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R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: R140 12.04% (smoothed) (r140sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 59.85 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140sm-il-1000000-n5.txt
Download as CSV file: xf-r140sm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8353   0.07414   0.07249  -0.0344   1.0000   0.0016
 -13.750  -0.8753   0.06212   0.06028  -0.0422   1.0000   0.0016
 -13.500  -0.8983   0.05520   0.05319  -0.0459   1.0000   0.0016
 -13.250  -0.9206   0.04925   0.04705  -0.0481   1.0000   0.0016
 -13.000  -0.9119   0.04780   0.04556  -0.0485   1.0000   0.0015
 -12.750  -0.9786   0.03792   0.03515  -0.0477   1.0000   0.0016
 -12.500  -0.9829   0.03557   0.03264  -0.0462   1.0000   0.0016
 -12.250  -0.9975   0.03242   0.02923  -0.0434   1.0000   0.0017
 -12.000  -0.9984   0.03067   0.02734  -0.0409   1.0000   0.0018
 -11.750  -0.9997   0.02892   0.02539  -0.0379   1.0000   0.0018
 -11.500  -0.9993   0.02741   0.02372  -0.0347   1.0000   0.0018
 -11.250  -1.0032   0.02556   0.02164  -0.0304   1.0000   0.0018
 -11.000  -0.9849   0.02607   0.02225  -0.0290   1.0000   0.0020
 -10.750  -0.9819   0.02486   0.02088  -0.0254   1.0000   0.0020
 -10.500  -0.9808   0.02288   0.01864  -0.0214   1.0000   0.0020
 -10.250  -0.9631   0.02294   0.01873  -0.0200   1.0000   0.0021
 -10.000  -0.9566   0.02159   0.01720  -0.0167   1.0000   0.0022
  -9.500  -0.9141   0.01948   0.01482  -0.0160   0.9950   0.0024
  -9.250  -0.8904   0.01854   0.01376  -0.0160   0.9897   0.0025
  -9.000  -0.8653   0.01749   0.01258  -0.0162   0.9852   0.0026
  -8.750  -0.8397   0.01673   0.01169  -0.0165   0.9796   0.0028
  -8.500  -0.8122   0.01575   0.01058  -0.0172   0.9748   0.0029
  -8.250  -0.7819   0.01495   0.00967  -0.0184   0.9705   0.0030
  -8.000  -0.7503   0.01436   0.00900  -0.0198   0.9649   0.0032
  -7.750  -0.7177   0.01360   0.00815  -0.0215   0.9594   0.0033
  -7.500  -0.6886   0.01276   0.00721  -0.0225   0.9503   0.0040
  -7.250  -0.6575   0.01237   0.00679  -0.0237   0.9411   0.0045
  -7.000  -0.6303   0.01195   0.00630  -0.0240   0.9301   0.0049
  -6.750  -0.6053   0.01163   0.00588  -0.0237   0.9183   0.0055
  -6.500  -0.5827   0.01126   0.00542  -0.0229   0.9056   0.0059
  -6.250  -0.5595   0.01101   0.00509  -0.0221   0.8927   0.0062
  -6.000  -0.5387   0.01059   0.00456  -0.0209   0.8792   0.0070
  -5.750  -0.5168   0.01028   0.00417  -0.0198   0.8647   0.0079
  -5.250  -0.4709   0.00989   0.00364  -0.0181   0.8316   0.0101
  -5.000  -0.4478   0.00973   0.00336  -0.0173   0.8131   0.0107
  -4.750  -0.4250   0.00955   0.00306  -0.0163   0.7951   0.0120
  -4.500  -0.4021   0.00936   0.00281  -0.0154   0.7776   0.0160
  -4.250  -0.3788   0.00918   0.00260  -0.0146   0.7614   0.0230
  -4.000  -0.3558   0.00897   0.00240  -0.0138   0.7466   0.0400
  -3.750  -0.3324   0.00877   0.00222  -0.0131   0.7337   0.0580
  -3.500  -0.3088   0.00858   0.00203  -0.0124   0.7217   0.0807
  -3.250  -0.2876   0.00819   0.00183  -0.0114   0.7105   0.1423
  -3.000  -0.2686   0.00760   0.00157  -0.0099   0.7006   0.2389
  -2.750  -0.2553   0.00664   0.00127  -0.0075   0.6917   0.4202
  -2.500  -0.2338   0.00632   0.00115  -0.0065   0.6830   0.4857
  -2.250  -0.2094   0.00616   0.00106  -0.0059   0.6746   0.5205
  -2.000  -0.1852   0.00603   0.00101  -0.0053   0.6673   0.5584
  -1.750  -0.1597   0.00596   0.00098  -0.0049   0.6602   0.5852
  -1.500  -0.1341   0.00591   0.00095  -0.0045   0.6537   0.6048
  -1.250  -0.1072   0.00590   0.00091  -0.0044   0.6467   0.6147
  -1.000  -0.0806   0.00589   0.00089  -0.0043   0.6405   0.6244
  -0.750  -0.0538   0.00587   0.00087  -0.0042   0.6345   0.6334
