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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 200,000
Max Cl/Cd: 72.74 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-200000.txt
Download as CSV file: xf-fx74cl5140-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX74_CL5_140                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.1671   0.10375   0.09846  -0.1222   0.6482   0.0155
  -9.750   0.1744   0.10205   0.09671  -0.1236   0.6407   0.0156
  -9.500   0.1811   0.10045   0.09506  -0.1251   0.6342   0.0156
  -8.750   0.2167   0.09092   0.08535  -0.1263   0.6173   0.0163
  -8.500   0.2271   0.08856   0.08296  -0.1270   0.6129   0.0167
  -8.250   0.2368   0.08648   0.08088  -0.1278   0.6083   0.0168
  -8.000   0.2465   0.08430   0.07868  -0.1286   0.6046   0.0172
  -7.750   0.2566   0.08220   0.07652  -0.1296   0.6013   0.0177
  -7.500   0.2661   0.08016   0.07450  -0.1304   0.5979   0.0181
  -7.250   0.2752   0.07814   0.07249  -0.1312   0.5944   0.0184
  -7.000   0.2843   0.07614   0.07049  -0.1320   0.5913   0.0190
  -6.750   0.2932   0.07418   0.06851  -0.1329   0.5883   0.0194
  -6.500   0.3020   0.07234   0.06665  -0.1339   0.5860   0.0200
  -6.250   0.3076   0.07079   0.06513  -0.1344   0.5836   0.0204
  -6.000   0.3153   0.06950   0.06391  -0.1370   0.5810   0.0209
  -5.750   0.3290   0.06757   0.06199  -0.1402   0.5786   0.0211
  -5.500   0.3469   0.06543   0.05985  -0.1448   0.5762   0.0212
  -5.250   0.3694   0.06286   0.05724  -0.1510   0.5739   0.0213
  -5.000   0.3722   0.05971   0.05409  -0.1465   0.5719   0.0223
  -4.750   0.3880   0.05757   0.05192  -0.1477   0.5697   0.0232
  -4.500   0.4061   0.05525   0.04964  -0.1506   0.5673   0.0245
  -4.250   0.4298   0.05266   0.04705  -0.1554   0.5647   0.0259
  -4.000   0.4641   0.04963   0.04395  -0.1634   0.5623   0.0279
  -3.500   0.5313   0.04320   0.03728  -0.1760   0.5581   0.0315
  -3.250   0.5626   0.04099   0.03495  -0.1800   0.5562   0.0353
  -3.000   0.6180   0.03718   0.03080  -0.1903   0.5542   0.0415
  -2.750   0.6412   0.03566   0.02934  -0.1914   0.5521   0.0470
  -2.500   0.6812   0.03335   0.02686  -0.1964   0.5499   0.0583
  -0.750   0.9608   0.02280   0.01427  -0.2184   0.5354   0.0767
  -0.500   0.9960   0.02188   0.01295  -0.2188   0.5334   0.0536
  -0.250   1.0285   0.02116   0.01217  -0.2196   0.5315   0.0458
   0.000   1.0585   0.02117   0.01205  -0.2197   0.5297   0.0401
   0.250   1.0927   0.02075   0.01161  -0.2212   0.5279   0.0373
   0.500   1.1268   0.02073   0.01146  -0.2226   0.5262   0.0352
   0.750   1.1579   0.02092   0.01154  -0.2234   0.5243   0.0349
   1.000   1.1865   0.02109   0.01170  -0.2238   0.5221   0.0414
   1.250   1.2276   0.02052   0.01258  -0.2275   0.5198   0.7106
   1.500   1.2485   0.02075   0.01295  -0.2257   0.5177   0.8085
   1.750   1.2596   0.02070   0.01304  -0.2218   0.5158   0.8866
   2.000   1.2731   0.02066   0.01302  -0.2186   0.5141   1.0000
