Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il)
Reynolds number: 100,000
Max Cl/Cd: 34.18 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx711525-il-100000-n5.txt
Download as CSV file: xf-fx711525-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/25 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.8575   0.10235   0.09611  -0.0136   1.0000   0.0278
 -15.000  -0.8835   0.09359   0.08710  -0.0191   1.0000   0.0276
 -14.750  -0.9015   0.08691   0.08023  -0.0229   1.0000   0.0276
 -14.500  -0.9184   0.08091   0.07402  -0.0260   1.0000   0.0275
 -14.250  -0.9336   0.07549   0.06837  -0.0284   1.0000   0.0275
 -14.000  -0.9449   0.07085   0.06351  -0.0302   1.0000   0.0275
 -13.750  -0.9545   0.06655   0.05898  -0.0315   1.0000   0.0275
 -13.500  -0.9608   0.06275   0.05494  -0.0323   1.0000   0.0276
 -13.250  -0.9638   0.05938   0.05134  -0.0328   1.0000   0.0277
 -13.000  -0.9616   0.05657   0.04838  -0.0329   1.0000   0.0278
 -12.750  -0.9558   0.05418   0.04589  -0.0329   1.0000   0.0280
 -12.500  -0.9488   0.05192   0.04353  -0.0327   1.0000   0.0283
 -12.250  -0.9407   0.04981   0.04131  -0.0324   1.0000   0.0285
 -12.000  -0.9313   0.04783   0.03923  -0.0321   1.0000   0.0288
 -11.750  -0.9208   0.04597   0.03728  -0.0317   1.0000   0.0291
 -11.500  -0.9096   0.04417   0.03539  -0.0312   1.0000   0.0296
 -11.250  -0.8976   0.04249   0.03361  -0.0306   1.0000   0.0301
 -11.000  -0.8851   0.04090   0.03192  -0.0300   1.0000   0.0307
 -10.750  -0.8725   0.03936   0.03027  -0.0293   1.0000   0.0313
 -10.500  -0.8615   0.03784   0.02875  -0.0286   1.0000   0.0318
 -10.250  -0.8512   0.03634   0.02724  -0.0280   1.0000   0.0325
 -10.000  -0.8405   0.03493   0.02580  -0.0273   1.0000   0.0332
  -9.750  -0.8299   0.03353   0.02434  -0.0265   1.0000   0.0347
  -9.500  -0.8197   0.03217   0.02297  -0.0257   1.0000   0.0361
  -9.250  -0.8095   0.03086   0.02165  -0.0249   1.0000   0.0376
  -9.000  -0.7995   0.02961   0.02038  -0.0239   1.0000   0.0400
  -8.750  -0.7900   0.02844   0.01922  -0.0227   1.0000   0.0424
  -8.500  -0.7809   0.02735   0.01812  -0.0212   1.0000   0.0453
  -8.250  -0.7710   0.02629   0.01707  -0.0198   0.9757   0.0497
  -8.000  -0.7442   0.02503   0.01578  -0.0215   0.9256   0.0581
  -7.750  -0.7216   0.02399   0.01473  -0.0220   0.9032   0.0693
  -7.500  -0.7029   0.02311   0.01384  -0.0215   0.8871   0.0857
  -7.250  -0.6869   0.02222   0.01305  -0.0205   0.8748   0.1066
  -7.000  -0.6705   0.02144   0.01233  -0.0194   0.8648   0.1321
  -6.750  -0.6548   0.02062   0.01165  -0.0182   0.8559   0.1651
  -6.500  -0.6407   0.01971   0.01097  -0.0168   0.8477   0.2106
  -6.250  -0.6271   0.01878   0.01036  -0.0152   0.8403   0.2719
  -6.000  -0.6133   0.01793   0.00993  -0.0135   0.8330   0.3464
  -5.750  -0.5955   0.01751   0.00985  -0.0119   0.8268   0.4159
