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FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 38-153 AIRFOIL (fx38153-il)
Reynolds number: 50,000
Max Cl/Cd: 26.56 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx38153-il-50000-n5.txt
Download as CSV file: xf-fx38153-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 38-153 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5177   0.10821   0.10135  -0.0491   1.0001   0.0369
 -10.500  -0.5333   0.10253   0.09570  -0.0509   1.0001   0.0363
 -10.250  -0.5539   0.09711   0.09032  -0.0521   1.0001   0.0357
 -10.000  -0.5784   0.09222   0.08541  -0.0523   1.0001   0.0352
  -9.750  -0.6055   0.08798   0.08113  -0.0513   1.0001   0.0348
  -9.500  -0.6342   0.08441   0.07750  -0.0490   1.0001   0.0344
  -9.250  -0.6645   0.08149   0.07450  -0.0453   1.0001   0.0341
  -9.000  -0.6941   0.07879   0.07169  -0.0410   1.0001   0.0337
  -8.750  -0.7179   0.07545   0.06815  -0.0373   1.0001   0.0333
  -8.500  -0.7368   0.07192   0.06434  -0.0336   1.0001   0.0328
  -8.250  -0.7522   0.06831   0.06026  -0.0299   1.0001   0.0323
  -8.000  -0.7553   0.06523   0.05694  -0.0272   1.0001   0.0323
  -7.750  -0.7556   0.06216   0.05358  -0.0247   1.0001   0.0322
  -7.500  -0.7528   0.05912   0.05021  -0.0224   1.0001   0.0321
  -7.250  -0.7467   0.05616   0.04689  -0.0203   1.0001   0.0321
  -7.000  -0.7375   0.05332   0.04362  -0.0184   1.0001   0.0322
  -6.750  -0.7250   0.05066   0.04057  -0.0167   1.0001   0.0323
  -6.500  -0.7101   0.04828   0.03791  -0.0153   1.0001   0.0327
  -6.250  -0.6939   0.04637   0.03586  -0.0142   1.0001   0.0336
  -6.000  -0.6764   0.04462   0.03388  -0.0130   1.0001   0.0349
  -5.750  -0.6572   0.04293   0.03191  -0.0117   1.0001   0.0366
  -5.500  -0.6363   0.04139   0.03000  -0.0103   1.0001   0.0382
  -5.250  -0.6148   0.03999   0.02840  -0.0088   1.0001   0.0398
  -5.000  -0.5939   0.03883   0.02721  -0.0074   1.0001   0.0415
  -4.750  -0.5726   0.03790   0.02619  -0.0057   1.0001   0.0437
  -4.500  -0.5450   0.03716   0.02522  -0.0050   0.9981   0.0469
  -4.250  -0.5176   0.03639   0.02443  -0.0053   0.9950   0.0529
  -4.000  -0.4909   0.03572   0.02365  -0.0056   0.9914   0.0670
  -3.750  -0.4671   0.03467   0.02279  -0.0059   0.9876   0.0886
  -3.500  -0.4436   0.03306   0.02162  -0.0062   0.9841   0.1384
  -3.250  -0.4467   0.03167   0.02348   0.0024   0.9812   0.5841
  -3.000  -0.4329   0.03401   0.02570   0.0082   0.9753   0.7537
  -2.750  -0.4131   0.03745   0.02895   0.0162   0.9713   0.8246
  -2.500  -0.3654   0.03955   0.03065   0.0172   0.9703   0.8743
  -2.250  -0.3270   0.03980   0.03054   0.0152   0.9667   0.8904
  -2.000  -0.2929   0.03967   0.03012   0.0132   0.9614   0.8972
  -1.750  -0.2624   0.03967   0.02985   0.0116   0.9563   0.9057
  -1.500  -0.2263   0.03959   0.02950   0.0091   0.9509   0.9112
  -1.250  -0.1969   0.03948   0.02919   0.0077   0.9446   0.9168
  -1.000  -0.1653   0.03953   0.02905   0.0058   0.9396   0.9224
  -0.750  -0.1360   0.03937   0.02871   0.0044   0.9327   0.9267
  -0.500  -0.1033   0.03939   0.02858   0.0023   0.9267   0.9317
  -0.250  -0.0771   0.03931   0.02837   0.0016   0.9191   0.9366
   0.000  -0.0391   0.03932   0.02824  -0.0015   0.9124   0.9396
   0.250  -0.0090   0.03928   0.02811  -0.0030   0.9048   0.9433
   0.500   0.0174   0.03925   0.02800  -0.0038   0.8972   0.9474
   0.750   0.0472   0.03923   0.02790  -0.0053   0.8895   0.9505
   1.000   0.0837   0.03922   0.02783  -0.0080   0.8819   0.9531
   1.250   0.1120   0.03914   0.02771  -0.0091   0.8722   0.9565
   1.500   0.1487   0.03909   0.02762  -0.0115   0.8652   0.9596
   1.750   0.1716   0.03899   0.02752  -0.0116   0.8544   0.9628