  -0.500  -0.0268   0.00587   0.00085  -0.0041   0.6289   0.6410
  -0.250   0.0001   0.00585   0.00084  -0.0040   0.6234   0.6468
   0.000   0.0272   0.00586   0.00083  -0.0040   0.6174   0.6529
   0.250   0.0542   0.00586   0.00083  -0.0039   0.6123   0.6586
   0.500   0.0813   0.00585   0.00084  -0.0039   0.6070   0.6648
   0.750   0.1082   0.00586   0.00085  -0.0038   0.6018   0.6710
   1.000   0.1351   0.00585   0.00086  -0.0037   0.5968   0.6782
   1.250   0.1618   0.00585   0.00088  -0.0036   0.5901   0.6859
   1.500   0.1883   0.00586   0.00092  -0.0034   0.5822   0.6950
   1.750   0.2141   0.00587   0.00095  -0.0031   0.5721   0.7057
   2.000   0.2396   0.00589   0.00098  -0.0027   0.5574   0.7183
   2.250   0.2648   0.00590   0.00103  -0.0023   0.5440   0.7339
   2.500   0.2899   0.00593   0.00110  -0.0018   0.5283   0.7516
   2.750   0.3141   0.00598   0.00117  -0.0012   0.5068   0.7704
   3.000   0.3372   0.00613   0.00126  -0.0003   0.4686   0.7883
   3.250   0.3588   0.00641   0.00139   0.0008   0.4128   0.8042
   3.750   0.3911   0.00781   0.00201   0.0047   0.1920   0.8325
   4.000   0.4071   0.00852   0.00237   0.0067   0.0890   0.8461
   4.250   0.4290   0.00882   0.00259   0.0077   0.0571   0.8591
   4.500   0.4496   0.00922   0.00286   0.0089   0.0189   0.8728
   4.750   0.4733   0.00942   0.00311   0.0096   0.0127   0.8861
   5.000   0.4983   0.00958   0.00335   0.0100   0.0117   0.8996
   5.250   0.5242   0.00979   0.00365   0.0102   0.0104   0.9133
   5.500   0.5517   0.01007   0.00397   0.0100   0.0086   0.9263
   5.750   0.5809   0.01051   0.00451   0.0093   0.0073   0.9381
   6.000   0.6144   0.01079   0.00483   0.0077   0.0068   0.9475
   6.250   0.6484   0.01120   0.00529   0.0059   0.0061   0.9549
   6.500   0.6813   0.01159   0.00573   0.0043   0.0054   0.9609
   6.750   0.7152   0.01195   0.00610   0.0025   0.0046   0.9648
   7.000   0.7418   0.01272   0.00695   0.0021   0.0038   0.9710
   7.250   0.7714   0.01313   0.00740   0.0012   0.0037   0.9751
   7.500   0.7980   0.01373   0.00807   0.0009   0.0036   0.9801
   7.750   0.8224   0.01429   0.00869   0.0011   0.0033   0.9856
   8.000   0.8487   0.01507   0.00957   0.0007   0.0032   0.9895
   8.250   0.8748   0.01571   0.01027   0.0004   0.0030   0.9934
   8.500   0.9015   0.01636   0.01098  -0.0001   0.0027   0.9967
   8.750   0.9276   0.01732   0.01208  -0.0006   0.0026   0.9991
   9.000   0.9512   0.01785   0.01265  -0.0004   0.0024   1.0000
   9.250   0.9655   0.01824   0.01307   0.0017   0.0023   1.0000
   9.500   0.9771   0.01888   0.01378   0.0044   0.0022   1.0000
   9.750   0.9866   0.01973   0.01472   0.0073   0.0021   1.0000
  10.000   0.9847   0.02152   0.01673   0.0121   0.0019   1.0000
  10.250   0.9938   0.02202   0.01729   0.0151   0.0019   1.0000
  10.500   0.9905   0.02430   0.01985   0.0197   0.0018   1.0000
  10.750   0.9912   0.02614   0.02192   0.0234   0.0018   1.0000
  11.000   0.9941   0.02771   0.02366   0.0264   0.0018   1.0000
  11.250   0.9904   0.03005   0.02626   0.0299   0.0018   1.0000
  11.500   0.9906   0.03192   0.02833   0.0325   0.0017   1.0000
  11.750   0.9774   0.03527   0.03197   0.0358   0.0017   1.0000
  12.000   0.9643   0.03864   0.03560   0.0383   0.0017   1.0000
  12.250   0.9467   0.04270   0.03991   0.0400   0.0017   1.0000
  12.500   0.9174   0.04847   0.04598   0.0407   0.0017   1.0000
  12.750   0.8842   0.05546   0.05323   0.0396   0.0017   1.0000
  13.000   0.8669   0.06077   0.05869   0.0377   0.0017   1.0000
  13.250   0.8350   0.06919   0.06730   0.0337   0.0018   1.0000
  13.500   0.8130   0.07702   0.07527   0.0291   0.0018   1.0000
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