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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 200,000
Max Cl/Cd: 53.48 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-r140sm-il-200000.txt
Download as CSV file: xf-r140sm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4422   0.10589   0.10255  -0.0286   1.0000   0.0505
 -11.250  -0.4515   0.10037   0.09705  -0.0316   1.0000   0.0520
 -11.000  -0.5535   0.10125   0.09772  -0.0295   1.0000   0.0465
 -10.750  -0.5580   0.09616   0.09267  -0.0320   1.0000   0.0475
 -10.500  -0.5665   0.09000   0.08655  -0.0359   1.0000   0.0486
 -10.250  -0.5815   0.08267   0.07924  -0.0417   1.0000   0.0485
  -8.000  -0.7344   0.05164   0.04707  -0.0248   1.0000   0.0563
  -7.750  -0.7299   0.04891   0.04433  -0.0223   1.0000   0.0579
  -7.500  -0.7284   0.04670   0.04203  -0.0189   1.0000   0.0600
  -7.250  -0.7294   0.04485   0.03996  -0.0147   1.0000   0.0634
  -7.000  -0.7404   0.04285   0.03755  -0.0089   1.0000   0.0690
  -6.750  -0.7333   0.04014   0.03483  -0.0063   1.0000   0.0710
  -6.500  -0.7160   0.03111   0.02448   0.0013   1.0000   0.0288
  -6.250  -0.7056   0.02840   0.02147   0.0044   1.0000   0.0278
  -6.000  -0.6931   0.02694   0.01973   0.0073   1.0000   0.0290
  -5.750  -0.6794   0.02571   0.01826   0.0099   1.0000   0.0296
  -5.500  -0.6475   0.02343   0.01566   0.0093   0.9975   0.0299
  -5.250  -0.6090   0.02133   0.01338   0.0073   0.9942   0.0306
  -5.000  -0.5772   0.01892   0.01095   0.0062   0.9895   0.0329
  -4.750  -0.5392   0.01795   0.00996   0.0036   0.9841   0.0393
  -4.500  -0.5084   0.01656   0.00853   0.0026   0.9764   0.0452
  -4.250  -0.4740   0.01525   0.00725   0.0008   0.9702   0.0722
  -4.000  -0.4697   0.01204   0.00608   0.0036   0.9582   0.4594
  -3.750  -0.4446   0.01155   0.00608   0.0043   0.9492   0.6071
  -3.500  -0.4104   0.01139   0.00607   0.0035   0.9433   0.6768
  -3.250  -0.3766   0.01130   0.00602   0.0028   0.9361   0.7119
  -3.000  -0.3383   0.01122   0.00589   0.0010   0.9304   0.7365
  -2.750  -0.3043   0.01123   0.00589   0.0002   0.9232   0.7623
  -2.500  -0.2687   0.01123   0.00586  -0.0008   0.9162   0.7814
  -2.250  -0.2359   0.01117   0.00572  -0.0016   0.9075   0.7946
  -2.000  -0.2000   0.01106   0.00553  -0.0031   0.9004   0.8054
  -1.750  -0.1721   0.01097   0.00537  -0.0030   0.8894   0.8161
  -1.500  -0.1402   0.01091   0.00526  -0.0037   0.8798   0.8250
  -1.250  -0.1073   0.01082   0.00510  -0.0045   0.8716   0.8342
  -1.000  -0.0810   0.01078   0.00501  -0.0041   0.8601   0.8449
  -0.750  -0.0517   0.01077   0.00497  -0.0042   0.8497   0.8545
  -0.500  -0.0201   0.01076   0.00493  -0.0049   0.8406   0.8635
  -0.250   0.0093   0.01076   0.00487  -0.0051   0.8311   0.8738
   0.000   0.0388   0.01081   0.00491  -0.0053   0.8210   0.8839
   0.250   0.0743   0.01089   0.00496  -0.0068   0.8125   0.8913
   0.500   0.1056   0.01096   0.00500  -0.0074   0.8036   0.9011
   0.750   0.1433   0.01110   0.00515  -0.0095   0.7948   0.9075
   1.000   0.1785   0.01121   0.00522  -0.0110   0.7873   0.9157
   1.250   0.2183   0.01137   0.00542  -0.0135   0.7782   0.9213
   1.500   0.2540   0.01150   0.00556  -0.0152   0.7706   0.9292
   1.750   0.2985   0.01166   0.00574  -0.0188   0.7626   0.9329
   2.000   0.3320   0.01181   0.00593  -0.0202   0.7546   0.9418
   2.250   0.3771   0.01194   0.00612  -0.0239   0.7475   0.9452
   2.500   0.4151   0.01208   0.00634  -0.0263   0.7381   0.9522
   2.750   0.4530   0.01211   0.00640  -0.0283   0.7238   0.9585
   3.000   0.4911   0.01210   0.00643  -0.0303   0.7064   0.9650
   3.250   0.5282   0.01211   0.00647  -0.0322   0.6901   0.9718
   3.500   0.5641   0.01197   0.00635  -0.0337   0.6581   0.9790
   3.750   0.5987   0.01180   0.00615  -0.0348   0.6107   0.9861
   4.000   0.6316   0.01181   0.00595  -0.0358   0.5232   0.9937
   4.250   0.6317   0.01491   0.00673  -0.0326   0.0823   1.0000
   4.500   0.6387   0.01599   0.00761  -0.0290   0.0450   1.0000
   4.750   0.6510   0.01650   0.00819  -0.0264   0.0376   1.0000
   5.000   0.6576   0.01744   0.00918  -0.0227   0.0342   1.0000
   5.250   0.6656   0.01829   0.01009  -0.0192   0.0326   1.0000
   5.500   0.6746   0.01916   0.01103  -0.0158   0.0314   1.0000
   5.750   0.6854   0.02010   0.01205  -0.0126   0.0301   1.0000
   6.000   0.6983   0.02106   0.01306  -0.0099   0.0285   1.0000
   6.250   0.7121   0.02205   0.01406  -0.0075   0.0261   1.0000
   6.500   0.7308   0.02360   0.01569  -0.0057   0.0258   1.0000
   6.750   0.7525   0.02555   0.01781  -0.0042   0.0257   1.0000
   7.000   0.7762   0.02829   0.02093  -0.0025   0.0276   1.0000
   7.250   0.7944   0.03199   0.02504  -0.0002   0.0310   1.0000
  11.750   0.5529   0.09555   0.09220   0.0363   0.0568   1.0000
  12.000   0.5303   0.10329   0.09995   0.0314   0.0568   1.0000
  12.250   0.5187   0.10993   0.10658   0.0278   0.0568   1.0000
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