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FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il)
Reynolds number: 50,000
Max Cl/Cd: 27.36 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx711525-il-50000.txt
Download as CSV file: xf-fx711525-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6748   0.10616   0.09880  -0.0140   1.0000   0.1242
 -11.750  -0.6784   0.09969   0.09235  -0.0165   1.0000   0.1219
 -11.500  -0.8141   0.08008   0.07248  -0.0311   1.0000   0.1123
 -11.250  -0.8303   0.07498   0.06729  -0.0322   1.0000   0.1114
 -11.000  -0.8510   0.07031   0.06249  -0.0326   1.0000   0.1104
 -10.750  -0.8726   0.06624   0.05825  -0.0317   1.0000   0.1095
 -10.500  -0.8898   0.06245   0.05422  -0.0302   1.0000   0.1087
 -10.250  -0.8989   0.05866   0.05014  -0.0288   1.0000   0.1084
 -10.000  -0.9012   0.05509   0.04626  -0.0275   1.0000   0.1083
  -9.750  -0.8984   0.05169   0.04250  -0.0262   1.0000   0.1090
  -9.500  -0.8906   0.04848   0.03892  -0.0249   1.0000   0.1103
  -9.250  -0.8801   0.04551   0.03547  -0.0236   1.0000   0.1122
  -9.000  -0.8540   0.04261   0.03261  -0.0237   1.0000   0.1169
  -8.750  -0.8341   0.04024   0.02998  -0.0229   1.0000   0.1238
  -8.500  -0.8069   0.03788   0.02773  -0.0229   1.0000   0.1350
  -8.250  -0.7823   0.03566   0.02550  -0.0223   1.0000   0.1516
  -8.000  -0.7637   0.03378   0.02405  -0.0215   1.0000   0.1769
  -7.750  -0.7510   0.03198   0.02258  -0.0199   1.0000   0.2080
  -7.500  -0.7408   0.03005   0.02104  -0.0177   1.0000   0.2487
  -7.250  -0.7375   0.02828   0.01992  -0.0144   1.0000   0.2992
  -7.000  -0.7436   0.02717   0.01951  -0.0092   1.0000   0.3588
  -6.750  -0.7475   0.02747   0.02047  -0.0029   1.0000   0.4273
  -6.500  -0.7385   0.02966   0.02292   0.0035   1.0000   0.4882
  -6.250  -0.7229   0.03223   0.02545   0.0092   1.0000   0.5299
  -6.000  -0.6745   0.03723   0.03031   0.0140   1.0000   0.5628
  -5.750  -0.6746   0.03796   0.03092   0.0193   1.0000   0.5883
  -5.500  -0.5812   0.04412   0.03674   0.0208   1.0000   0.6160
  -5.250  -0.5619   0.04510   0.03757   0.0243   1.0000   0.6393
  -5.000  -0.5514   0.04544   0.03781   0.0279   1.0000   0.6609
  -4.750  -0.5420   0.04553   0.03779   0.0313   1.0000   0.6817
  -4.500  -0.5306   0.04548   0.03764   0.0342   1.0000   0.7017
  -4.250  -0.5202   0.04523   0.03730   0.0370   1.0000   0.7213
  -4.000  -0.5100   0.04484   0.03680   0.0396   1.0000   0.7400
  -3.750  -0.5049   0.04425   0.03613   0.0425   1.0000   0.7578
  -3.500  -0.4800   0.04383   0.03559   0.0428   1.0000   0.7752
  -3.250  -0.4700   0.04311   0.03478   0.0446   1.0000   0.7910
  -3.000  -0.4646   0.04236   0.03395   0.0469   1.0000   0.8063
  -2.750  -0.4211   0.04200   0.03343   0.0437   1.0000   0.8222
  -2.500  -0.3869   0.04148   0.03280   0.0415   1.0000   0.8358
  -2.250  -0.3826   0.04070   0.03197   0.0434   1.0000   0.8478
  -2.000  -0.3786   0.04002   0.03122   0.0454   1.0000   0.8600
  -1.750  -0.3038   0.03998   0.03102   0.0356   0.9932   0.8729
  -1.500  -0.2696   0.03960   0.03056   0.0320   0.9856   0.8844
  -1.250  -0.2116   0.03943   0.03028   0.0246   0.9785   0.8951
  -1.000  -0.1732   0.03917   0.02995   0.0203   0.9708   0.9045
  -0.750  -0.1271   0.03901   0.02974   0.0148   0.9637   0.9142
  -0.500  -0.0865   0.03889   0.02958   0.0102   0.9562   0.9231
