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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 100,000
Max Cl/Cd: 41.39 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140sm-il-100000-n5.txt
Download as CSV file: xf-r140sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: R140  12.04% (smoothed)                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5719   0.09412   0.08915  -0.0337   1.0000   0.0178
 -11.000  -0.5833   0.08668   0.08171  -0.0382   1.0000   0.0175
 -10.750  -0.5983   0.08005   0.07506  -0.0423   1.0000   0.0174
 -10.500  -0.6136   0.07472   0.06967  -0.0453   1.0000   0.0172
 -10.250  -0.6315   0.06990   0.06477  -0.0471   1.0000   0.0170
 -10.000  -0.6493   0.06587   0.06063  -0.0475   1.0000   0.0169
  -9.750  -0.6673   0.06236   0.05700  -0.0464   1.0000   0.0169
  -9.500  -0.6849   0.05934   0.05384  -0.0437   1.0000   0.0169
  -9.250  -0.7012   0.05662   0.05097  -0.0399   1.0000   0.0167
  -9.000  -0.7126   0.05370   0.04785  -0.0365   1.0000   0.0167
  -8.750  -0.7211   0.05072   0.04462  -0.0328   1.0000   0.0167
  -8.500  -0.7263   0.04781   0.04145  -0.0292   1.0000   0.0167
  -8.250  -0.7289   0.04495   0.03826  -0.0254   1.0000   0.0169
  -8.000  -0.7280   0.04240   0.03534  -0.0217   1.0000   0.0176
  -7.750  -0.7235   0.04057   0.03309  -0.0181   1.0000   0.0184
  -7.500  -0.7214   0.03731   0.02952  -0.0147   1.0000   0.0192
  -7.250  -0.7139   0.03483   0.02679  -0.0119   1.0000   0.0200
  -7.000  -0.7025   0.03266   0.02435  -0.0093   1.0000   0.0205
  -6.750  -0.6887   0.03064   0.02200  -0.0069   1.0000   0.0211
  -6.500  -0.6731   0.02883   0.01998  -0.0047   1.0000   0.0220
  -6.250  -0.6565   0.02719   0.01817  -0.0027   1.0000   0.0230
  -6.000  -0.6406   0.02583   0.01664  -0.0005   1.0000   0.0248
  -5.750  -0.6257   0.02489   0.01554   0.0018   1.0000   0.0276
  -5.500  -0.6134   0.02362   0.01422   0.0044   1.0000   0.0297
  -5.250  -0.5838   0.02210   0.01265   0.0033   0.9935   0.0330
  -5.000  -0.5534   0.02095   0.01134   0.0023   0.9859   0.0377
  -4.750  -0.5243   0.01992   0.01019   0.0014   0.9774   0.0491
  -4.500  -0.4963   0.01874   0.00905   0.0008   0.9691   0.0739
  -4.250  -0.4727   0.01704   0.00805   0.0003   0.9603   0.1953
  -4.000  -0.4652   0.01497   0.00783   0.0035   0.9488   0.5402
  -3.750  -0.4387   0.01481   0.00780   0.0042   0.9401   0.6317
  -3.500  -0.4056   0.01473   0.00770   0.0036   0.9332   0.6771
  -3.250  -0.3761   0.01478   0.00772   0.0041   0.9244   0.7176
  -3.000  -0.3402   0.01483   0.00768   0.0031   0.9183   0.7437
  -2.750  -0.3092   0.01478   0.00749   0.0026   0.9084   0.7576
  -2.500  -0.2755   0.01468   0.00723   0.0014   0.8999   0.7684
  -2.250  -0.2416   0.01457   0.00695   0.0001   0.8916   0.7789
  -2.000  -0.2090   0.01452   0.00680  -0.0008   0.8817   0.7880
  -1.750  -0.1757   0.01445   0.00662  -0.0019   0.8727   0.7978
  -1.500  -0.1433   0.01438   0.00644  -0.0028   0.8637   0.8083
  -1.250  -0.1120   0.01435   0.00632  -0.0035   0.8533   0.8181
  -1.000  -0.0787   0.01432   0.00623  -0.0046   0.8439   0.8273
  -0.750  -0.0456   0.01428   0.00611  -0.0056   0.8354   0.8373
  -0.500  -0.0158   0.01427   0.00606  -0.0060   0.8249   0.8479
