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PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: PSU-90-125WL (psu-90-125wl-il)
Reynolds number: 100,000
Max Cl/Cd: 54.1 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-psu-90-125wl-il-100000.txt
Download as CSV file: xf-psu-90-125wl-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PSU-90-125WL                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3843   0.10759   0.10254  -0.0394   1.0000   0.1273
 -10.000  -0.3843   0.10458   0.09958  -0.0399   1.0000   0.1318
  -9.750  -0.4431   0.10173   0.09699  -0.0481   1.0000   0.1364
  -9.500  -0.4005   0.09741   0.09258  -0.0424   1.0000   0.1390
  -9.250  -0.3915   0.09467   0.08987  -0.0411   1.0000   0.1425
  -9.000  -0.4017   0.09172   0.08702  -0.0419   1.0000   0.1479
  -8.750  -0.4434   0.08796   0.08349  -0.0446   1.0000   0.1521
  -8.500  -0.4220   0.08535   0.08086  -0.0412   1.0000   0.1548
  -8.250  -0.4256   0.08327   0.07885  -0.0391   1.0000   0.1593
  -8.000  -0.4535   0.08134   0.07708  -0.0367   1.0000   0.1614
  -7.750  -0.5011   0.08033   0.07625  -0.0329   1.0000   0.1630
  -7.000  -0.6309   0.05364   0.04863  -0.0378   1.0000   0.0842
  -6.750  -0.6372   0.04530   0.03906  -0.0362   1.0000   0.0662
  -6.500  -0.6272   0.04166   0.03518  -0.0351   1.0000   0.0646
  -6.250  -0.6144   0.03845   0.03157  -0.0340   1.0000   0.0634
  -6.000  -0.5990   0.03588   0.02855  -0.0330   1.0000   0.0639
  -5.750  -0.5813   0.03366   0.02590  -0.0320   1.0000   0.0645
  -5.500  -0.5557   0.03142   0.02319  -0.0321   0.9984   0.0649
  -5.250  -0.5205   0.02940   0.02075  -0.0337   0.9944   0.0655
  -5.000  -0.4864   0.02791   0.01892  -0.0348   0.9899   0.0670
  -4.750  -0.4529   0.02609   0.01712  -0.0363   0.9859   0.0705
  -4.500  -0.4192   0.02526   0.01622  -0.0377   0.9814   0.0778
  -4.250  -0.3885   0.02411   0.01516  -0.0386   0.9762   0.0867
  -4.000  -0.3536   0.02295   0.01413  -0.0402   0.9720   0.1098
  -3.750  -0.3287   0.02103   0.01314  -0.0408   0.9667   0.2359
  -3.500  -0.3002   0.02014   0.01302  -0.0418   0.9612   0.3908
  -3.250  -0.2715   0.01991   0.01350  -0.0420   0.9559   0.5386
  -3.000  -0.2486   0.02008   0.01384  -0.0407   0.9487   0.6218
  -2.750  -0.2150   0.02052   0.01429  -0.0411   0.9434   0.6836
  -2.500  -0.1971   0.02073   0.01453  -0.0386   0.9355   0.7229
  -2.250  -0.1661   0.02107   0.01483  -0.0384   0.9296   0.7630
  -2.000  -0.1486   0.02125   0.01499  -0.0358   0.9215   0.7945
  -1.750  -0.1198   0.02147   0.01516  -0.0351   0.9152   0.8270
  -1.500  -0.1026   0.02161   0.01527  -0.0324   0.9069   0.8567
  -1.250  -0.0714   0.02176   0.01536  -0.0321   0.9005   0.8874
  -1.000  -0.0431   0.02194   0.01546  -0.0318   0.8927   0.9169
  -0.750   0.0109   0.02218   0.01559  -0.0364   0.8871   0.9435
  -0.500   0.0886   0.02244   0.01568  -0.0457   0.8842   0.9606
  -0.250   0.1559   0.02264   0.01576  -0.0537   0.8778   0.9752
   0.000   0.2319   0.02260   0.01559  -0.0632   0.8733   0.9865
   0.250   0.3121   0.02230   0.01521  -0.0733   0.8704   0.9951
   0.500   0.3481   0.02222   0.01508  -0.0759   0.8607   1.0000
   0.750   0.3959   0.02182   0.01464  -0.0798   0.8549   1.0000
   1.000   0.4024   0.02185   0.01465  -0.0768   0.8421   1.0000
   1.250   0.4553   0.02129   0.01405  -0.0810   0.8377   1.0000
   1.500   0.4582   0.02136   0.01410  -0.0771   0.8243   1.0000
   1.750   0.4648   0.02144   0.01415  -0.0737   0.8113   1.0000
   2.000   0.4831   0.02145   0.01413  -0.0721   0.8000   1.0000
   2.250   0.5280   0.02093   0.01360  -0.0744   0.7937   1.0000
   2.500   0.5469   0.02097   0.01363  -0.0727   0.7812   1.0000
   2.750   0.5739   0.02085   0.01351  -0.0722   0.7701   1.0000
