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Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il)
Reynolds number: 100,000
Max Cl/Cd: 33.35 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-atr72sm-il-100000.txt
Download as CSV file: xf-atr72sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Smoothed ATR airfoil coordinates obtained  using
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3407   0.09821   0.09327  -0.0281   1.0000   0.1446
  -9.250  -0.3630   0.09479   0.08996  -0.0317   1.0000   0.1511
  -9.000  -0.4126   0.08919   0.08454  -0.0380   1.0000   0.1536
  -8.750  -0.3520   0.08818   0.08346  -0.0302   1.0000   0.1587
  -8.500  -0.3582   0.08526   0.08061  -0.0306   1.0000   0.1644
  -8.250  -0.4130   0.08101   0.07654  -0.0344   1.0000   0.1677
  -8.000  -0.4766   0.07916   0.07477  -0.0310   1.0000   0.1686
  -7.750  -0.5383   0.07835   0.07382  -0.0263   1.0000   0.1693
  -7.500  -0.4415   0.07369   0.06948  -0.0257   1.0000   0.1769
  -7.250  -0.6118   0.05412   0.04843  -0.0215   1.0000   0.0940
  -7.000  -0.6100   0.05109   0.04536  -0.0190   1.0000   0.0932
  -6.750  -0.6108   0.04818   0.04229  -0.0161   1.0000   0.0924
  -6.500  -0.6108   0.04523   0.03912  -0.0132   1.0000   0.0914
  -6.250  -0.6094   0.04221   0.03580  -0.0103   1.0000   0.0903
  -6.000  -0.6050   0.03940   0.03265  -0.0076   1.0000   0.0894
  -5.750  -0.5761   0.03609   0.02880  -0.0090   0.9940   0.0902
  -5.500  -0.5289   0.03337   0.02526  -0.0129   0.9824   0.0943
  -5.250  -0.4834   0.03102   0.02290  -0.0168   0.9715   0.0990
  -5.000  -0.4403   0.02953   0.02104  -0.0196   0.9604   0.1059
  -4.750  -0.3960   0.02786   0.01928  -0.0228   0.9505   0.1130
  -4.500  -0.3471   0.02652   0.01771  -0.0263   0.9409   0.1232
  -4.250  -0.3059   0.02546   0.01668  -0.0287   0.9289   0.1335
  -4.000  -0.2591   0.02418   0.01544  -0.0318   0.9185   0.1453
  -3.750  -0.2063   0.02289   0.01420  -0.0359   0.9096   0.1604
  -3.500  -0.1655   0.02180   0.01320  -0.0377   0.8967   0.1765
  -3.250  -0.1248   0.02066   0.01221  -0.0393   0.8841   0.1989
  -3.000  -0.0862   0.01932   0.01114  -0.0404   0.8718   0.2338
  -2.750  -0.0603   0.01777   0.01020  -0.0393   0.8564   0.3081
  -2.500  -0.0510   0.01592   0.01006  -0.0342   0.8392   0.6297
  -2.250  -0.0199   0.01568   0.01017  -0.0314   0.8201   0.7710
  -2.000   0.0178   0.01587   0.01034  -0.0300   0.7961   0.8311
  -1.750   0.0588   0.01612   0.01037  -0.0292   0.7700   0.8704
  -1.500   0.1196   0.01663   0.01055  -0.0321   0.7273   0.8974
  -1.250   0.1767   0.01706   0.01052  -0.0352   0.6729   0.9221
  -1.000   0.2473   0.01760   0.01043  -0.0415   0.6103   0.9436
  -0.750   0.3120   0.01797   0.01023  -0.0478   0.5618   0.9672
  -0.500   0.3837   0.01785   0.00964  -0.0562   0.5243   0.9878
  -0.250   0.4344   0.01762   0.00913  -0.0612   0.5003   1.0000
   0.000   0.4520   0.01770   0.00902  -0.0601   0.4869   1.0000