  -5.500  -0.5737   0.01744   0.00996  -0.0106   0.8207   0.4653
  -5.250  -0.5502   0.01749   0.01002  -0.0096   0.8142   0.5001
  -5.000  -0.5258   0.01761   0.01007  -0.0086   0.8088   0.5253
  -4.750  -0.5007   0.01770   0.01008  -0.0079   0.8035   0.5453
  -4.500  -0.4751   0.01783   0.01015  -0.0073   0.7979   0.5617
  -4.250  -0.4490   0.01801   0.01025  -0.0065   0.7927   0.5762
  -4.000  -0.4232   0.01816   0.01031  -0.0059   0.7875   0.5901
  -3.750  -0.3962   0.01841   0.01053  -0.0053   0.7816   0.6013
  -3.500  -0.3698   0.01858   0.01062  -0.0047   0.7767   0.6114
  -3.250  -0.3438   0.01871   0.01066  -0.0041   0.7719   0.6215
  -3.000  -0.3172   0.01879   0.01071  -0.0038   0.7658   0.6296
  -2.750  -0.2906   0.01892   0.01078  -0.0032   0.7606   0.6367
  -2.500  -0.2653   0.01886   0.01060  -0.0029   0.7556   0.6459
  -2.250  -0.2379   0.01901   0.01077  -0.0026   0.7496   0.6511
  -2.000  -0.2115   0.01905   0.01075  -0.0021   0.7445   0.6576
  -1.750  -0.1860   0.01895   0.01053  -0.0019   0.7399   0.6653
  -1.500  -0.1589   0.01903   0.01065  -0.0016   0.7336   0.6695
  -1.250  -0.1323   0.01907   0.01066  -0.0012   0.7283   0.6751
  -1.000  -0.1064   0.01900   0.01050  -0.0009   0.7241   0.6827
  -0.750  -0.0797   0.01903   0.01054  -0.0007   0.7185   0.6874
  -0.500  -0.0530   0.01906   0.01060  -0.0004   0.7126   0.6920
  -0.250  -0.0265   0.01904   0.01054  -0.0002   0.7079   0.6978
   0.000   0.0000   0.01897   0.01039   0.0000   0.7043   0.7043
   0.250   0.0265   0.01904   0.01054   0.0001   0.6978   0.7079
   0.500   0.0530   0.01906   0.01059   0.0004   0.6920   0.7126
   0.750   0.0797   0.01903   0.01054   0.0007   0.6874   0.7185
   1.000   0.1064   0.01900   0.01050   0.0009   0.6827   0.7241
   1.250   0.1323   0.01907   0.01066   0.0012   0.6751   0.7284
   1.500   0.1589   0.01903   0.01065   0.0016   0.6695   0.7336
   1.750   0.1860   0.01895   0.01053   0.0019   0.6653   0.7399
   2.000   0.2115   0.01905   0.01075   0.0021   0.6576   0.7445
   2.250   0.2379   0.01901   0.01077   0.0026   0.6510   0.7497
   2.500   0.2653   0.01886   0.01060   0.0029   0.6459   0.7556
   2.750   0.2906   0.01892   0.01078   0.0032   0.6367   0.7606
   3.000   0.3173   0.01879   0.01071   0.0038   0.6296   0.7658
   3.250   0.3438   0.01871   0.01066   0.0041   0.6215   0.7720
   3.500   0.3698   0.01858   0.01062   0.0046   0.6115   0.7767
   3.750   0.3962   0.01841   0.01053   0.0053   0.6013   0.7816
   4.000   0.4232   0.01817   0.01031   0.0058   0.5901   0.7875
   4.250   0.4490   0.01801   0.01025   0.0065   0.5763   0.7927
   4.500   0.4751   0.01783   0.01015   0.0073   0.5616   0.7979
   4.750   0.5008   0.01770   0.01008   0.0079   0.5452   0.8035
   5.000   0.5258   0.01761   0.01007   0.0086   0.5252   0.8088
