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FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il)
Reynolds number: 50,000
Max Cl/Cd: 27.29 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx71l150-il-50000.txt
Download as CSV file: xf-fx71l150-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/30 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  -0.7301   0.09495   0.08752  -0.0225   1.0000   0.1163
 -11.750  -0.7469   0.08789   0.08044  -0.0256   1.0000   0.1147
 -11.500  -0.7809   0.08009   0.07256  -0.0295   1.0000   0.1126
 -11.250  -0.8224   0.07319   0.06550  -0.0323   1.0000   0.1104
 -11.000  -0.8623   0.06779   0.05986  -0.0329   1.0000   0.1086
 -10.750  -0.8975   0.06370   0.05547  -0.0309   1.0000   0.1073
 -10.500  -0.9167   0.05987   0.05128  -0.0290   1.0000   0.1066
 -10.250  -0.9192   0.05633   0.04744  -0.0277   1.0000   0.1068
 -10.000  -0.9102   0.05317   0.04412  -0.0268   1.0000   0.1084
  -9.750  -0.9010   0.05027   0.04101  -0.0257   1.0000   0.1110
  -9.500  -0.8930   0.04739   0.03779  -0.0244   1.0000   0.1140
  -9.250  -0.8825   0.04450   0.03453  -0.0231   1.0000   0.1180
  -9.000  -0.8576   0.04199   0.03209  -0.0230   1.0000   0.1251
  -8.750  -0.8347   0.03924   0.02920  -0.0224   1.0000   0.1337
  -8.500  -0.8089   0.03686   0.02685  -0.0220   1.0000   0.1475
  -8.250  -0.7908   0.03503   0.02528  -0.0211   1.0000   0.1687
  -8.000  -0.7804   0.03330   0.02358  -0.0194   1.0000   0.1944
  -7.750  -0.7650   0.03134   0.02205  -0.0179   1.0000   0.2292
  -7.500  -0.7522   0.02940   0.02071  -0.0157   1.0000   0.2735
  -7.250  -0.7489   0.02785   0.01982  -0.0122   1.0000   0.3297
  -7.000  -0.7490   0.02745   0.02013  -0.0072   1.0000   0.3957
  -6.750  -0.7437   0.02882   0.02194  -0.0013   1.0000   0.4564
  -6.500  -0.7344   0.03091   0.02410   0.0046   1.0000   0.4998
  -6.250  -0.6931   0.03548   0.02861   0.0094   1.0000   0.5351
  -6.000  -0.6855   0.03706   0.03009   0.0148   1.0000   0.5607
  -5.750  -0.6089   0.04272   0.03548   0.0175   1.0000   0.5873
  -5.500  -0.5863   0.04424   0.03685   0.0213   1.0000   0.6103
  -5.250  -0.5884   0.04432   0.03686   0.0261   1.0000   0.6308
  -5.000  -0.6021   0.04366   0.03618   0.0313   1.0000   0.6503
  -4.750  -0.5432   0.04559   0.03786   0.0314   1.0000   0.6734
  -4.500  -0.5532   0.04488   0.03709   0.0361   1.0000   0.6920
  -4.250  -0.5303   0.04490   0.03699   0.0378   1.0000   0.7114
  -4.000  -0.5290   0.04426   0.03628   0.0413   1.0000   0.7303
  -3.750  -0.5134   0.04381   0.03573   0.0431   1.0000   0.7484
  -3.500  -0.4888   0.04343   0.03523   0.0435   1.0000   0.7654
  -3.250  -0.4777   0.04273   0.03442   0.0451   1.0000   0.7809
  -3.000  -0.4637   0.04207   0.03367   0.0463   1.0000   0.7961
  -2.750  -0.4464   0.04150   0.03301   0.0469   1.0000   0.8115
  -2.500  -0.4287   0.04090   0.03232   0.0471   1.0000   0.8254
  -2.250  -0.4102   0.04029   0.03162   0.0470   0.9995   0.8381
  -2.000  -0.3573   0.04007   0.03124   0.0407   0.9923   0.8511
  -1.750  -0.3136   0.03980   0.03086   0.0360   0.9844   0.8646
  -1.500  -0.2525   0.03970   0.03063   0.0284   0.9770   0.8769
  -1.250  -0.1997   0.03944   0.03029   0.0219   0.9697   0.8870
  -1.000  -0.1797   0.03920   0.02999   0.0208   0.9631   0.8969
  -0.750  -0.1247   0.03900   0.02974   0.0140   0.9562   0.9056