   2.000   0.2045   0.03896   0.02749  -0.0136   0.8460   0.9652
   2.250   0.2377   0.03886   0.02741  -0.0154   0.8373   0.9676
   2.750   0.2873   0.03857   0.02717  -0.0158   0.8151   0.9732
   3.000   0.3264   0.03833   0.02698  -0.0184   0.8065   0.9749
   3.250   0.3514   0.03824   0.02696  -0.0188   0.7942   0.9773
   3.500   0.3772   0.03811   0.02690  -0.0192   0.7822   0.9796
   3.750   0.4070   0.03784   0.02672  -0.0199   0.7708   0.9820
   4.000   0.4423   0.03737   0.02634  -0.0214   0.7608   0.9841
   4.250   0.4696   0.03714   0.02622  -0.0219   0.7470   0.9862
   4.500   0.4969   0.03687   0.02608  -0.0221   0.7332   0.9884
   4.750   0.5247   0.03652   0.02585  -0.0224   0.7192   0.9908
   5.000   0.5534   0.03604   0.02549  -0.0225   0.7050   0.9932
   5.250   0.5840   0.03539   0.02500  -0.0228   0.6903   0.9953
   5.500   0.6145   0.03468   0.02444  -0.0229   0.6750   0.9972
   5.750   0.6443   0.03397   0.02387  -0.0228   0.6587   0.9993
   6.000   0.6677   0.03334   0.02337  -0.0216   0.6418   0.9999
   6.250   0.6909   0.03266   0.02279  -0.0201   0.6240   0.9999
   6.500   0.7188   0.03186   0.02210  -0.0193   0.6053   0.9999
   6.750   0.7351   0.03154   0.02184  -0.0169   0.5822   0.9999
   7.000   0.7597   0.03098   0.02131  -0.0156   0.5581   0.9999
   7.250   0.7764   0.03082   0.02118  -0.0135   0.5337   0.9999
   7.500   0.7968   0.03064   0.02102  -0.0119   0.5097   0.9999
   7.750   0.8075   0.03076   0.02115  -0.0090   0.4845   0.9999
   8.000   0.8200   0.03087   0.02120  -0.0064   0.4583   0.9999
   8.250   0.8276   0.03118   0.02148  -0.0032   0.4316   0.9999
   8.500   0.8361   0.03162   0.02189  -0.0005   0.4056   0.9999
   8.750   0.8468   0.03217   0.02239   0.0018   0.3806   0.9999
   9.000   0.8580   0.03286   0.02311   0.0037   0.3570   0.9999
   9.250   0.8733   0.03358   0.02380   0.0050   0.3361   0.9999
   9.500   0.8874   0.03447   0.02476   0.0062   0.3151   0.9999
   9.750   0.9006   0.03543   0.02575   0.0075   0.2944   0.9999
  10.000   0.9130   0.03647   0.02676   0.0087   0.2743   0.9999
  10.250   0.9240   0.03765   0.02797   0.0098   0.2547   0.9999
  10.500   0.9367   0.03887   0.02927   0.0107   0.2375   0.9999
  10.750   0.9515   0.04011   0.03057   0.0113   0.2223   0.9999
  11.000   0.9653   0.04146   0.03202   0.0120   0.2074   0.9999
  11.250   0.9752   0.04295   0.03360   0.0128   0.1927   0.9999
  11.500   0.9825   0.04456   0.03526   0.0137   0.1786   0.9999
  11.750   0.9882   0.04633   0.03709   0.0146   0.1651   0.9999
  12.000   0.9935   0.04825   0.03916   0.0153   0.1522   0.9999
  12.250   1.0002   0.05025   0.04135   0.0158   0.1408   0.9999
  12.500   1.0061   0.05239   0.04364   0.0163   0.1304   0.9999
  12.750   1.0102   0.05464   0.04593   0.0167   0.1211   0.9999
  13.000   1.0119   0.05724   0.04874   0.0169   0.1114   0.9999
  13.250   1.0129   0.06003   0.05172   0.0170   0.1028   0.9999
  13.500   1.0140   0.06272   0.05445   0.0169   0.0964   0.9999
  13.750   1.0163   0.06587   0.05789   0.0167   0.0898   0.9999
  14.000   1.0171   0.06889   0.06097   0.0164   0.0845   0.9999
  14.250   1.0173   0.07241   0.06471   0.0159   0.0798   0.9999
  14.500   1.0148   0.07640   0.06900   0.0151   0.0757   0.9999
  14.750   1.0136   0.08005   0.07278   0.0142   0.0724   0.9999
  15.000   1.0120   0.08395   0.07679   0.0131   0.0697   0.9999
  15.250   1.0006   0.08964   0.08283   0.0110   0.0677   0.9999
  15.500   0.9869   0.09587   0.08935   0.0083   0.0661   0.9999
  15.750   0.9703   0.10294   0.09667   0.0048   0.0649   0.9999
  16.000   0.9473   0.11171   0.10569  -0.0001   0.0644   0.9999
  16.250   0.9041   0.12592   0.12015  -0.0086   0.0653   0.9999
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