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FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il)
Reynolds number: 200,000
Max Cl/Cd: 44.3 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx711520-il-200000.txt
Download as CSV file: xf-fx711520-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/20 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -1.0609   0.05927   0.05336  -0.0307   1.0000   0.0339
 -13.000  -1.0637   0.05610   0.05003  -0.0304   1.0000   0.0338
 -12.750  -1.0705   0.05319   0.04693  -0.0297   1.0000   0.0338
 -12.500  -1.0694   0.05041   0.04399  -0.0290   1.0000   0.0337
 -12.250  -1.0711   0.04783   0.04121  -0.0279   1.0000   0.0337
 -12.000  -1.0639   0.04534   0.03858  -0.0270   1.0000   0.0335
 -11.750  -1.0571   0.04304   0.03610  -0.0259   1.0000   0.0335
 -11.500  -1.0454   0.04086   0.03375  -0.0250   1.0000   0.0333
 -11.250  -1.0301   0.03876   0.03149  -0.0243   1.0000   0.0332
 -11.000  -1.0113   0.03671   0.02928  -0.0239   1.0000   0.0331
 -10.750  -0.9903   0.03491   0.02735  -0.0237   1.0000   0.0331
 -10.500  -0.9665   0.03323   0.02554  -0.0237   1.0000   0.0332
 -10.250  -0.9414   0.03172   0.02394  -0.0237   1.0000   0.0333
 -10.000  -0.9160   0.03038   0.02253  -0.0237   1.0000   0.0335
  -9.750  -0.8916   0.02917   0.02124  -0.0236   1.0000   0.0339
  -9.500  -0.8652   0.02795   0.02015  -0.0237   1.0000   0.0344
  -9.250  -0.8407   0.02683   0.01908  -0.0243   0.9403   0.0350
  -9.000  -0.8059   0.02563   0.01778  -0.0268   0.9043   0.0360
  -8.750  -0.7872   0.02466   0.01670  -0.0265   0.8857   0.0369
  -8.500  -0.7732   0.02380   0.01573  -0.0252   0.8733   0.0377
  -8.250  -0.7648   0.02295   0.01487  -0.0231   0.8629   0.0387
  -8.000  -0.7529   0.02220   0.01407  -0.0214   0.8541   0.0403
  -7.750  -0.7391   0.02146   0.01326  -0.0198   0.8459   0.0422
  -7.500  -0.7251   0.02074   0.01250  -0.0183   0.8391   0.0451
  -7.250  -0.7101   0.01990   0.01165  -0.0169   0.8327   0.0506
  -7.000  -0.6974   0.01886   0.01070  -0.0152   0.8267   0.0640
  -6.750  -0.6849   0.01777   0.00985  -0.0136   0.8215   0.0991
  -6.500  -0.6700   0.01667   0.00911  -0.0125   0.8155   0.1539
  -6.250  -0.6545   0.01569   0.00847  -0.0113   0.8098   0.2192
  -6.000  -0.6389   0.01479   0.00793  -0.0100   0.8051   0.2934
  -5.750  -0.6205   0.01401   0.00757  -0.0090   0.7998   0.3736
  -5.500  -0.5983   0.01366   0.00746  -0.0082   0.7946   0.4340
  -5.250  -0.5739   0.01358   0.00749  -0.0075   0.7903   0.4756
  -5.000  -0.5486   0.01368   0.00759  -0.0068   0.7867   0.5063
  -4.750  -0.5213   0.01376   0.00767  -0.0066   0.7822   0.5293
  -4.500  -0.4942   0.01394   0.00787  -0.0062   0.7774   0.5499
  -4.250  -0.4674   0.01417   0.00804  -0.0057   0.7729   0.5670
  -4.000  -0.4406   0.01447   0.00829  -0.0051   0.7691   0.5808
  -3.750  -0.4128   0.01490   0.00875  -0.0046   0.7652   0.5952
  -3.500  -0.3849   0.01535   0.00923  -0.0040   0.7607   0.6102
  -3.250  -0.3576   0.01574   0.00959  -0.0035   0.7562   0.6232
  -3.000  -0.3300   0.01604   0.00989  -0.0028   0.7521   0.6310
  -2.750  -0.3031   0.01633   0.01013  -0.0020   0.7484   0.6389
  -2.500  -0.2754   0.01638   0.01015  -0.0021   0.7431   0.6477
  -2.250  -0.2473   0.01660   0.01042  -0.0016   0.7383   0.6529
  -2.000  -0.2199   0.01676   0.01055  -0.0012   0.7341   0.6599
  -1.750  -0.1931   0.01674   0.01041  -0.0010   0.7306   0.6677
  -1.500  -0.1657   0.01686   0.01054  -0.0006   0.7273   0.6714
  -1.250  -0.1374   0.01698   0.01072  -0.0006   0.7224   0.6761
  -1.000  -0.1097   0.01704   0.01076  -0.0006   0.7179   0.6821
  -0.750  -0.0822   0.01696   0.01060  -0.0007   0.7140   0.6883
