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WORTMANN FX L V-152 AIRFOIL (fxlv152-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX L V-152 AIRFOIL (fxlv152-il)
Reynolds number: 50,000
Max Cl/Cd: 27.39 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxlv152-il-50000-n5.txt
Download as CSV file: xf-fxlv152-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX L V-152 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.8270   0.11458   0.10780   0.0031   1.0005   0.0716
 -14.000  -0.8625   0.10276   0.09588  -0.0040   1.0005   0.0706
 -13.750  -0.8991   0.09231   0.08526  -0.0102   1.0005   0.0695
 -13.500  -0.9301   0.08392   0.07662  -0.0146   1.0005   0.0691
 -13.250  -0.9526   0.07743   0.06988  -0.0175   1.0005   0.0696
 -13.000  -0.9718   0.07181   0.06396  -0.0196   1.0005   0.0706
 -12.750  -0.9897   0.06663   0.05840  -0.0210   1.0005   0.0719
 -12.500  -0.9825   0.06423   0.05600  -0.0210   1.0005   0.0746
 -12.250  -0.9839   0.06079   0.05232  -0.0213   1.0005   0.0769
 -12.000  -0.9864   0.05709   0.04820  -0.0213   1.0005   0.0792
 -11.750  -0.9694   0.05522   0.04637  -0.0209   1.0005   0.0822
 -11.500  -0.9617   0.05258   0.04344  -0.0206   1.0005   0.0860
 -11.250  -0.9471   0.05071   0.04154  -0.0201   1.0005   0.0901
 -11.000  -0.9340   0.04851   0.03905  -0.0196   1.0005   0.0953
 -10.750  -0.9158   0.04699   0.03758  -0.0190   1.0005   0.1003
 -10.500  -0.8980   0.04535   0.03579  -0.0184   1.0005   0.1064
 -10.250  -0.8828   0.04373   0.03403  -0.0179   1.0005   0.1138
 -10.000  -0.8702   0.04214   0.03247  -0.0174   1.0005   0.1220
  -9.750  -0.8591   0.04051   0.03082  -0.0170   1.0005   0.1320
  -9.500  -0.8474   0.03892   0.02922  -0.0164   1.0005   0.1434
  -9.250  -0.8349   0.03738   0.02768  -0.0157   1.0005   0.1559
  -9.000  -0.8221   0.03588   0.02623  -0.0149   1.0005   0.1690
  -8.750  -0.8106   0.03441   0.02484  -0.0139   1.0005   0.1831
  -8.500  -0.7993   0.03293   0.02349  -0.0130   1.0005   0.1995
  -8.250  -0.7885   0.03145   0.02214  -0.0120   1.0005   0.2207
  -8.000  -0.7784   0.03001   0.02094  -0.0110   1.0005   0.2462
  -7.750  -0.7677   0.02867   0.01979  -0.0099   1.0005   0.2805
  -7.500  -0.7554   0.02756   0.01898  -0.0086   1.0005   0.3188
  -7.250  -0.7393   0.02702   0.01882  -0.0070   1.0005   0.3604
  -7.000  -0.7205   0.02693   0.01890  -0.0056   1.0005   0.4020
  -6.750  -0.7022   0.02700   0.01903  -0.0041   1.0005   0.4374
  -6.500  -0.6894   0.02703   0.01904  -0.0022   1.0005   0.4674
  -6.250  -0.6639   0.02773   0.01969  -0.0014   0.9852   0.4938
  -6.000  -0.6283   0.02811   0.01981  -0.0032   0.9642   0.5221
  -5.250  -0.5225   0.02911   0.02014  -0.0067   0.9221   0.5779
  -5.000  -0.4897   0.02970   0.02058  -0.0065   0.9104   0.5912
  -4.750  -0.4577   0.03017   0.02090  -0.0063   0.9000   0.6043
  -4.500  -0.4321   0.03024   0.02079  -0.0058   0.8881   0.6182
  -4.250  -0.4086   0.03013   0.02050  -0.0054   0.8767   0.6313
  -4.000  -0.3794   0.03023   0.02048  -0.0049   0.8677   0.6391
  -3.750  -0.3591   0.02981   0.01988  -0.0046   0.8571   0.6499
  -3.500  -0.3318   0.02970   0.01963  -0.0043   0.8496   0.6560
  -3.250  -0.3079   0.02953   0.01935  -0.0040   0.8405   0.6635
  -3.000  -0.2852   0.02921   0.01890  -0.0037   0.8330   0.6721
  -2.750  -0.2591   0.02921   0.01881  -0.0033   0.8258   0.6785
  -2.500  -0.2382   0.02890   0.01839  -0.0031   0.8185   0.6885
  -2.250  -0.2104   0.02898   0.01841  -0.0025   0.8130   0.6946
  -2.000  -0.1897   0.02881   0.01818  -0.0022   0.8050   0.7048
  -1.750  -0.1640   0.02883   0.01814  -0.0016   0.7986   0.7115
  -1.500  -0.1400   0.02871   0.01797  -0.0013   0.7930   0.7193
  -1.250  -0.1185   0.02853   0.01774  -0.0013   0.7858   0.7263
  -1.000  -0.0927   0.02846   0.01764  -0.0010   0.7800   0.7313
  -0.750  -0.0690   0.02833   0.01745  -0.0009   0.7743   0.7381