  -0.250   0.0192   0.01430   0.00605  -0.0075   0.8159   0.8559
   0.000   0.0531   0.01429   0.00600  -0.0087   0.8079   0.8653
   0.250   0.0836   0.01433   0.00602  -0.0093   0.7978   0.8756
   0.500   0.1205   0.01439   0.00608  -0.0111   0.7894   0.8828
   0.750   0.1537   0.01443   0.00611  -0.0123   0.7813   0.8922
   1.000   0.1885   0.01451   0.00622  -0.0138   0.7724   0.9003
   1.250   0.2244   0.01458   0.00632  -0.0155   0.7650   0.9080
   1.500   0.2557   0.01467   0.00645  -0.0164   0.7563   0.9179
   1.750   0.2952   0.01477   0.00661  -0.0189   0.7486   0.9233
   2.000   0.3283   0.01487   0.00680  -0.0202   0.7410   0.9322
   2.250   0.3674   0.01498   0.00702  -0.0227   0.7330   0.9377
   2.500   0.4007   0.01509   0.00720  -0.0240   0.7259   0.9461
   2.750   0.4384   0.01521   0.00748  -0.0264   0.7177   0.9521
   3.000   0.4719   0.01532   0.00774  -0.0277   0.7109   0.9599
   3.250   0.5084   0.01540   0.00801  -0.0297   0.6999   0.9661
   3.500   0.5399   0.01539   0.00810  -0.0304   0.6810   0.9738
   3.750   0.5734   0.01530   0.00809  -0.0313   0.6553   0.9804
   4.000   0.6041   0.01520   0.00807  -0.0316   0.6164   0.9878
   4.250   0.6292   0.01520   0.00777  -0.0307   0.5014   0.9964
   4.500   0.6316   0.01684   0.00797  -0.0267   0.2390   1.0000
   4.750   0.6282   0.01877   0.00891  -0.0222   0.0805   1.0000
   5.000   0.6362   0.01973   0.00972  -0.0188   0.0476   1.0000
   5.250   0.6457   0.02054   0.01056  -0.0156   0.0391   1.0000
   5.500   0.6552   0.02132   0.01144  -0.0124   0.0347   1.0000
   5.750   0.6624   0.02227   0.01244  -0.0089   0.0309   1.0000
   6.000   0.6726   0.02304   0.01334  -0.0059   0.0272   1.0000
   6.250   0.6815   0.02401   0.01439  -0.0027   0.0254   1.0000
   6.500   0.6914   0.02514   0.01558   0.0003   0.0240   1.0000
   6.750   0.7038   0.02650   0.01698   0.0029   0.0229   1.0000
   7.000   0.7214   0.02862   0.01921   0.0045   0.0217   1.0000
   7.250   0.7421   0.03056   0.02132   0.0058   0.0206   1.0000
   7.500   0.7608   0.03204   0.02306   0.0074   0.0191   1.0000
   7.750   0.7783   0.03395   0.02525   0.0092   0.0177   1.0000
   8.000   0.7937   0.03631   0.02793   0.0112   0.0173   1.0000
   8.250   0.8053   0.03886   0.03084   0.0137   0.0171   1.0000
   8.500   0.8129   0.04155   0.03390   0.0166   0.0169   1.0000
   8.750   0.8168   0.04433   0.03702   0.0198   0.0168   1.0000
   9.000   0.8166   0.04727   0.04031   0.0232   0.0168   1.0000
   9.250   0.8127   0.05023   0.04358   0.0268   0.0168   1.0000
   9.500   0.8059   0.05312   0.04674   0.0303   0.0170   1.0000
   9.750   0.7941   0.05587   0.04971   0.0342   0.0171   1.0000
  10.000   0.7782   0.05873   0.05277   0.0379   0.0171   1.0000
  10.250   0.7636   0.06167   0.05588   0.0403   0.0173   1.0000
  10.500   0.7441   0.06540   0.05978   0.0418   0.0173   1.0000
  10.750   0.7265   0.06930   0.06384   0.0420   0.0175   1.0000
  11.000   0.7088   0.07368   0.06835   0.0410   0.0177   1.0000
  11.250   0.6894   0.07898   0.07375   0.0388   0.0178   1.0000
  11.500   0.6704   0.08508   0.07994   0.0355   0.0180   1.0000
  11.750   0.6530   0.09211   0.08702   0.0312   0.0182   1.0000
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