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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 200,000
Max Cl/Cd: 67.13 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda3-il-200000-n5.txt
Download as CSV file: xf-coanda3-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 3                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4203   0.08911   0.08586  -0.0253   1.0000   0.0221
  -8.250  -0.4281   0.08666   0.08347  -0.0245   1.0000   0.0225
  -8.000  -0.4403   0.08456   0.08145  -0.0230   1.0000   0.0227
  -7.750  -0.4501   0.08214   0.07908  -0.0219   1.0000   0.0228
  -7.500  -0.4568   0.07922   0.07620  -0.0215   1.0000   0.0232
  -7.250  -0.4616   0.07613   0.07314  -0.0215   1.0000   0.0236
  -7.000  -0.4521   0.07165   0.06860  -0.0253   0.9980   0.0242
  -6.750  -0.4306   0.06563   0.06249  -0.0322   0.9937   0.0247
  -5.750  -0.3398   0.03445   0.03005  -0.0481   0.9751   0.0091
  -5.500  -0.3205   0.02949   0.02448  -0.0484   0.9705   0.0087
  -5.250  -0.2952   0.02574   0.02008  -0.0487   0.9677   0.0085
  -5.000  -0.2747   0.02348   0.01733  -0.0473   0.9625   0.0086
  -4.750  -0.2480   0.02163   0.01506  -0.0471   0.9590   0.0087
  -4.500  -0.2191   0.01959   0.01257  -0.0473   0.9566   0.0103
  -4.250  -0.1922   0.01819   0.01098  -0.0470   0.9531   0.0106
  -4.000  -0.1671   0.01709   0.00971  -0.0462   0.9484   0.0108
  -3.750  -0.1371   0.01616   0.00860  -0.0465   0.9452   0.0113
  -3.500  -0.1042   0.01539   0.00763  -0.0473   0.9428   0.0120
  -3.250  -0.0754   0.01482   0.00688  -0.0472   0.9388   0.0128
  -3.000  -0.0475   0.01420   0.00608  -0.0470   0.9339   0.0159
  -2.750  -0.0131   0.01367   0.00535  -0.0481   0.9304   0.0173
  -2.500   0.0239   0.01302   0.00467  -0.0497   0.9278   0.0268
  -2.250   0.0502   0.01282   0.00468  -0.0492   0.9196   0.0768
  -2.000   0.0895   0.01288   0.00470  -0.0516   0.9157   0.0935
  -1.750   0.1195   0.01290   0.00472  -0.0520   0.9087   0.1052
  -1.500   0.1540   0.01262   0.00438  -0.0533   0.9029   0.1085
  -1.250   0.1843   0.01239   0.00409  -0.0536   0.8954   0.1116
  -1.000   0.2164   0.01204   0.00378  -0.0545   0.8882   0.1157
  -0.750   0.2443   0.01182   0.00357  -0.0544   0.8781   0.1194
  -0.500   0.2746   0.01160   0.00333  -0.0548   0.8679   0.1234
  -0.250   0.3041   0.01138   0.00311  -0.0549   0.8547   0.1278
   0.000   0.3322   0.01117   0.00293  -0.0548   0.8396   0.1344
   0.250   0.3607   0.01100   0.00278  -0.0548   0.8240   0.1425
   0.500   0.3914   0.01078   0.00259  -0.0553   0.8025   0.1574
   0.750   0.4148   0.00982   0.00249  -0.0545   0.7754   0.4607
   1.250   0.5961   0.00913   0.00270  -0.0818   0.6906   1.0000
   1.750   0.6388   0.00955   0.00285  -0.0789   0.6213   1.0000
   2.000   0.6585   0.00981   0.00296  -0.0771   0.5794   1.0000
   2.250   0.6762   0.01016   0.00313  -0.0750   0.5238   1.0000
   2.500   0.6916   0.01064   0.00331  -0.0725   0.4581   1.0000
   2.750   0.7079   0.01113   0.00357  -0.0702   0.4073   1.0000
   3.000   0.7252   0.01161   0.00387  -0.0682   0.3674   1.0000
   3.250   0.7403   0.01226   0.00423  -0.0659   0.3132   1.0000
   3.500   0.7578   0.01278   0.00454  -0.0640   0.2624   1.0000
   3.750   0.7732   0.01351   0.00486  -0.0619   0.1859   1.0000
   4.000   0.7785   0.01540   0.00574  -0.0582   0.0229   1.0000
   4.250   0.7976   0.01602   0.00646  -0.0564   0.0167   1.0000
   4.500   0.8175   0.01654   0.00715  -0.0548   0.0138   1.0000
   4.750   0.8367   0.01717   0.00796  -0.0530   0.0123   1.0000
   5.000   0.8549   0.01792   0.00889  -0.0510   0.0113   1.0000
   5.250   0.8712   0.01882   0.00996  -0.0488   0.0104   1.0000
   5.500   0.8777   0.02056   0.01181  -0.0451   0.0087   1.0000
   5.750   0.8938   0.02142   0.01276  -0.0429   0.0083   1.0000
   6.000   0.9082   0.02261   0.01400  -0.0405   0.0080   1.0000
   6.250   0.9238   0.02391   0.01541  -0.0383   0.0078   1.0000
   6.500   0.9413   0.02547   0.01705  -0.0364   0.0076   1.0000
   6.750   0.9607   0.02713   0.01882  -0.0349   0.0076   1.0000
   7.000   0.9805   0.02902   0.02087  -0.0334   0.0075   1.0000
   7.250   0.9988   0.03080   0.02287  -0.0316   0.0071   1.0000
   7.500   1.0153   0.03275   0.02506  -0.0297   0.0071   1.0000
   7.750   1.0296   0.03418   0.02649  -0.0284   0.0056   1.0000
   8.000   1.0427   0.03699   0.02950  -0.0265   0.0054   1.0000
   8.500   1.0604   0.04125   0.03437  -0.0208   0.0056   1.0000
   8.750   1.0633   0.04429   0.03769  -0.0177   0.0055   1.0000
   9.000   1.0636   0.04613   0.03987  -0.0138   0.0056   1.0000
   9.250   1.0511   0.04849   0.04272  -0.0080   0.0060   1.0000
   9.500   1.0381   0.05117   0.04571  -0.0030   0.0063   1.0000
   9.750   1.0251   0.05388   0.04866   0.0009   0.0063   1.0000
  10.000   1.0093   0.05714   0.05218   0.0041   0.0067   1.0000
  10.250   0.9936   0.06047   0.05572   0.0061   0.0067   1.0000
  10.500   0.9765   0.06439   0.05985   0.0070   0.0069   1.0000
  10.750   0.9605   0.06857   0.06420   0.0067   0.0069   1.0000
  11.000   0.9424   0.07368   0.06949   0.0051   0.0070   1.0000
  11.250   0.9243   0.07964   0.07560   0.0021   0.0070   1.0000
  11.500   0.9078   0.08621   0.08232  -0.0021   0.0070   1.0000
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