   5.250   0.5502   0.01749   0.01002   0.0096   0.5002   0.8142
   5.500   0.5737   0.01744   0.00996   0.0106   0.4653   0.8207
   5.750   0.5955   0.01751   0.00985   0.0119   0.4158   0.8269
   6.000   0.6131   0.01794   0.00993   0.0135   0.3454   0.8330
   6.250   0.6270   0.01879   0.01036   0.0152   0.2712   0.8404
   6.500   0.6407   0.01972   0.01098   0.0167   0.2100   0.8476
   6.750   0.6549   0.02062   0.01164   0.0182   0.1651   0.8559
   7.000   0.6706   0.02144   0.01234   0.0194   0.1319   0.8648
   7.250   0.6868   0.02224   0.01306   0.0205   0.1057   0.8748
   7.500   0.7030   0.02311   0.01384   0.0215   0.0855   0.8871
   7.750   0.7218   0.02399   0.01472   0.0220   0.0694   0.9032
   8.000   0.7443   0.02504   0.01579   0.0215   0.0577   0.9257
   8.250   0.7712   0.02629   0.01706   0.0197   0.0497   0.9763
   8.500   0.7813   0.02734   0.01812   0.0212   0.0454   1.0000
   8.750   0.7903   0.02844   0.01922   0.0227   0.0423   1.0000
   9.000   0.7996   0.02963   0.02039   0.0239   0.0401   1.0000
   9.250   0.8097   0.03088   0.02167   0.0249   0.0380   1.0000
   9.500   0.8199   0.03218   0.02299   0.0257   0.0362   1.0000
   9.750   0.8301   0.03354   0.02435   0.0265   0.0347   1.0000
  10.000   0.8411   0.03492   0.02578   0.0272   0.0335   1.0000
  10.250   0.8516   0.03635   0.02725   0.0279   0.0325   1.0000
  10.500   0.8623   0.03781   0.02873   0.0286   0.0319   1.0000
  10.750   0.8731   0.03936   0.03028   0.0292   0.0312   1.0000
  11.000   0.8858   0.04086   0.03188   0.0299   0.0307   1.0000
  11.250   0.8983   0.04249   0.03360   0.0305   0.0301   1.0000
  11.500   0.9105   0.04415   0.03536   0.0311   0.0297   1.0000
  11.750   0.9217   0.04595   0.03725   0.0316   0.0292   1.0000
  12.000   0.9323   0.04780   0.03920   0.0320   0.0289   1.0000
  12.250   0.9415   0.04980   0.04130   0.0324   0.0285   1.0000
  12.500   0.9498   0.05191   0.04351   0.0326   0.0282   1.0000
  12.750   0.9566   0.05417   0.04588   0.0328   0.0280   1.0000
  13.000   0.9624   0.05658   0.04840   0.0328   0.0278   1.0000
  13.250   0.9638   0.05948   0.05146   0.0327   0.0277   1.0000
  13.500   0.9621   0.06270   0.05488   0.0323   0.0276   1.0000
  13.750   0.9561   0.06647   0.05888   0.0314   0.0275   1.0000
  14.000   0.9464   0.07078   0.06343   0.0301   0.0275   1.0000
  14.250   0.9357   0.07536   0.06823   0.0284   0.0275   1.0000
  14.500   0.9208   0.08070   0.07379   0.0260   0.0275   1.0000
  14.750   0.9039   0.08670   0.08000   0.0229   0.0276   1.0000
  15.000   0.8859   0.09336   0.08687   0.0191   0.0277   1.0000
  15.250   0.8513   0.10384   0.09765   0.0124   0.0279   1.0000
<< Back to FX 71-L-150/25 AIRFOIL (fx711525-il)

Polar data table (+)

Polar graphs


<< Back to FX 71-L-150/25 AIRFOIL (fx711525-il)