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Coanda 1 (coanda1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Coanda 1 (coanda1-il)
Reynolds number: 100,000
Max Cl/Cd: 47.75 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda1-il-100000-n5.txt
Download as CSV file: xf-coanda1-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 1                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4333   0.10402   0.09925  -0.0192   1.0000   0.0460
  -8.250  -0.4329   0.10080   0.09609  -0.0195   1.0000   0.0459
  -8.000  -0.4388   0.09865   0.09402  -0.0208   1.0000   0.0461
  -7.500  -0.4299   0.08728   0.08268  -0.0173   1.0000   0.0272
  -7.250  -0.4288   0.08414   0.07959  -0.0175   1.0000   0.0257
  -7.000  -0.4281   0.08069   0.07619  -0.0183   1.0000   0.0246
  -6.750  -0.4259   0.07718   0.07271  -0.0194   1.0000   0.0234
  -6.500  -0.4233   0.07300   0.06855  -0.0210   1.0000   0.0220
  -6.250  -0.4180   0.06759   0.06313  -0.0239   1.0000   0.0202
  -6.000  -0.4086   0.06394   0.05941  -0.0242   1.0000   0.0193
  -5.750  -0.4016   0.06043   0.05585  -0.0241   1.0000   0.0190
  -5.500  -0.3935   0.05653   0.05188  -0.0240   1.0000   0.0186
  -5.250  -0.3840   0.05262   0.04787  -0.0237   1.0000   0.0183
  -5.000  -0.3735   0.04864   0.04374  -0.0231   1.0000   0.0181
  -4.750  -0.3623   0.04439   0.03930  -0.0222   1.0000   0.0179
  -4.500  -0.3503   0.04024   0.03491  -0.0208   1.0000   0.0176
  -4.250  -0.3382   0.03544   0.02973  -0.0189   1.0000   0.0174
  -4.000  -0.3252   0.03038   0.02413  -0.0165   1.0000   0.0172
  -3.750  -0.3093   0.02598   0.01902  -0.0140   1.0000   0.0172
  -3.500  -0.2900   0.02324   0.01564  -0.0120   1.0000   0.0176
  -3.250  -0.2686   0.02151   0.01339  -0.0104   1.0000   0.0192
  -3.000  -0.2465   0.02014   0.01166  -0.0089   1.0000   0.0217
  -2.750  -0.2127   0.01926   0.01052  -0.0099   0.9962   0.0247
  -2.500  -0.1752   0.02027   0.01196  -0.0121   0.9890   0.0463
  -2.250  -0.1376   0.02057   0.01161  -0.0136   0.9823   0.0791
  -2.000  -0.1031   0.02124   0.01201  -0.0153   0.9749   0.0973
  -1.750  -0.0684   0.02097   0.01160  -0.0172   0.9683   0.1095
  -1.500  -0.0351   0.02037   0.01076  -0.0183   0.9608   0.1098
  -1.250   0.0027   0.01993   0.01005  -0.0203   0.9550   0.1118
  -1.000   0.0348   0.01947   0.00943  -0.0211   0.9460   0.1128
  -0.750   0.0723   0.01892   0.00877  -0.0231   0.9397   0.1128
  -0.500   0.1063   0.01845   0.00820  -0.0243   0.9308   0.1131
  -0.250   0.1414   0.01796   0.00769  -0.0258   0.9223   0.1135
   0.000   0.1820   0.01728   0.00707  -0.0284   0.9146   0.1148
   0.250   0.2199   0.01666   0.00652  -0.0302   0.9018   0.1165
   0.500   0.2593   0.01611   0.00603  -0.0323   0.8869   0.1181
   0.750   0.2961   0.01567   0.00564  -0.0338   0.8687   0.1202
   1.000   0.3360   0.01529   0.00526  -0.0359   0.8468   0.1225
   1.250   0.3761   0.01495   0.00489  -0.0380   0.8175   0.1266
   1.500   0.4167   0.01460   0.00455  -0.0402   0.7821   0.1322
   1.750   0.4547   0.01443   0.00434  -0.0420   0.7496   0.1361
   2.000   0.4891   0.01439   0.00422  -0.0430   0.7173   0.1390
   2.250   0.5196   0.01443   0.00425  -0.0433   0.6827   0.1425
   2.500   0.5482   0.01450   0.00432  -0.0432   0.6483   0.1479
   2.750   0.5752   0.01460   0.00445  -0.0428   0.6129   0.1593
   3.250   0.7058   0.01478   0.00529  -0.0599   0.3531   1.0000
   3.500   0.7218   0.01587   0.00564  -0.0580   0.2447   1.0000
   3.750   0.7418   0.01659   0.00607  -0.0567   0.1885   1.0000
   4.000   0.7620   0.01732   0.00656  -0.0553   0.1399   1.0000
   4.500   0.7974   0.01962   0.00828  -0.0516   0.0210   1.0000
   4.750   0.8176   0.02048   0.00934  -0.0500   0.0180   1.0000
   5.000   0.8376   0.02142   0.01051  -0.0483   0.0169   1.0000
   5.250   0.8573   0.02236   0.01175  -0.0465   0.0166   1.0000
   5.500   0.8757   0.02341   0.01304  -0.0446   0.0162   1.0000
   5.750   0.8928   0.02455   0.01440  -0.0426   0.0157   1.0000
   6.000   0.9085   0.02576   0.01581  -0.0403   0.0149   1.0000
   6.250   0.9233   0.02709   0.01730  -0.0380   0.0140   1.0000
   6.500   0.9379   0.02861   0.01895  -0.0356   0.0137   1.0000
   6.750   0.9537   0.03024   0.02070  -0.0334   0.0138   1.0000
   7.000   0.9711   0.03212   0.02272  -0.0314   0.0138   1.0000
   7.250   0.9890   0.03406   0.02494  -0.0296   0.0140   1.0000
   7.500   1.0064   0.03637   0.02750  -0.0276   0.0144   1.0000
   7.750   1.0218   0.03897   0.03041  -0.0255   0.0148   1.0000
   8.000   1.0340   0.04190   0.03368  -0.0230   0.0152   1.0000
   8.250   1.0432   0.04484   0.03694  -0.0205   0.0158   1.0000
   8.500   1.0485   0.04887   0.04126  -0.0179   0.0165   1.0000
   8.750   1.0657   0.04985   0.04250  -0.0156   0.0183   1.0000
   9.000   1.0636   0.05239   0.04564  -0.0114   0.0198   1.0000
   9.250   1.0563   0.05587   0.04956  -0.0075   0.0209   1.0000
   9.500   1.0485   0.05909   0.05307  -0.0041   0.0219   1.0000
   9.750   1.0321   0.06196   0.05617   0.0000   0.0217   1.0000
  10.000   1.0151   0.06512   0.05952   0.0033   0.0223   1.0000
  10.250   0.9979   0.06849   0.06307   0.0052   0.0225   1.0000
  10.500   0.9789   0.07259   0.06734   0.0055   0.0227   1.0000
  10.750   0.9631   0.07701   0.07190   0.0044   0.0230   1.0000
  11.000   0.9406   0.08302   0.07806   0.0009   0.0227   1.0000
  11.250   0.9206   0.09007   0.08524  -0.0039   0.0226   1.0000
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