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USA 48 AIRFOIL (usa48-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 48 AIRFOIL (usa48-il)
Reynolds number: 100,000
Max Cl/Cd: 49.31 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa48-il-100000-n5.txt
Download as CSV file: xf-usa48-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 48 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5165   0.08856   0.08329  -0.0605   1.0000   0.0330
 -12.000  -0.5706   0.07547   0.07008  -0.0689   1.0000   0.0318
 -11.750  -0.6140   0.06713   0.06156  -0.0737   1.0000   0.0312
 -11.500  -0.6463   0.06209   0.05639  -0.0749   1.0000   0.0310
 -11.250  -0.6754   0.05840   0.05256  -0.0741   1.0000   0.0309
 -11.000  -0.7029   0.05576   0.04980  -0.0714   1.0000   0.0308
 -10.750  -0.7298   0.05393   0.04786  -0.0667   1.0000   0.0309
 -10.500  -0.7496   0.05209   0.04590  -0.0623   1.0000   0.0310
 -10.250  -0.7627   0.05013   0.04379  -0.0584   1.0000   0.0314
 -10.000  -0.7724   0.04819   0.04168  -0.0548   1.0000   0.0320
  -9.750  -0.7795   0.04623   0.03949  -0.0513   1.0000   0.0328
  -9.500  -0.7849   0.04421   0.03717  -0.0478   1.0000   0.0337
  -9.250  -0.7732   0.04139   0.03364  -0.0479   0.9953   0.0354
  -9.000  -0.7484   0.03930   0.03152  -0.0492   0.9909   0.0368
  -8.750  -0.7222   0.03735   0.02936  -0.0505   0.9861   0.0385
  -8.500  -0.6980   0.03562   0.02722  -0.0512   0.9805   0.0412
  -8.250  -0.6704   0.03378   0.02515  -0.0523   0.9756   0.0435
  -8.000  -0.6431   0.03220   0.02348  -0.0531   0.9703   0.0458
  -7.750  -0.6140   0.03091   0.02193  -0.0541   0.9647   0.0490
  -7.500  -0.5851   0.02936   0.02034  -0.0550   0.9593   0.0519
  -7.250  -0.5573   0.02807   0.01906  -0.0557   0.9527   0.0546
  -7.000  -0.5263   0.02699   0.01782  -0.0568   0.9470   0.0582
  -6.750  -0.5024   0.02579   0.01666  -0.0568   0.9388   0.0610
  -6.500  -0.4712   0.02478   0.01562  -0.0580   0.9336   0.0647
  -6.250  -0.4486   0.02401   0.01475  -0.0574   0.9244   0.0678
  -6.000  -0.4163   0.02311   0.01383  -0.0588   0.9197   0.0714
  -5.750  -0.3941   0.02251   0.01319  -0.0581   0.9103   0.0757
  -5.500  -0.3613   0.02181   0.01248  -0.0593   0.9052   0.0821
  -5.250  -0.3363   0.02125   0.01187  -0.0589   0.8968   0.0907
  -5.000  -0.3056   0.02059   0.01114  -0.0596   0.8907   0.1075
  -4.500  -0.2536   0.01902   0.01014  -0.0596   0.8761   0.2207
  -4.250  -0.2180   0.01854   0.00971  -0.0612   0.8718   0.2620
  -4.000  -0.1957   0.01828   0.00949  -0.0602   0.8616   0.2882
  -3.750  -0.1602   0.01792   0.00914  -0.0616   0.8566   0.3154
  -3.500  -0.1357   0.01771   0.00891  -0.0609   0.8469   0.3358
  -3.250  -0.1005   0.01740   0.00857  -0.0623   0.8411   0.3593
  -3.000  -0.0747   0.01717   0.00837  -0.0619   0.8317   0.3822
  -2.750  -0.0407   0.01682   0.00806  -0.0630   0.8253   0.4126
  -2.500  -0.0147   0.01657   0.00786  -0.0626   0.8159   0.4390
  -2.250   0.0186   0.01621   0.00758  -0.0636   0.8091   0.4719
  -2.000   0.0429   0.01594   0.00753  -0.0627   0.7994   0.5151
  -1.750   0.0741   0.01572   0.00768  -0.0626   0.7926   0.5884
  -1.500   0.0979   0.01578   0.00775  -0.0615   0.7823   0.6485
  -1.250   0.1319   0.01573   0.00758  -0.0623   0.7752   0.6828
  -1.000   0.1576   0.01574   0.00755  -0.0616   0.7647   0.7042
  -0.750   0.1890   0.01569   0.00743  -0.0620   0.7563   0.7238
  -0.500   0.2187   0.01564   0.00733  -0.0620   0.7469   0.7409
  -0.250   0.2476   0.01562   0.00726  -0.0620   0.7372   0.7557
   0.000   0.2808   0.01555   0.00712  -0.0628   0.7282   0.7696
   0.250   0.3068   0.01556   0.00709  -0.0622   0.7167   0.7830
   0.500   0.3360   0.01554   0.00702  -0.0622   0.7056   0.7975
   0.750   0.3667   0.01550   0.00694  -0.0623   0.6947   0.8137
   1.000   0.3918   0.01552   0.00698  -0.0615   0.6819   0.8306