  -0.250  -0.0419   0.03882   0.02949   0.0049   0.9486   0.9324
   0.000  -0.0002   0.03880   0.02945   0.0000   0.9405   0.9404
   0.250   0.0420   0.03882   0.02948  -0.0049   0.9324   0.9486
   0.500   0.0868   0.03888   0.02957  -0.0102   0.9232   0.9563
   0.750   0.1269   0.03901   0.02973  -0.0148   0.9143   0.9637
   1.000   0.1732   0.03917   0.02995  -0.0203   0.9045   0.9709
   1.250   0.2116   0.03942   0.03027  -0.0246   0.8952   0.9785
   1.500   0.2691   0.03959   0.03054  -0.0320   0.8844   0.9856
   1.750   0.3036   0.03997   0.03101  -0.0355   0.8728   0.9931
   2.000   0.3792   0.04000   0.03120  -0.0455   0.8602   1.0000
   2.250   0.3823   0.04069   0.03196  -0.0434   0.8479   1.0000
   2.500   0.3868   0.04146   0.03279  -0.0415   0.8359   1.0000
   2.750   0.4213   0.04198   0.03342  -0.0438   0.8222   1.0000
   3.000   0.4650   0.04233   0.03393  -0.0470   0.8063   1.0000
   3.250   0.4690   0.04310   0.03477  -0.0445   0.7911   1.0000
   3.500   0.4781   0.04384   0.03559  -0.0426   0.7754   1.0000
   3.750   0.5054   0.04423   0.03611  -0.0426   0.7578   1.0000
   4.000   0.5113   0.04481   0.03677  -0.0397   0.7401   1.0000
   4.250   0.5206   0.04521   0.03728  -0.0370   0.7213   1.0000
   4.500   0.5310   0.04544   0.03761  -0.0343   0.7018   1.0000
   4.750   0.5425   0.04551   0.03778  -0.0313   0.6818   1.0000
   5.000   0.5519   0.04542   0.03778  -0.0279   0.6610   1.0000
   5.250   0.5620   0.04509   0.03755  -0.0243   0.6394   1.0000
   5.500   0.5808   0.04413   0.03675  -0.0208   0.6161   1.0000
   5.750   0.6734   0.03805   0.03101  -0.0193   0.5884   1.0000
   6.000   0.6744   0.03723   0.03030  -0.0140   0.5628   1.0000
   6.250   0.7228   0.03223   0.02544  -0.0092   0.5299   1.0000
   6.500   0.7384   0.02966   0.02292  -0.0035   0.4883   1.0000
   6.750   0.7474   0.02747   0.02047   0.0029   0.4275   1.0000
   7.000   0.7434   0.02717   0.01950   0.0093   0.3586   1.0000
   7.250   0.7373   0.02828   0.01991   0.0144   0.2991   1.0000
   7.500   0.7409   0.03005   0.02103   0.0177   0.2487   1.0000
   7.750   0.7512   0.03198   0.02258   0.0199   0.2080   1.0000
   8.000   0.7634   0.03379   0.02406   0.0215   0.1765   1.0000
   8.250   0.7825   0.03566   0.02550   0.0223   0.1516   1.0000
   8.500   0.8071   0.03788   0.02772   0.0228   0.1351   1.0000
   8.750   0.8343   0.04026   0.03000   0.0229   0.1237   1.0000
   9.000   0.8542   0.04261   0.03261   0.0236   0.1168   1.0000
   9.250   0.8803   0.04551   0.03547   0.0236   0.1122   1.0000
   9.500   0.8907   0.04848   0.03891   0.0249   0.1103   1.0000
   9.750   0.8984   0.05170   0.04251   0.0261   0.1090   1.0000
  10.000   0.9016   0.05508   0.04624   0.0274   0.1084   1.0000
  10.250   0.8989   0.05869   0.05017   0.0288   0.1083   1.0000
  10.500   0.8904   0.06244   0.05421   0.0301   0.1088   1.0000
  10.750   0.8725   0.06628   0.05828   0.0317   0.1094   1.0000
  11.000   0.8522   0.07029   0.06247   0.0325   0.1104   1.0000
  11.250   0.8301   0.07503   0.06735   0.0321   0.1113   1.0000
  11.500   0.8155   0.08008   0.07248   0.0310   0.1123   1.0000
  11.750   0.6795   0.09966   0.09231   0.0165   0.1220   1.0000
  12.000   0.6766   0.10600   0.09864   0.0141   0.1242   1.0000
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