  -0.500  -0.0462   0.02825   0.01736  -0.0010   0.7674   0.7446
  -0.250  -0.0199   0.02824   0.01735  -0.0008   0.7619   0.7495
   0.000   0.0053   0.02817   0.01725  -0.0008   0.7570   0.7556
   0.250   0.0272   0.02822   0.01731  -0.0008   0.7495   0.7622
   0.500   0.0533   0.02828   0.01740  -0.0006   0.7439   0.7673
   0.750   0.0795   0.02828   0.01740  -0.0006   0.7396   0.7734
   1.000   0.0999   0.02848   0.01766  -0.0006   0.7317   0.7800
   1.250   0.1250   0.02860   0.01783  -0.0003   0.7257   0.7855
   1.500   0.1501   0.02864   0.01789   0.0000   0.7205   0.7922
   1.750   0.1703   0.02888   0.01821   0.0002   0.7113   0.7988
   2.000   0.1969   0.02884   0.01823   0.0007   0.7045   0.8043
   2.250   0.2175   0.02902   0.01848   0.0012   0.6944   0.8118
   2.500   0.2433   0.02900   0.01852   0.0017   0.6872   0.8182
   2.750   0.2659   0.02922   0.01884   0.0022   0.6788   0.8253
   3.000   0.2893   0.02937   0.01909   0.0025   0.6712   0.8332
   3.250   0.3180   0.02933   0.01914   0.0029   0.6660   0.8396
   3.500   0.3361   0.02985   0.01980   0.0032   0.6554   0.8488
   3.750   0.3640   0.02985   0.01994   0.0036   0.6491   0.8564
   4.000   0.3835   0.03032   0.02058   0.0040   0.6384   0.8668
   4.250   0.4126   0.03022   0.02063   0.0044   0.6305   0.8757
   4.500   0.4340   0.03042   0.02100   0.0051   0.6170   0.8875
   4.750   0.4632   0.03012   0.02085   0.0056   0.6047   0.8982
   5.000   0.4955   0.02958   0.02046   0.0059   0.5920   0.9089
   5.250   0.5233   0.02939   0.02046   0.0060   0.5758   0.9216
   5.500   0.5563   0.02911   0.02039   0.0052   0.5592   0.9336
   5.750   0.5916   0.02881   0.02032   0.0041   0.5414   0.9462
   6.000   0.6283   0.02836   0.02010   0.0027   0.5202   0.9616
   6.250   0.6671   0.02756   0.01949   0.0013   0.4946   0.9798
   6.500   0.6936   0.02715   0.01920   0.0013   0.4647   0.9995
   6.750   0.7065   0.02693   0.01896   0.0036   0.4362   0.9995
   7.000   0.7236   0.02684   0.01881   0.0053   0.4013   0.9995
   7.250   0.7406   0.02704   0.01884   0.0068   0.3597   0.9995
   7.500   0.7557   0.02760   0.01906   0.0085   0.3185   0.9995
   7.750   0.7672   0.02869   0.01987   0.0099   0.2805   0.9995
   8.000   0.7772   0.03000   0.02097   0.0112   0.2470   0.9995
   8.250   0.7860   0.03143   0.02214   0.0124   0.2220   0.9995
   8.500   0.7956   0.03291   0.02343   0.0135   0.2015   0.9995
   8.750   0.8059   0.03434   0.02475   0.0146   0.1851   0.9995
   9.000   0.8166   0.03580   0.02610   0.0157   0.1712   0.9995
   9.250   0.8292   0.03728   0.02755   0.0166   0.1577   0.9995
   9.500   0.8412   0.03882   0.02908   0.0174   0.1450   0.9995
   9.750   0.8527   0.04040   0.03071   0.0180   0.1335   0.9995
  10.000   0.8633   0.04204   0.03239   0.0185   0.1231   0.9995
  10.250   0.8754   0.04365   0.03404   0.0190   0.1146   0.9995
  10.500   0.8904   0.04513   0.03547   0.0196   0.1080   0.9995
  10.750   0.9071   0.04681   0.03738   0.0203   0.1014   0.9995
  11.000   0.9231   0.04852   0.03918   0.0210   0.0960   0.9995
  11.250   0.9372   0.05033   0.04108   0.0215   0.0910   0.9995
  11.500   0.9485   0.05254   0.04348   0.0220   0.0867   0.9995
  11.750   0.9607   0.05463   0.04569   0.0225   0.0830   0.9995
  12.000   0.9711   0.05717   0.04841   0.0229   0.0802   0.9995
  12.250   0.9729   0.06043   0.05197   0.0231   0.0778   0.9995
  12.500   0.9785   0.06307   0.05471   0.0232   0.0753   0.9995
  12.750   0.9743   0.06661   0.05845   0.0229   0.0732   0.9995
  13.000   0.9586   0.07146   0.06362   0.0216   0.0719   0.9995
  13.250   0.9429   0.07649   0.06890   0.0200   0.0705   0.9995
  13.500   0.9502   0.07853   0.07087   0.0198   0.0674   0.9995
  13.750   0.9251   0.08522   0.07784   0.0169   0.0672   0.9995
  14.000   0.8979   0.09280   0.08564   0.0131   0.0672   0.9995
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