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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 200,000
Max Cl/Cd: 64.29 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa32-il-200000.txt
Download as CSV file: xf-usa32-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 32 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   0.0921   0.10347   0.09979  -0.1131   0.9158   0.0530
  -9.000   0.0663   0.10304   0.09941  -0.1115   0.9042   0.0542
  -8.750   0.0813   0.09861   0.09498  -0.1154   0.9020   0.0552
  -8.500   0.1136   0.09496   0.09131  -0.1170   0.9011   0.0567
  -8.250   0.1126   0.09334   0.08972  -0.1150   0.8926   0.0576
  -8.000   0.1257   0.09035   0.08673  -0.1174   0.8881   0.0599
  -7.750   0.1071   0.08715   0.08351  -0.1277   0.8826   0.0628
  -7.250   0.1413   0.08139   0.07780  -0.1227   0.8707   0.0649
  -7.000   0.1641   0.07827   0.07466  -0.1256   0.8686   0.0681
  -6.750   0.1513   0.07668   0.07307  -0.1231   0.8567   0.0702
  -6.500   0.1614   0.07191   0.06826  -0.1290   0.8518   0.0735
  -6.250   0.1960   0.06889   0.06521  -0.1313   0.8508   0.0758
  -6.000   0.1922   0.06732   0.06365  -0.1280   0.8386   0.0777
  -5.750   0.2121   0.06221   0.05841  -0.1364   0.8341   0.0842
  -5.500   0.2149   0.06073   0.05693  -0.1323   0.8235   0.0852
  -5.250   0.2456   0.05815   0.05431  -0.1344   0.8197   0.0886
  -5.000   0.2798   0.05362   0.04962  -0.1417   0.8163   0.0971
  -4.750   0.2772   0.05255   0.04856  -0.1364   0.8034   0.0987
  -4.500   0.3144   0.04863   0.04443  -0.1430   0.7994   0.1097
  -4.250   0.3098   0.04763   0.04344  -0.1371   0.7867   0.1108
  -4.000   0.3481   0.04540   0.04112  -0.1403   0.7829   0.1165
  -3.750   0.3434   0.04337   0.03895  -0.1366   0.7703   0.1240
  -3.500   0.3384   0.02887   0.02340  -0.1367   0.7652   0.0856
  -3.250   0.3215   0.02451   0.01808  -0.1279   0.7537   0.0695
  -3.000   0.3568   0.02235   0.01545  -0.1290   0.7495   0.0680
  -2.750   0.3670   0.02136   0.01412  -0.1251   0.7404   0.0664
  -2.500   0.4006   0.02010   0.01244  -0.1256   0.7347   0.0649
  -2.250   0.4321   0.01929   0.01138  -0.1259   0.7286   0.0644
  -2.000   0.4545   0.01871   0.01068  -0.1245   0.7209   0.0647
  -1.750   0.5010   0.01783   0.00966  -0.1279   0.7160   0.0656
  -1.500   0.5153   0.01762   0.00944  -0.1250   0.7077   0.0671
  -1.250   0.5524   0.01711   0.00883  -0.1266   0.7017   0.0688
  -1.000   0.5819   0.01680   0.00846  -0.1267   0.6951   0.0699
  -0.750   0.6070   0.01660   0.00821  -0.1259   0.6881   0.0712
  -0.500   0.6545   0.01620   0.00771  -0.1297   0.6824   0.0741
  -0.250   0.6668   0.01621   0.00773  -0.1265   0.6747   0.0769
   0.000   0.7050   0.01605   0.00746  -0.1284   0.6683   0.0835
   0.250   0.7385   0.01569   0.00744  -0.1297   0.6621   0.1600
   0.500   0.7584   0.01600   0.00780  -0.1279   0.6549   0.2263
   0.750   0.8033   0.01650   0.00812  -0.1313   0.6484   0.2588
   1.000   0.8054   0.01684   0.00850  -0.1259   0.6412   0.2684
   1.250   0.8312   0.01718   0.00877  -0.1254   0.6342   0.2812
   1.500   0.8607   0.01754   0.00899  -0.1257   0.6275   0.2932
   1.750   0.8718   0.01772   0.00923  -0.1223   0.6203   0.2982
   2.000   0.9069   0.01804   0.00941  -0.1239   0.6137   0.3102
   2.250   0.9176   0.01827   0.00969  -0.1204   0.6067   0.3171
   2.500   0.9335   0.01847   0.00986  -0.1180   0.5993   0.3251
   2.750   0.9740   0.01865   0.00991  -0.1207   0.5926   0.3333
   3.000   0.9686   0.01878   0.01012  -0.1139   0.5847   0.3356
   3.250   0.9942   0.01886   0.01012  -0.1135   0.5777   0.3407
   3.500   1.0097   0.01906   0.01026  -0.1111   0.5707   0.3457
   3.750   1.0191   0.01917   0.01042  -0.1075   0.5631   0.3497
   4.000   1.0511   0.01921   0.01037  -0.1085   0.5569   0.3567