   0.250   0.4699   0.01780   0.00892  -0.0589   0.4751   1.0000
   0.500   0.4881   0.01791   0.00892  -0.0577   0.4636   1.0000
   0.750   0.5067   0.01809   0.00893  -0.0566   0.4544   1.0000
   1.000   0.5256   0.01826   0.00900  -0.0555   0.4454   1.0000
   1.250   0.5451   0.01850   0.00908  -0.0544   0.4381   1.0000
   1.500   0.5642   0.01872   0.00926  -0.0532   0.4301   1.0000
   1.750   0.5847   0.01902   0.00936  -0.0522   0.4237   1.0000
   2.000   0.6037   0.01929   0.00966  -0.0510   0.4165   1.0000
   2.250   0.6238   0.01961   0.00989  -0.0498   0.4101   1.0000
   2.500   0.6450   0.02006   0.01018  -0.0489   0.4051   1.0000
   2.750   0.6638   0.02045   0.01064  -0.0476   0.3993   1.0000
   3.000   0.6838   0.02086   0.01102  -0.0464   0.3939   1.0000
   3.250   0.7057   0.02137   0.01137  -0.0454   0.3891   1.0000
   3.500   0.7240   0.02187   0.01195  -0.0440   0.3839   1.0000
   3.750   0.7431   0.02237   0.01250  -0.0427   0.3789   1.0000
   4.000   0.7637   0.02290   0.01298  -0.0415   0.3746   1.0000
   4.250   0.7860   0.02362   0.01356  -0.0407   0.3710   1.0000
   4.500   0.8020   0.02424   0.01438  -0.0389   0.3666   1.0000
   4.750   0.8201   0.02487   0.01508  -0.0374   0.3620   1.0000
   5.000   0.8400   0.02547   0.01565  -0.0361   0.3577   1.0000
   5.250   0.8620   0.02621   0.01630  -0.0352   0.3542   1.0000
   5.500   0.8767   0.02711   0.01736  -0.0333   0.3507   1.0000
   5.750   0.8914   0.02799   0.01840  -0.0314   0.3468   1.0000
   6.000   0.9090   0.02877   0.01924  -0.0299   0.3429   1.0000
   6.250   0.9295   0.02946   0.01990  -0.0288   0.3393   1.0000
   6.500   0.9520   0.03044   0.02077  -0.0281   0.3361   1.0000
   6.750   0.9587   0.03163   0.02228  -0.0252   0.3325   1.0000
   7.000   0.9691   0.03288   0.02371  -0.0229   0.3290   1.0000
   7.250   0.9838   0.03393   0.02485  -0.0212   0.3255   1.0000
   7.500   1.0051   0.03469   0.02559  -0.0203   0.3223   1.0000
   7.750   1.0296   0.03565   0.02644  -0.0199   0.3192   1.0000
   8.000   1.0257   0.03758   0.02872  -0.0161   0.3157   1.0000
   8.250   1.0240   0.03966   0.03106  -0.0129   0.3123   1.0000
   8.500   1.0282   0.04146   0.03303  -0.0105   0.3091   1.0000
   8.750   1.0462   0.04246   0.03404  -0.0094   0.3059   1.0000
   9.000   1.0814   0.04276   0.03420  -0.0101   0.3030   1.0000
   9.250   1.0659   0.04584   0.03756  -0.0061   0.2999   1.0000
   9.500   0.9930   0.05225   0.04440   0.0015   0.2970   1.0000
   9.750   0.6981   0.08915   0.08155  -0.0044   0.3013   1.0000
  10.000   0.7002   0.09372   0.08615  -0.0053   0.3017   1.0000
  10.250   0.5888   0.11313   0.10566  -0.0162   0.3383   1.0000
  10.500   1.0529   0.05787   0.05011   0.0053   0.2851   1.0000
  10.750   0.5802   0.11896   0.11151  -0.0174   0.3241   1.0000
  11.000   0.6067   0.12142   0.11399  -0.0171   0.3210   1.0000
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