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WORTMANN FX L V-152 AIRFOIL (fxlv152-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX L V-152 AIRFOIL (fxlv152-il)
Reynolds number: 50,000
Max Cl/Cd: 27.06 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxlv152-il-50000.txt
Download as CSV file: xf-fxlv152-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8847   0.08625   0.07967  -0.0143   1.0005   0.1504
 -11.750  -0.9100   0.07922   0.07257  -0.0170   1.0005   0.1494
 -11.500  -0.9396   0.07296   0.06617  -0.0188   1.0005   0.1483
 -11.250  -0.9682   0.06775   0.06077  -0.0189   1.0005   0.1475
 -11.000  -0.9882   0.06293   0.05564  -0.0184   1.0005   0.1475
 -10.750  -1.0014   0.05844   0.05075  -0.0175   1.0005   0.1484
 -10.500  -1.0108   0.05436   0.04612  -0.0162   1.0005   0.1502
 -10.250  -0.9875   0.05126   0.04312  -0.0161   1.0005   0.1570
 -10.000  -0.9831   0.04787   0.03927  -0.0150   1.0005   0.1623
  -9.750  -0.9650   0.04473   0.03602  -0.0146   1.0005   0.1697
  -9.500  -0.9515   0.04189   0.03279  -0.0137   1.0005   0.1784
  -9.250  -0.9277   0.03953   0.03050  -0.0134   1.0005   0.1913
  -9.000  -0.9091   0.03752   0.02848  -0.0127   1.0005   0.2078
  -8.750  -0.8925   0.03564   0.02657  -0.0118   1.0005   0.2276
  -8.500  -0.8685   0.03408   0.02538  -0.0112   1.0005   0.2508
  -8.250  -0.8495   0.03238   0.02373  -0.0103   1.0005   0.2759
  -8.000  -0.8279   0.03078   0.02243  -0.0092   1.0005   0.3069
  -7.750  -0.8088   0.02953   0.02157  -0.0076   1.0005   0.3470
  -7.500  -0.7876   0.02947   0.02202  -0.0052   1.0005   0.3961
  -7.250  -0.7612   0.03087   0.02374  -0.0020   1.0005   0.4489
  -7.000  -0.7155   0.03492   0.02786   0.0019   1.0005   0.4901
  -6.750  -0.6798   0.03784   0.03066   0.0054   1.0005   0.5230
  -6.500  -0.6233   0.04263   0.03523   0.0095   1.0005   0.5488
  -6.250  -0.6079   0.04307   0.03557   0.0121   1.0005   0.5773
  -6.000  -0.5538   0.04584   0.03809   0.0145   1.0005   0.5989
  -5.750  -0.5111   0.04697   0.03903   0.0157   1.0005   0.6210
  -5.500  -0.4852   0.04702   0.03896   0.0168   1.0005   0.6420
  -5.250  -0.4798   0.04670   0.03859   0.0197   1.0005   0.6599
  -5.000  -0.5080   0.04596   0.03789   0.0261   1.0005   0.6740
  -4.750  -0.5277   0.04519   0.03712   0.0316   1.0005   0.6899
  -4.500  -0.5140   0.04513   0.03695   0.0342   1.0005   0.7086
  -4.250  -0.4996   0.04493   0.03666   0.0364   1.0005   0.7274
  -4.000  -0.4923   0.04446   0.03611   0.0391   1.0005   0.7452
  -3.750  -0.4974   0.04366   0.03525   0.0429   1.0005   0.7614
  -3.500  -0.4862   0.04313   0.03462   0.0448   1.0005   0.7777
  -3.250  -0.4569   0.04274   0.03411   0.0441   1.0005   0.7925
  -3.000  -0.4388   0.04212   0.03339   0.0445   1.0005   0.8058
  -2.750  -0.4451   0.04116   0.03237   0.0480   1.0005   0.8180
  -2.500  -0.4088   0.04056   0.03162   0.0443   0.9939   0.8300
  -2.250  -0.3566   0.04012   0.03104   0.0382   0.9879   0.8400
  -2.000  -0.3471   0.03939   0.03021   0.0386   0.9802   0.8510
  -1.750  -0.2691   0.03928   0.02995   0.0284   0.9741   0.8616
  -1.500  -0.2389   0.03889   0.02947   0.0257   0.9675   0.8718
  -1.250  -0.1979   0.03864   0.02915   0.0214   0.9608   0.8825
  -1.000  -0.1296   0.03848   0.02891   0.0123   0.9547   0.8935
  -0.750  -0.1248   0.03826   0.02867   0.0141   0.9470   0.9035
