.0421
  -3.750   0.1656   0.04499   0.04141  -0.0971   0.8423   0.0435
  -3.500   0.1832   0.04264   0.03899  -0.0966   0.8235   0.0454
  -3.250   0.2121   0.04019   0.03639  -0.0987   0.8040   0.0491
  -3.000   0.2608   0.03631   0.03213  -0.1058   0.7860   0.0569
  -2.500   0.3282   0.03126   0.02652  -0.1108   0.7482   0.0704
  -2.250   0.3508   0.02964   0.02483  -0.1106   0.7284   0.0748
  -2.000   0.3864   0.02736   0.02219  -0.1130   0.7101   0.0866
  -1.750   0.4186   0.02566   0.02020  -0.1145   0.6908   0.1006
  -1.500   0.4502   0.02414   0.01836  -0.1156   0.6714   0.1147
  -1.250   0.4799   0.02282   0.01678  -0.1162   0.6523   0.1294
  -1.000   0.5252   0.01961   0.01249  -0.1175   0.6356   0.0830
  -0.750   0.5588   0.01688   0.00921  -0.1181   0.6175   0.0678
  -0.500   0.5882   0.01607   0.00803  -0.1180   0.5987   0.0682
  -0.250   0.6169   0.01548   0.00711  -0.1178   0.5804   0.0690
   0.000   0.6454   0.01479   0.00618  -0.1177   0.5617   0.0692
   0.250   0.6735   0.01417   0.00542  -0.1176   0.5430   0.0709
   0.500   0.7011   0.01388   0.00503  -0.1174   0.5249   0.0738
   0.750   0.7285   0.01381   0.00484  -0.1172   0.5078   0.0802
   1.000   0.7562   0.01368   0.00461  -0.1170   0.4917   0.0855
   1.250   0.7840   0.01363   0.00449  -0.1169   0.4758   0.0987
   1.500   0.8117   0.01296   0.00461  -0.1172   0.4609   0.4068
   1.750   0.8328   0.01219   0.00455  -0.1155   0.4480   1.0000
   2.000   0.8599   0.01248   0.00463  -0.1153   0.4349   1.0000
   2.250   0.8869   0.01276   0.00475  -0.1151   0.4228   1.0000
   2.500   0.9139   0.01307   0.00492  -0.1149   0.4121   1.0000
   2.750   0.9407   0.01341   0.00511  -0.1147   0.4027   1.0000
   3.000   0.9675   0.01371   0.00529  -0.1145   0.3934   1.0000
   3.250   0.9943   0.01403   0.00553  -0.1143   0.3848   1.0000
   3.500   1.0209   0.01440   0.00576  -0.1141   0.3776   1.0000
   3.750   1.0478   0.01471   0.00607  -0.1139   0.3703   1.0000
   4.000   1.0743   0.01507   0.00634  -0.1137   0.3642   1.0000
   4.250   1.1009   0.01544   0.00668  -0.1136   0.3582   1.0000
   4.500   1.1274   0.01577   0.00699  -0.1134   0.3521   1.0000
   4.750   1.1538   0.01622   0.00737  -0.1132   0.3470   1.0000
   5.000   1.1801   0.01654   0.00776  -0.1130   0.3414   1.0000
   5.250   1.2065   0.01693   0.00813  -0.1128   0.3368   1.0000
   5.500   1.2328   0.01743   0.00859  -0.1127   0.3326   1.0000
   5.750   1.2583   0.01767   0.00896  -0.1123   0.3257   1.0000
   6.000   1.2831   0.01796   0.00919  -0.1120   0.3174   1.0000
   6.250   1.3078   0.01812   0.00942  -0.1115   0.3087   1.0000
   6.500   1.3324   0.01841   0.00974  -0.1111   0.3009   1.0000
   6.750   1.3561   0.01862   0.00993  -0.1106   0.2907   1.0000
   7.000   1.3795   0.01867   0.01008  -0.1100   0.2783   1.0000
   7.250   1.4031   0.01880   0.01030  -0.1095   0.2656   1.0000
   7.500   1.4266   0.01899   0.01056  -0.1089   0.2513   1.0000
   7.750   1.4492   0.01924   0.01077  -0.1083   0.2235   1.0000
   8.000   1.4701   0.01987   0.01126  -0.1074   0.1848   1.0000
   8.250   1.4649   0.02361   0.01395  -0.1040   0.0406   1.0000
   8.500   1.4793   0.02496   0.01535  -0.1023   0.0295   1.0000
   8.750   1.4948   0.02610   0.01665  -0.1006   0.0266   1.0000
   9.000   1.5071   0.02746   0.01825  -0.0986   0.0241   1.0000
   9.250   1.5181   0.02881   0.01982  -0.0965   0.0232   1.0000
   9.500   1.5253   0.03028   0.02155  -0.0941   0.0227   1.0000
   9.750   1.5265   0.03194   0.02343  -0.0909   0.0224   1.0000
  10.000   1.5248   0.03397   0.02567  -0.0881   0.0222   1.0000
  10.250   1.5203   0.03647   0.02838  -0.0858   0.0220   1.0000
  10.500   1.5136   0.03951   0.03161  -0.0843   0.0219   1.0000
  10.750   1.5051   0.04315   0.03543  -0.0835   0.0218   1.0000
  11.000   1.4954   0.04733   0.03979  -0.0835   0.0218   1.0000
  11.250   1.4848   0.05197   0.04459  -0.0840   0.0218   1.0000
  11.500   1.4738   0.05687   0.04964  -0.0847   0.0218   1.0000
  11.750   1.4626   0.06186   0.05476  -0.0855   0.0218   1.0000
  12.000   1.4523   0.06673   0.05976  -0.0862   0.0217   1.0000
  12.250   1.4431   0.07139   0.06452  -0.0867   0.0216   1.0000
  12.500   1.4354   0.07576   0.06898  -0.0870   0.0213   1.0000
  12.750   1.4295   0.07975   0.07305  -0.0871   0.0209   1.0000
  13.000   1.4266   0.08325   0.07661  -0.0869   0.0206   1.0000
  13.250   1.4286   0.08579   0.07922  -0.0858   0.0205   1.0000
  13.500   1.4369   0.08708   0.08054  -0.0835   0.0208   1.0000
  13.750   1.4509   0.08742   0.08092  -0.0801   0.0215   1.0000
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