  -0.500  -0.0549   0.01695   0.01061  -0.0003   0.7108   0.6915
  -0.250  -0.0277   0.01705   0.01070   0.0001   0.7071   0.6955
   0.000   0.0000   0.01709   0.01080   0.0000   0.7007   0.7006
   0.250   0.0277   0.01705   0.01070  -0.0001   0.6955   0.7071
   0.500   0.0549   0.01695   0.01061   0.0003   0.6915   0.7108
   0.750   0.0821   0.01696   0.01060   0.0008   0.6883   0.7140
   1.000   0.1097   0.01704   0.01077   0.0006   0.6822   0.7179
   1.250   0.1374   0.01698   0.01073   0.0006   0.6761   0.7224
   1.500   0.1657   0.01686   0.01055   0.0006   0.6714   0.7273
   1.750   0.1931   0.01674   0.01041   0.0010   0.6676   0.7306
   2.000   0.2198   0.01676   0.01055   0.0012   0.6599   0.7341
   2.250   0.2473   0.01660   0.01042   0.0016   0.6529   0.7383
   2.500   0.2754   0.01638   0.01015   0.0021   0.6477   0.7431
   2.750   0.3031   0.01633   0.01013   0.0020   0.6389   0.7484
   3.000   0.3300   0.01604   0.00990   0.0028   0.6310   0.7521
   3.250   0.3576   0.01574   0.00959   0.0035   0.6232   0.7562
   3.500   0.3849   0.01534   0.00922   0.0041   0.6101   0.7607
   3.750   0.4128   0.01488   0.00874   0.0046   0.5949   0.7652
   4.000   0.4406   0.01446   0.00828   0.0051   0.5805   0.7691
   4.250   0.4674   0.01417   0.00804   0.0057   0.5669   0.7729
   4.500   0.4942   0.01394   0.00786   0.0062   0.5498   0.7774
   4.750   0.5213   0.01376   0.00767   0.0066   0.5294   0.7822
   5.000   0.5487   0.01368   0.00758   0.0068   0.5061   0.7867
   5.250   0.5739   0.01358   0.00749   0.0075   0.4755   0.7903
   5.500   0.5983   0.01366   0.00746   0.0082   0.4339   0.7946
   5.750   0.6206   0.01401   0.00757   0.0090   0.3736   0.7998
   6.000   0.6390   0.01478   0.00793   0.0100   0.2940   0.8051
   6.250   0.6544   0.01570   0.00847   0.0113   0.2184   0.8098
   6.500   0.6698   0.01669   0.00912   0.0125   0.1527   0.8155
   6.750   0.6852   0.01775   0.00985   0.0136   0.1000   0.8214
   7.000   0.6973   0.01887   0.01071   0.0152   0.0637   0.8267
   7.250   0.7102   0.01990   0.01164   0.0169   0.0509   0.8327
   7.500   0.7251   0.02075   0.01251   0.0183   0.0450   0.8391
   7.750   0.7388   0.02149   0.01328   0.0198   0.0421   0.8459
   8.000   0.7531   0.02220   0.01407   0.0213   0.0403   0.8541
   8.250   0.7652   0.02295   0.01486   0.0230   0.0388   0.8628
   8.500   0.7734   0.02381   0.01573   0.0252   0.0378   0.8733
   8.750   0.7875   0.02467   0.01670   0.0264   0.0370   0.8856
   9.000   0.8062   0.02563   0.01779   0.0268   0.0359   0.9043
   9.250   0.8411   0.02683   0.01908   0.0242   0.0350   0.9400
   9.500   0.8656   0.02796   0.02015   0.0237   0.0343   1.0000
   9.750   0.8921   0.02917   0.02124   0.0236   0.0339   1.0000
  10.000   0.9165   0.03040   0.02255   0.0237   0.0335   1.0000
  10.250   0.9423   0.03172   0.02393   0.0236   0.0333   1.0000
  10.500   0.9672   0.03324   0.02556   0.0236   0.0332   1.0000
  10.750   0.9910   0.03490   0.02733   0.0236   0.0331   1.0000
  11.000   1.0122   0.03671   0.02928   0.0238   0.0331   1.0000
  11.250   1.0306   0.03874   0.03147   0.0243   0.0332   1.0000
  11.500   1.0459   0.04085   0.03374   0.0249   0.0333   1.0000
  11.750   1.0580   0.04308   0.03614   0.0258   0.0335   1.0000
  12.000   1.0636   0.04534   0.03858   0.0270   0.0335   1.0000
  12.250   1.0686   0.04788   0.04129   0.0280   0.0336   1.0000
  12.500   1.0671   0.05039   0.04399   0.0291   0.0336   1.0000
  12.750   1.0704   0.05318   0.04692   0.0297   0.0338   1.0000
  13.000   1.0660   0.05611   0.05002   0.0303   0.0338   1.0000
  13.250   1.0605   0.05926   0.05334   0.0307   0.0339   1.0000
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