   4.250   1.0497   0.01947   0.01069  -0.1027   0.5491   0.3607
   4.500   1.0679   0.01951   0.01072  -0.1010   0.5421   0.3657
   4.750   1.0860   0.01964   0.01083  -0.0992   0.5355   0.3722
   5.000   1.0925   0.01983   0.01105  -0.0952   0.5277   0.3785
   5.250   1.1193   0.01982   0.01100  -0.0952   0.5218   0.3871
   5.500   1.1233   0.02010   0.01135  -0.0909   0.5140   0.3943
   5.750   1.1415   0.02018   0.01144  -0.0894   0.5073   0.4040
   6.000   1.1654   0.02030   0.01158  -0.0890   0.5013   0.4146
   6.250   1.1787   0.02057   0.01190  -0.0867   0.4943   0.4249
   6.500   1.2051   0.02063   0.01192  -0.0868   0.4887   0.4394
   6.750   1.2213   0.02092   0.01227  -0.0852   0.4827   0.4542
   7.000   1.2369   0.02113   0.01257  -0.0835   0.4756   0.4817
   7.250   1.4069   0.02189   0.01418  -0.1155   0.4624   1.0000
   7.500   1.4244   0.02222   0.01446  -0.1139   0.4572   1.0000
   7.750   1.4497   0.02255   0.01468  -0.1138   0.4524   1.0000
   8.000   1.4566   0.02309   0.01530  -0.1104   0.4471   1.0000
   8.250   1.4714   0.02350   0.01571  -0.1085   0.4418   1.0000
   8.500   1.5013   0.02376   0.01582  -0.1092   0.4368   1.0000
   8.750   1.5043   0.02440   0.01657  -0.1053   0.4318   1.0000
   9.000   1.5163   0.02491   0.01711  -0.1030   0.4270   1.0000
   9.250   1.5367   0.02529   0.01745  -0.1021   0.4226   1.0000
   9.500   1.5619   0.02568   0.01780  -0.1021   0.4183   1.0000
   9.750   1.5639   0.02641   0.01865  -0.0982   0.4137   1.0000
  10.000   1.5759   0.02696   0.01924  -0.0961   0.4091   1.0000
  10.250   1.5975   0.02734   0.01960  -0.0955   0.4051   1.0000
  10.500   1.6186   0.02783   0.02008  -0.0949   0.4009   1.0000
  10.750   1.6183   0.02869   0.02108  -0.0910   0.3965   1.0000
  11.000   1.6274   0.02934   0.02178  -0.0885   0.3917   1.0000
  11.250   1.6507   0.02961   0.02196  -0.0882   0.3865   1.0000
  11.500   1.6550   0.03049   0.02296  -0.0852   0.3823   1.0000
  11.750   1.6538   0.03148   0.02407  -0.0815   0.3775   1.0000
  12.000   1.6643   0.03209   0.02470  -0.0795   0.3724   1.0000
  12.250   1.6878   0.03242   0.02498  -0.0793   0.3676   1.0000
  12.500   1.6766   0.03386   0.02662  -0.0745   0.3629   1.0000
  12.750   1.6778   0.03488   0.02771  -0.0715   0.3574   1.0000
  13.000   1.6978   0.03518   0.02794  -0.0709   0.3521   1.0000
  13.250   1.6878   0.03684   0.02977  -0.0668   0.3470   1.0000
  13.500   1.6834   0.03827   0.03131  -0.0635   0.3410   1.0000
  13.750   1.7003   0.03865   0.03159  -0.0626   0.3348   1.0000
  14.000   1.6856   0.04090   0.03405  -0.0586   0.3295   1.0000
  14.250   1.6807   0.04264   0.03589  -0.0558   0.3230   1.0000
  14.500   1.6847   0.04388   0.03711  -0.0539   0.3163   1.0000
  14.750   1.6711   0.04656   0.03997  -0.0509   0.3094   1.0000
  15.000   1.6763   0.04784   0.04121  -0.0494   0.3026   1.0000
  15.250   1.6615   0.05100   0.04456  -0.0468   0.2952   1.0000
  15.500   1.6588   0.05317   0.04673  -0.0452   0.2876   1.0000
  15.750   1.6481   0.05631   0.05002  -0.0434   0.2796   1.0000
  16.000   1.6435   0.05888   0.05258  -0.0421   0.2710   1.0000
  16.250   1.6295   0.06269   0.05653  -0.0408   0.2615   1.0000
  16.500   1.6231   0.06567   0.05951  -0.0397   0.2526   1.0000
  16.750   1.6114   0.06938   0.06330  -0.0387   0.2427   1.0000
  17.000   1.6012   0.07297   0.06695  -0.0379   0.2336   1.0000
  17.500   1.5799   0.08048   0.07449  -0.0367   0.2152   1.0000
  17.750   1.5709   0.08407   0.07807  -0.0362   0.2071   1.0000
  18.000   1.5627   0.08764   0.08167  -0.0358   0.1998   1.0000
  18.250   1.5551   0.09116   0.08518  -0.0356   0.1927   1.0000
  18.500   1.5457   0.09500   0.08904  -0.0355   0.1855   1.0000
  18.750   1.5400   0.09832   0.09234  -0.0354   0.1791   1.0000
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