   1.250   0.4198   0.01554   0.00700  -0.0612   0.6694   0.8471
   1.500   0.4500   0.01557   0.00701  -0.0614   0.6573   0.8613
   1.750   0.4830   0.01563   0.00705  -0.0622   0.6457   0.8752
   2.000   0.5151   0.01572   0.00713  -0.0630   0.6314   0.8899
   2.250   0.5498   0.01582   0.00723  -0.0644   0.6180   0.9043
   2.500   0.5862   0.01594   0.00733  -0.0661   0.6047   0.9195
   2.750   0.6241   0.01607   0.00744  -0.0682   0.5923   0.9350
   3.000   0.6627   0.01621   0.00753  -0.0706   0.5804   0.9509
   3.250   0.7006   0.01638   0.00771  -0.0729   0.5682   0.9667
   3.500   0.7371   0.01655   0.00787  -0.0751   0.5564   0.9830
   3.750   0.7730   0.01675   0.00804  -0.0772   0.5449   0.9998
   4.000   0.7861   0.01688   0.00814  -0.0747   0.5349   1.0000
   4.250   0.8011   0.01706   0.00828  -0.0724   0.5242   1.0000
   4.500   0.8179   0.01725   0.00841  -0.0704   0.5131   1.0000
   4.750   0.8346   0.01747   0.00861  -0.0684   0.5015   1.0000
   5.000   0.8518   0.01770   0.00884  -0.0665   0.4904   1.0000
   5.250   0.8701   0.01794   0.00907  -0.0648   0.4799   1.0000
   5.500   0.8876   0.01820   0.00931  -0.0629   0.4682   1.0000
   5.750   0.9047   0.01847   0.00962  -0.0610   0.4564   1.0000
   6.000   0.9222   0.01875   0.00991  -0.0592   0.4451   1.0000
   6.250   0.9386   0.01904   0.01019  -0.0571   0.4321   1.0000
   6.500   0.9542   0.01935   0.01048  -0.0550   0.4188   1.0000
   6.750   0.9697   0.01968   0.01085  -0.0528   0.4056   1.0000
   7.000   0.9835   0.02002   0.01120  -0.0504   0.3917   1.0000
   7.250   0.9965   0.02040   0.01156  -0.0478   0.3780   1.0000
   7.500   1.0103   0.02081   0.01197  -0.0454   0.3661   1.0000
   7.750   1.0237   0.02125   0.01243  -0.0430   0.3546   1.0000
   8.000   1.0373   0.02172   0.01292  -0.0407   0.3429   1.0000
   8.250   1.0506   0.02222   0.01346  -0.0385   0.3311   1.0000
   8.500   1.0631   0.02278   0.01404  -0.0362   0.3194   1.0000
   8.750   1.0747   0.02338   0.01466  -0.0338   0.3077   1.0000
   9.000   1.0859   0.02403   0.01536  -0.0314   0.2952   1.0000
   9.250   1.0952   0.02475   0.01611  -0.0289   0.2806   1.0000
   9.500   1.1027   0.02557   0.01693  -0.0262   0.2646   1.0000
   9.750   1.1087   0.02649   0.01784  -0.0235   0.2477   1.0000
  10.000   1.1140   0.02751   0.01884  -0.0209   0.2311   1.0000
  10.250   1.1196   0.02860   0.01991  -0.0185   0.2159   1.0000
  10.500   1.1251   0.02976   0.02110  -0.0163   0.2021   1.0000
  10.750   1.1299   0.03102   0.02236  -0.0142   0.1889   1.0000
  11.000   1.1333   0.03243   0.02376  -0.0121   0.1760   1.0000
  11.250   1.1360   0.03397   0.02529  -0.0102   0.1648   1.0000
  11.500   1.1377   0.03566   0.02698  -0.0084   0.1552   1.0000
  11.750   1.1393   0.03746   0.02878  -0.0068   0.1464   1.0000
  12.000   1.1405   0.03938   0.03075  -0.0054   0.1382   1.0000
  12.250   1.1390   0.04161   0.03300  -0.0041   0.1306   1.0000
  12.500   1.1407   0.04369   0.03519  -0.0031   0.1225   1.0000
  12.750   1.1350   0.04650   0.03799  -0.0021   0.1142   1.0000
  13.000   1.1369   0.04881   0.04047  -0.0015   0.1022   1.0000
  13.250   1.1393   0.05118   0.04298  -0.0011   0.0670   1.0000
  13.500   1.1252   0.05531   0.04687  -0.0010   0.0581   1.0000
  13.750   1.1141   0.05932   0.05085  -0.0009   0.0531   1.0000
  14.000   1.1029   0.06352   0.05508  -0.0012   0.0498   1.0000
  14.250   1.0935   0.06768   0.05933  -0.0016   0.0470   1.0000
  14.500   1.0862   0.07173   0.06352  -0.0022   0.0447   1.0000
  14.750   1.0778   0.07604   0.06796  -0.0030   0.0427   1.0000
  15.000   1.0679   0.08067   0.07270  -0.0040   0.0411   1.0000
  15.250   1.0571   0.08556   0.07768  -0.0053   0.0398   1.0000
  15.500   1.0496   0.09007   0.08231  -0.0065   0.0384   1.0000
  15.750   1.0447   0.09429   0.08668  -0.0077   0.0370   1.0000
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