  -0.500  -0.0560   0.03812   0.02849   0.0048   0.9410   0.9125
  -0.250  -0.0444   0.03808   0.02843   0.0052   0.9346   0.9207
   0.000   0.0044   0.03799   0.02834  -0.0008   0.9270   0.9270
   0.250   0.0544   0.03804   0.02838  -0.0071   0.9204   0.9339
   0.500   0.0641   0.03813   0.02850  -0.0063   0.9126   0.9409
   0.750   0.1339   0.03819   0.02861  -0.0157   0.9035   0.9476
   1.000   0.1377   0.03846   0.02890  -0.0138   0.8934   0.9543
   1.250   0.2098   0.03853   0.02905  -0.0235   0.8825   0.9602
   1.500   0.2472   0.03878   0.02938  -0.0272   0.8715   0.9675
   1.750   0.2840   0.03913   0.02982  -0.0309   0.8613   0.9740
   2.000   0.3453   0.03931   0.03013  -0.0386   0.8512   0.9802
   2.250   0.3619   0.04002   0.03094  -0.0392   0.8407   0.9877
   2.500   0.4263   0.04023   0.03132  -0.0470   0.8295   0.9939
   2.750   0.4458   0.04101   0.03221  -0.0482   0.8175   0.9995
   3.000   0.4440   0.04200   0.03328  -0.0454   0.8066   0.9995
   3.250   0.4729   0.04247   0.03386  -0.0463   0.7928   0.9995
   3.500   0.4884   0.04300   0.03449  -0.0451   0.7772   0.9995
   3.750   0.4814   0.04388   0.03543  -0.0412   0.7615   0.9995
   4.000   0.4756   0.04475   0.03635  -0.0374   0.7462   0.9995
   4.250   0.4788   0.04537   0.03704  -0.0345   0.7293   0.9995
   4.500   0.4891   0.04569   0.03745  -0.0320   0.7103   0.9995
   4.750   0.4994   0.04588   0.03772  -0.0292   0.6912   0.9995
   5.000   0.4949   0.04632   0.03821  -0.0251   0.6746   0.9995
   5.250   0.4891   0.04671   0.03863  -0.0208   0.6588   0.9995
   5.500   0.4936   0.04695   0.03893  -0.0175   0.6414   0.9995
   5.750   0.5099   0.04712   0.03918  -0.0157   0.6208   0.9995
   6.000   0.5417   0.04661   0.03883  -0.0144   0.5981   0.9995
   6.250   0.5914   0.04444   0.03689  -0.0124   0.5751   0.9995
   6.500   0.6508   0.04023   0.03292  -0.0090   0.5516   0.9995
   6.750   0.6724   0.03875   0.03157  -0.0058   0.5209   0.9995
   7.000   0.7184   0.03481   0.02777  -0.0021   0.4894   0.9995
   7.250   0.7613   0.03114   0.02405   0.0016   0.4466   0.9995
   7.500   0.7902   0.02948   0.02203   0.0048   0.3941   0.9995
   8.000   0.8317   0.03074   0.02229   0.0088   0.3058   0.9995
   8.250   0.8498   0.03243   0.02385   0.0100   0.2753   0.9995
   8.500   0.8710   0.03408   0.02530   0.0109   0.2504   0.9995
   8.750   0.8888   0.03580   0.02698   0.0119   0.2284   0.9995
   9.000   0.9066   0.03752   0.02861   0.0128   0.2080   0.9995
   9.250   0.9254   0.03947   0.03053   0.0136   0.1914   0.9995
   9.500   0.9448   0.04197   0.03314   0.0142   0.1796   0.9995
   9.750   0.9683   0.04471   0.03583   0.0145   0.1696   0.9995
  10.000   0.9753   0.04777   0.03935   0.0157   0.1629   0.9995
  10.250   0.9964   0.05079   0.04233   0.0160   0.1554   0.9995
  10.500   0.9911   0.05445   0.04654   0.0176   0.1523   0.9995
  10.750   0.9843   0.05841   0.05089   0.0188   0.1501   0.9995
  11.000   0.9713   0.06272   0.05553   0.0198   0.1490   0.9995
  11.250   0.9454   0.06746   0.06054   0.0206   0.1495   0.9995
  11.500   0.9082   0.07345   0.06672   0.0196   0.1511   0.9995
  11.750   0.8660   0.08123   0.07460   0.0163   0.1536   0.9995
  12.000   0.8336   0.08969   0.08310   0.0123   0.1555   0.9995
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