  -0.500  -0.0939   0.03897   0.02966   0.0111   0.9491   0.9152
  -0.250  -0.0418   0.03883   0.02951   0.0047   0.9412   0.9242
   0.000  -0.0004   0.03895   0.02961   0.0001   0.9338   0.9338
   0.250   0.0415   0.03882   0.02951  -0.0047   0.9243   0.9412
   0.500   0.0936   0.03896   0.02966  -0.0110   0.9150   0.9492
   0.750   0.1254   0.03899   0.02973  -0.0141   0.9054   0.9563
   1.000   0.1797   0.03919   0.02998  -0.0208   0.8969   0.9631
   1.250   0.1999   0.03943   0.03028  -0.0220   0.8871   0.9697
   1.500   0.2527   0.03969   0.03063  -0.0284   0.8771   0.9770
   1.750   0.3124   0.03980   0.03086  -0.0358   0.8647   0.9843
   2.000   0.3575   0.04006   0.03123  -0.0407   0.8511   0.9923
   2.250   0.4105   0.04027   0.03159  -0.0471   0.8382   0.9996
   2.500   0.4287   0.04088   0.03230  -0.0471   0.8255   1.0000
   2.750   0.4469   0.04147   0.03298  -0.0469   0.8114   1.0000
   3.000   0.4638   0.04206   0.03365  -0.0463   0.7962   1.0000
   3.250   0.4778   0.04271   0.03440  -0.0451   0.7809   1.0000
   3.500   0.4896   0.04339   0.03518  -0.0435   0.7653   1.0000
   3.750   0.5116   0.04383   0.03575  -0.0429   0.7486   1.0000
   4.000   0.5292   0.04424   0.03626  -0.0413   0.7303   1.0000
   4.250   0.5295   0.04491   0.03700  -0.0377   0.7116   1.0000
   4.500   0.5538   0.04484   0.03707  -0.0361   0.6921   1.0000
   4.750   0.5433   0.04557   0.03783  -0.0314   0.6734   1.0000
   5.000   0.6006   0.04372   0.03622  -0.0312   0.6504   1.0000
   5.250   0.5885   0.04429   0.03683  -0.0260   0.6308   1.0000
   5.500   0.5865   0.04421   0.03683  -0.0213   0.6104   1.0000
   5.750   0.6082   0.04274   0.03549  -0.0174   0.5874   1.0000
   6.000   0.6837   0.03719   0.03022  -0.0148   0.5609   1.0000
   6.250   0.6931   0.03547   0.02859  -0.0094   0.5352   1.0000
   6.500   0.7343   0.03090   0.02409  -0.0046   0.4999   1.0000
   6.750   0.7437   0.02881   0.02193   0.0013   0.4565   1.0000
   7.000   0.7489   0.02744   0.02013   0.0072   0.3957   1.0000
   7.250   0.7489   0.02785   0.01981   0.0122   0.3297   1.0000
   7.500   0.7523   0.02940   0.02070   0.0157   0.2734   1.0000
   7.750   0.7652   0.03135   0.02205   0.0179   0.2292   1.0000
   8.000   0.7808   0.03329   0.02359   0.0194   0.1947   1.0000
   8.250   0.7911   0.03504   0.02528   0.0211   0.1687   1.0000
   8.500   0.8092   0.03687   0.02685   0.0220   0.1475   1.0000
   8.750   0.8349   0.03926   0.02920   0.0224   0.1334   1.0000
   9.000   0.8577   0.04200   0.03210   0.0229   0.1250   1.0000
   9.250   0.8826   0.04448   0.03451   0.0231   0.1180   1.0000
   9.500   0.8936   0.04740   0.03779   0.0243   0.1142   1.0000
   9.750   0.9013   0.05026   0.04100   0.0257   0.1110   1.0000
  10.000   0.9101   0.05318   0.04414   0.0267   0.1085   1.0000
  10.250   0.9194   0.05634   0.04746   0.0276   0.1068   1.0000
  10.500   0.9180   0.05989   0.05128   0.0289   0.1065   1.0000
  10.750   0.8958   0.06374   0.05554   0.0309   0.1075   1.0000
  11.000   0.8625   0.06781   0.05988   0.0328   0.1087   1.0000
  11.250   0.8232   0.07320   0.06550   0.0322   0.1105   1.0000
  11.500   0.7823   0.08007   0.07254   0.0294   0.1127   1.0000
  11.750   0.7482   0.08790   0.08045   0.0256   0.1148   1.0000
  12.000   0.7332   0.09470   0.08726   0.0226   0.1163   1.0000
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