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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 50,000
Max Cl/Cd: 29.37 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140sm-il-50000-n5.txt
Download as CSV file: xf-r140sm-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5691   0.09886   0.09191  -0.0336   1.0000   0.0372
 -10.750  -0.5782   0.09265   0.08574  -0.0372   1.0000   0.0367
 -10.500  -0.5906   0.08686   0.07996  -0.0406   1.0000   0.0362
 -10.250  -0.6064   0.08150   0.07459  -0.0434   1.0000   0.0357
 -10.000  -0.6243   0.07682   0.06986  -0.0450   1.0000   0.0353
  -9.750  -0.6430   0.07282   0.06578  -0.0451   1.0000   0.0351
  -9.500  -0.6614   0.06941   0.06228  -0.0437   1.0000   0.0348
  -9.250  -0.6789   0.06637   0.05912  -0.0410   1.0000   0.0346
  -9.000  -0.6914   0.06323   0.05581  -0.0383   1.0000   0.0344
  -8.750  -0.7009   0.06005   0.05241  -0.0355   1.0000   0.0342
  -8.500  -0.7071   0.05693   0.04904  -0.0325   1.0000   0.0341
  -8.250  -0.7104   0.05381   0.04562  -0.0294   1.0000   0.0341
  -8.000  -0.7108   0.05077   0.04225  -0.0262   1.0000   0.0343
  -7.750  -0.7078   0.04791   0.03904  -0.0231   1.0000   0.0349
  -7.500  -0.7019   0.04531   0.03605  -0.0202   1.0000   0.0364
  -7.250  -0.6935   0.04285   0.03301  -0.0172   1.0000   0.0386
  -7.000  -0.6813   0.04065   0.03028  -0.0144   1.0000   0.0402
  -6.750  -0.6629   0.03764   0.02709  -0.0131   1.0000   0.0417
  -6.500  -0.6408   0.03525   0.02453  -0.0120   1.0000   0.0436
  -6.250  -0.6147   0.03319   0.02227  -0.0112   1.0000   0.0463
  -6.000  -0.5884   0.03155   0.02035  -0.0102   1.0000   0.0515
  -5.750  -0.5704   0.03011   0.01893  -0.0085   1.0000   0.0589
  -5.500  -0.5543   0.02891   0.01750  -0.0061   1.0000   0.0653
  -5.250  -0.5457   0.02758   0.01619  -0.0030   1.0000   0.0722
  -5.000  -0.5386   0.02640   0.01500   0.0004   1.0000   0.0845
  -4.750  -0.5332   0.02512   0.01380   0.0038   1.0000   0.1099
  -4.500  -0.5308   0.02338   0.01254   0.0074   1.0000   0.1706
  -4.250  -0.5428   0.02081   0.01203   0.0135   1.0000   0.4619
  -4.000  -0.5432   0.02072   0.01250   0.0203   1.0000   0.6309
  -3.750  -0.5321   0.02112   0.01301   0.0255   1.0000   0.7056
  -3.500  -0.5141   0.02223   0.01413   0.0306   1.0000   0.7730
  -3.250  -0.4878   0.02319   0.01486   0.0334   1.0000   0.8146
  -3.000  -0.4447   0.02339   0.01466   0.0303   0.9926   0.8311
  -2.750  -0.3990   0.02345   0.01428   0.0262   0.9846   0.8418
  -2.500  -0.3562   0.02344   0.01395   0.0225   0.9756   0.8526
  -2.250  -0.3142   0.02344   0.01367   0.0190   0.9666   0.8637
  -2.000  -0.2650   0.02351   0.01343   0.0142   0.9596   0.8727
  -1.750  -0.2206   0.02352   0.01324   0.0103   0.9507   0.8819
  -1.500  -0.1756   0.02352   0.01305   0.0061   0.9428   0.8918
  -1.250  -0.1266   0.02354   0.01288   0.0013   0.9351   0.8998
  -1.000  -0.0789   0.02353   0.01274  -0.0034   0.9274   0.9080
  -0.750  -0.0320   0.02349   0.01260  -0.0079   0.9198   0.9170
  -0.500   0.0170   0.02345   0.01248  -0.0128   0.9119   0.9242