   3.000   0.6164   0.02025   0.01291  -0.0737   0.7629   1.0000
   3.250   0.6398   0.02020   0.01288  -0.0725   0.7499   1.0000
   3.500   0.6663   0.02005   0.01275  -0.0718   0.7373   1.0000
   3.750   0.6958   0.01979   0.01250  -0.0714   0.7253   1.0000
   4.000   0.7287   0.01938   0.01212  -0.0713   0.7137   1.0000
   4.250   0.7626   0.01891   0.01166  -0.0714   0.7016   1.0000
   4.500   0.7901   0.01866   0.01142  -0.0706   0.6866   1.0000
   4.750   0.8143   0.01851   0.01131  -0.0694   0.6696   1.0000
   5.000   0.8387   0.01837   0.01121  -0.0682   0.6515   1.0000
   5.250   0.8650   0.01815   0.01101  -0.0672   0.6328   1.0000
   5.500   0.8932   0.01790   0.01074  -0.0665   0.6136   1.0000
   5.750   0.9164   0.01789   0.01075  -0.0652   0.5910   1.0000
   6.000   0.9430   0.01783   0.01061  -0.0643   0.5682   1.0000
   6.250   0.9645   0.01801   0.01077  -0.0628   0.5423   1.0000
   6.500   0.9865   0.01828   0.01099  -0.0614   0.5158   1.0000
   6.750   1.0078   0.01863   0.01125  -0.0600   0.4889   1.0000
   7.000   1.0282   0.01907   0.01158  -0.0584   0.4617   1.0000
   7.250   1.0466   0.01959   0.01203  -0.0567   0.4341   1.0000
   7.500   1.0635   0.02017   0.01257  -0.0548   0.4063   1.0000
   7.750   1.0798   0.02081   0.01315  -0.0528   0.3792   1.0000
   8.000   1.0952   0.02151   0.01376  -0.0508   0.3526   1.0000
   8.250   1.1102   0.02228   0.01440  -0.0488   0.3271   1.0000
   8.500   1.1230   0.02307   0.01516  -0.0464   0.3016   1.0000
   8.750   1.1354   0.02395   0.01601  -0.0442   0.2776   1.0000
   9.000   1.1472   0.02488   0.01682  -0.0419   0.2552   1.0000
   9.250   1.1574   0.02587   0.01781  -0.0394   0.2333   1.0000
   9.500   1.1667   0.02691   0.01877  -0.0368   0.2135   1.0000
   9.750   1.1757   0.02807   0.01983  -0.0343   0.1951   1.0000
  10.000   1.1823   0.02923   0.02103  -0.0315   0.1776   1.0000
  10.250   1.1879   0.03048   0.02228  -0.0288   0.1610   1.0000
  10.500   1.1903   0.03173   0.02353  -0.0259   0.1454   1.0000
  10.750   1.1907   0.03306   0.02487  -0.0231   0.1307   1.0000
  11.000   1.1904   0.03455   0.02637  -0.0206   0.1169   1.0000
  11.250   1.1908   0.03630   0.02813  -0.0183   0.1037   1.0000
  11.500   1.1904   0.03829   0.03014  -0.0162   0.0910   1.0000
  11.750   1.1894   0.04056   0.03242  -0.0143   0.0790   1.0000
  12.000   1.1902   0.04303   0.03491  -0.0126   0.0689   1.0000
  12.250   1.1955   0.04566   0.03750  -0.0111   0.0607   1.0000
  12.500   1.2006   0.04805   0.03998  -0.0098   0.0549   1.0000
  12.750   1.2106   0.05081   0.04280  -0.0088   0.0503   1.0000
  13.000   1.2142   0.05345   0.04571  -0.0077   0.0473   1.0000
  13.250   1.2195   0.05597   0.04834  -0.0069   0.0448   1.0000
  13.500   1.2386   0.05958   0.05191  -0.0064   0.0423   1.0000
  13.750   1.2328   0.06304   0.05571  -0.0054   0.0417   1.0000
  14.000   1.2245   0.06693   0.05993  -0.0048   0.0413   1.0000
  14.250   1.2127   0.07125   0.06457  -0.0046   0.0409   1.0000
  14.500   1.1986   0.07594   0.06955  -0.0049   0.0408   1.0000
  14.750   1.1813   0.08116   0.07506  -0.0058   0.0408   1.0000
  15.000   1.1619   0.08687   0.08102  -0.0075   0.0408   1.0000
  15.250   1.1413   0.09310   0.08750  -0.0099   0.0410   1.0000
  15.500   1.1169   0.10032   0.09495  -0.0134   0.0412   1.0000
  15.750   1.0942   0.10794   0.10276  -0.0175   0.0415   1.0000
  16.000   1.0702   0.11641   0.11141  -0.0225   0.0418   1.0000
  16.250   1.0464   0.12563   0.12076  -0.0281   0.0422   1.0000
  16.500   0.8946   0.17975   0.17491  -0.0621   0.0605   1.0000
  16.750   0.8952   0.18595   0.18109  -0.0650   0.0612   1.0000
  17.000   0.9000   0.19109   0.18623  -0.0670   0.0621   1.0000
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