   2.250   1.3036   0.02105   0.01325  -0.2196   0.5123   1.0000
   2.500   1.3342   0.02154   0.01360  -0.2205   0.5106   1.0000
   2.750   1.3608   0.02206   0.01414  -0.2209   0.5085   1.0000
   3.000   1.3868   0.02260   0.01472  -0.2211   0.5063   1.0000
   3.250   1.4134   0.02312   0.01527  -0.2214   0.5042   1.0000
   3.500   1.4406   0.02361   0.01578  -0.2218   0.5022   1.0000
   3.750   1.4682   0.02404   0.01619  -0.2222   0.5002   1.0000
   4.000   1.4964   0.02444   0.01655  -0.2227   0.4983   1.0000
   4.250   1.5250   0.02486   0.01692  -0.2233   0.4967   1.0000
   4.500   1.5535   0.02548   0.01749  -0.2239   0.4952   1.0000
   4.750   1.5742   0.02625   0.01847  -0.2233   0.4929   1.0000
   5.000   1.5956   0.02703   0.01938  -0.2228   0.4905   1.0000
   5.250   1.6187   0.02772   0.02016  -0.2225   0.4882   1.0000
   5.500   1.6433   0.02831   0.02080  -0.2225   0.4862   1.0000
   5.750   1.6694   0.02876   0.02129  -0.2227   0.4843   1.0000
   6.000   1.6966   0.02916   0.02173  -0.2230   0.4825   1.0000
   6.250   1.7246   0.02963   0.02221  -0.2234   0.4810   1.0000
   6.500   1.7457   0.03055   0.02326  -0.2229   0.4789   1.0000
   6.750   1.7580   0.03172   0.02471  -0.2211   0.4752   1.0000
   7.000   1.7784   0.03242   0.02554  -0.2204   0.4723   1.0000
   7.250   1.8031   0.03289   0.02608  -0.2204   0.4701   1.0000
   7.500   1.8286   0.03335   0.02663  -0.2204   0.4684   1.0000
   7.750   1.8554   0.03380   0.02715  -0.2207   0.4668   1.0000
   8.000   1.8841   0.03432   0.02772  -0.2213   0.4654   1.0000
   8.250   1.8784   0.03661   0.03042  -0.2170   0.4608   1.0000
   8.500   1.8917   0.03769   0.03170  -0.2154   0.4575   1.0000
   8.750   1.9338   0.03607   0.03004  -0.2172   0.4539   1.0000
   9.000   1.9677   0.03432   0.02827  -0.2176   0.4472   1.0000
   9.250   1.9939   0.03310   0.02713  -0.2169   0.4403   1.0000
   9.500   2.0205   0.03112   0.02513  -0.2160   0.4308   1.0000
   9.750   2.0441   0.02903   0.02300  -0.2143   0.4196   1.0000
  10.000   2.0455   0.02812   0.02220  -0.2093   0.4060   1.0000
  10.250   2.0298   0.02820   0.02246  -0.2017   0.3891   1.0000
  10.500   2.0139   0.02885   0.02307  -0.1948   0.3620   1.0000
  10.750   1.9900   0.03109   0.02515  -0.1881   0.3229   1.0000
  11.000   1.9624   0.03463   0.02853  -0.1826   0.2926   1.0000
  11.250   1.9326   0.03928   0.03311  -0.1784   0.2658   1.0000
  11.500   1.9039   0.04471   0.03854  -0.1756   0.2472   1.0000
  11.750   1.8739   0.05104   0.04492  -0.1739   0.2308   1.0000
  12.000   1.8431   0.05807   0.05201  -0.1729   0.2139   1.0000
  12.250   1.8150   0.06510   0.05911  -0.1724   0.2003   1.0000
  12.500   1.7856   0.07254   0.06659  -0.1722   0.1873   1.0000
  12.750   1.7575   0.08000   0.07408  -0.1722   0.1718   1.0000
  13.000   1.7290   0.08773   0.08179  -0.1725   0.1530   1.0000
  13.250   1.6988   0.09596   0.08995  -0.1732   0.1309   1.0000
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