  -0.250   0.0645   0.02337   0.01236  -0.0174   0.9049   0.9329
   0.000   0.1089   0.02331   0.01228  -0.0215   0.8957   0.9413
   0.250   0.1555   0.02320   0.01220  -0.0260   0.8881   0.9494
   0.500   0.1970   0.02314   0.01217  -0.0295   0.8791   0.9592
   0.750   0.2420   0.02303   0.01212  -0.0337   0.8702   0.9672
   1.000   0.2878   0.02289   0.01209  -0.0380   0.8629   0.9754
   1.250   0.3277   0.02284   0.01215  -0.0413   0.8529   0.9850
   1.500   0.3713   0.02273   0.01217  -0.0453   0.8442   0.9935
   1.750   0.4124   0.02260   0.01223  -0.0488   0.8361   1.0000
   2.000   0.4291   0.02275   0.01248  -0.0476   0.8246   1.0000
   2.250   0.4466   0.02292   0.01276  -0.0464   0.8139   1.0000
   2.500   0.4671   0.02306   0.01304  -0.0457   0.8045   1.0000
   2.750   0.4878   0.02322   0.01334  -0.0449   0.7951   1.0000
   3.000   0.5031   0.02353   0.01387  -0.0432   0.7845   1.0000
   3.250   0.5207   0.02381   0.01433  -0.0418   0.7747   1.0000
   3.500   0.5445   0.02397   0.01470  -0.0412   0.7665   1.0000
   3.750   0.5591   0.02433   0.01527  -0.0392   0.7550   1.0000
   4.000   0.5773   0.02453   0.01571  -0.0373   0.7422   1.0000
   4.250   0.6023   0.02429   0.01572  -0.0357   0.7256   1.0000
   4.500   0.6245   0.02367   0.01541  -0.0326   0.6977   1.0000
   4.750   0.6384   0.02275   0.01460  -0.0273   0.6503   1.0000
   5.000   0.6380   0.02172   0.01321  -0.0187   0.5452   1.0000
   5.250   0.6299   0.02236   0.01255  -0.0109   0.3042   1.0000
   5.500   0.6155   0.02507   0.01386  -0.0051   0.1296   1.0000
   5.750   0.6128   0.02706   0.01544  -0.0007   0.0899   1.0000
   6.000   0.6154   0.02857   0.01686   0.0031   0.0714   1.0000
   6.250   0.6209   0.02985   0.01816   0.0064   0.0600   1.0000
   6.500   0.6267   0.03123   0.01956   0.0098   0.0547   1.0000
   6.750   0.6387   0.03253   0.02105   0.0125   0.0507   1.0000
   7.000   0.6589   0.03406   0.02271   0.0142   0.0466   1.0000
   7.250   0.6914   0.03609   0.02489   0.0141   0.0425   1.0000
   7.500   0.7204   0.03792   0.02707   0.0145   0.0377   1.0000
   7.750   0.7473   0.04029   0.02970   0.0150   0.0352   1.0000
   8.000   0.7691   0.04296   0.03265   0.0160   0.0341   1.0000
   8.250   0.7856   0.04582   0.03581   0.0175   0.0334   1.0000
   8.500   0.7972   0.04887   0.03917   0.0194   0.0329   1.0000
   8.750   0.8044   0.05201   0.04264   0.0217   0.0326   1.0000
   9.000   0.8074   0.05531   0.04625   0.0243   0.0324   1.0000
   9.250   0.8069   0.05860   0.04982   0.0268   0.0321   1.0000
   9.500   0.8032   0.06178   0.05327   0.0295   0.0320   1.0000
   9.750   0.7947   0.06497   0.05665   0.0323   0.0318   1.0000
  10.000   0.7801   0.06762   0.05955   0.0356   0.0316   1.0000
  10.250   0.7696   0.07077   0.06283   0.0379   0.0318   1.0000
  10.500   0.7499   0.07383   0.06609   0.0399   0.0316   1.0000
  10.750   0.7326   0.07736   0.06976   0.0406   0.0316   1.0000
  11.000   0.7193   0.08140   0.07390   0.0403   0.0318   1.0000
  11.250   0.7032   0.08589   0.07848   0.0392   0.0319   1.0000
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