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20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: 20-32C AIRFOIL (2032c-il)
Reynolds number: 50,000
Max Cl/Cd: 40.82 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-2032c-il-50000-n5.txt
Download as CSV file: xf-2032c-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2164   0.10214   0.09678  -0.0202   1.0000   0.0621
  -6.500  -0.2233   0.10113   0.09590  -0.0187   1.0000   0.0634
  -6.250  -0.2313   0.10033   0.09523  -0.0174   1.0000   0.0647
  -6.000  -0.2134   0.09885   0.09379  -0.0250   0.9918   0.0671
  -5.750  -0.1645   0.09639   0.09127  -0.0423   0.9769   0.0683
  -5.500  -0.1546   0.08928   0.08418  -0.0375   0.9697   0.0706
  -5.250  -0.1264   0.08495   0.07982  -0.0419   0.9586   0.0749
  -5.000  -0.0770   0.08210   0.07686  -0.0565   0.9440   0.0821
  -4.750  -0.0477   0.07701   0.07178  -0.0609   0.9335   0.0849
  -4.500  -0.0121   0.07301   0.06772  -0.0666   0.9229   0.0949
  -4.250   0.0259   0.06883   0.06349  -0.0739   0.9107   0.1009
  -4.000   0.0869   0.06619   0.06057  -0.0884   0.8964   0.1125
  -3.750   0.1013   0.06143   0.05587  -0.0864   0.8834   0.1157
  -3.500   0.1521   0.05823   0.05245  -0.0961   0.8693   0.1279
  -3.250   0.1846   0.05478   0.04891  -0.0994   0.8551   0.1431
  -2.750   0.2824   0.04530   0.03876  -0.1124   0.8270   0.0778
  -2.500   0.3292   0.04143   0.03452  -0.1180   0.8120   0.0727
  -2.250   0.3704   0.03845   0.03118  -0.1217   0.7963   0.0753
  -2.000   0.4153   0.03506   0.02725  -0.1257   0.7807   0.0723
  -1.750   0.4519   0.03278   0.02450  -0.1277   0.7631   0.0752
  -1.500   0.4893   0.03067   0.02180  -0.1295   0.7456   0.0799
  -1.250   0.5242   0.02876   0.01929  -0.1305   0.7283   0.0802
  -1.000   0.5569   0.02724   0.01719  -0.1309   0.7111   0.0813
  -0.750   0.5880   0.02606   0.01544  -0.1308   0.6941   0.0832
  -0.500   0.6156   0.02539   0.01456  -0.1305   0.6765   0.0920
  -0.250   0.6444   0.02478   0.01337  -0.1298   0.6585   0.0976
   0.000   0.6717   0.02418   0.01250  -0.1291   0.6411   0.1014
   0.250   0.6988   0.02376   0.01177  -0.1284   0.6242   0.1068
   0.500   0.7259   0.02342   0.01117  -0.1277   0.6077   0.1146
   0.750   0.7530   0.02317   0.01076  -0.1271   0.5916   0.1297
   1.000   0.7804   0.02287   0.01053  -0.1268   0.5760   0.1799
   1.250   0.8016   0.02135   0.01047  -0.1255   0.5614   1.0000
   1.500   0.8283   0.02171   0.01035  -0.1249   0.5464   1.0000
   1.750   0.8545   0.02210   0.01037  -0.1244   0.5319   1.0000
   2.000   0.8806   0.02251   0.01049  -0.1239   0.5180   1.0000
   2.250   0.9065   0.02295   0.01068  -0.1235   0.5048   1.0000
   2.500   0.9323   0.02341   0.01094  -0.1231   0.4922   1.0000
   2.750   0.9580   0.02388   0.01121  -0.1226   0.4806   1.0000
   3.000   0.9839   0.02435   0.01147  -0.1222   0.4703   1.0000
   3.250   1.0092   0.02489   0.01192  -0.1218   0.4595   1.0000
   3.500   1.0344   0.02545   0.01239  -0.1215   0.4495   1.0000
   3.750   1.0601   0.02597   0.01276  -0.1210   0.4410   1.0000
   4.000   1.0848   0.02660   0.01341  -0.1207   0.4316   1.0000
   4.250   1.1100   0.02721   0.01396  -0.1203   0.4239   1.0000
   4.500   1.1347   0.02785   0.01459  -0.1199   0.4161   1.0000
   4.750   1.1594   0.02853   0.01526  -0.1195   0.4089   1.0000
   5.000   1.1837   0.02922   0.01602  -0.1191   0.4016   1.0000
   5.250   1.2083   0.02992   0.01673  -0.1188   0.3955   1.0000
   5.500   1.2316   0.03076   0.01768  -0.1183   0.3888   1.0000
   5.750   1.2568   0.03142   0.01838  -0.1180   0.3837   1.0000
   6.000   1.2786   0.03242   0.01959  -0.1174   0.3773   1.0000
   6.250   1.3021   0.03324   0.02050  -0.1170   0.3718   1.0000
   6.500   1.3259   0.03406   0.02141  -0.1165   0.3670   1.0000
   6.750   1.3460   0.03525   0.02293  -0.1159   0.3614   1.0000
   7.000   1.3689   0.03619   0.02402  -0.1154   0.3569   1.0000
   7.250   1.3927   0.03708   0.02503  -0.1149   0.3530   1.0000
   7.500   1.4091   0.03859   0.02692  -0.1140   0.3475   1.0000
   7.750   1.4326   0.03866   0.02699  -0.1130   0.3385   1.0000
   8.000   1.4448   0.03873   0.02724  -0.1108   0.3218   1.0000
   8.250   1.4590   0.03893   0.02754  -0.1089   0.3081   1.0000
   8.500   1.4721   0.03951   0.02830  -0.1070   0.2967   1.0000
   8.750   1.4805   0.04030   0.02932  -0.1048   0.2838   1.0000
   9.000   1.4838   0.04093   0.03002  -0.1019   0.2668   1.0000
   9.250   1.4869   0.04226   0.03161  -0.0995   0.2542   1.0000
   9.500   1.4862   0.04379   0.03337  -0.0968   0.2416   1.0000
   9.750   1.4817   0.04569   0.03546  -0.0942   0.2269   1.0000
  10.000   1.4769   0.04808   0.03804  -0.0923   0.2115   1.0000
  10.500   1.4631   0.05460   0.04500  -0.0906   0.1709   1.0000
  11.250   1.4032   0.07162   0.06159  -0.0927   0.0644   1.0000
  11.500   1.3826   0.07833   0.06839  -0.0944   0.0560   1.0000
  11.750   1.3627   0.08518   0.07537  -0.0962   0.0520   1.0000
  12.000   1.3429   0.09221   0.08254  -0.0982   0.0483   1.0000
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