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Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 33.32 at α=2.25°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-160-050-gn-500000-n1.txt
Download as CSV file: xf-cp-160-050-gn-500000-n1.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=16% T=5% R=0.86                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250   0.3635   0.11165   0.10749  -0.2330   0.8201   0.0065
 -13.000   0.3701   0.10993   0.10574  -0.2332   0.8168   0.0065
 -12.750   0.3762   0.10816   0.10395  -0.2333   0.8137   0.0066
 -12.500   0.3820   0.10639   0.10218  -0.2332   0.8102   0.0068
 -12.250   0.3877   0.10464   0.10042  -0.2332   0.8070   0.0071
 -12.000   0.3935   0.10302   0.09879  -0.2330   0.8039   0.0070
 -11.750   0.3988   0.10152   0.09728  -0.2326   0.8003   0.0072
 -11.500   0.4036   0.09995   0.09569  -0.2321   0.7970   0.0078
 -11.250   0.4088   0.09840   0.09414  -0.2317   0.7936   0.0079
 -11.000   0.4137   0.09680   0.09254  -0.2312   0.7906   0.0082
 -10.750   0.4183   0.09530   0.09103  -0.2306   0.7874   0.0083
 -10.500   0.4223   0.09391   0.08963  -0.2297   0.7840   0.0083
 -10.250   0.4259   0.09245   0.08816  -0.2287   0.7805   0.0086
 -10.000   0.4295   0.09102   0.08673  -0.2278   0.7766   0.0087
  -9.750   0.4336   0.08964   0.08535  -0.2269   0.7737   0.0088
  -9.500   0.4366   0.08831   0.08402  -0.2257   0.7703   0.0090
  -9.250   0.4387   0.08716   0.08286  -0.2241   0.7666   0.0090
  -9.000   0.4412   0.08595   0.08166  -0.2226   0.7624   0.0094
  -8.750   0.4438   0.08473   0.08044  -0.2212   0.7594   0.0096
  -8.500   0.4449   0.08355   0.07927  -0.2194   0.7561   0.0099
  -8.250   0.4436   0.08257   0.07830  -0.2168   0.7524   0.0101
  -8.000   0.4418   0.08161   0.07734  -0.2142   0.7484   0.0103
  -7.750   0.4407   0.08061   0.07636  -0.2117   0.7442   0.0104
  -7.500   0.4398   0.07966   0.07542  -0.2093   0.7409   0.0104
  -7.250   0.4354   0.07883   0.07460  -0.2060   0.7372   0.0107
  -7.000   0.4312   0.07814   0.07392  -0.2027   0.7334   0.0107
  -6.750   0.4267   0.07738   0.07318  -0.1994   0.7292   0.0108
  -6.500   0.4189   0.07679   0.07261  -0.1953   0.7252   0.0110
  -6.250   0.4115   0.07630   0.07215  -0.1912   0.7216   0.0111
  -6.000   0.4037   0.07578   0.07165  -0.1870   0.7179   0.0112
  -5.750   0.4009   0.07491   0.07080  -0.1842   0.7140   0.0115
  -5.500   0.3993   0.07391   0.06981  -0.1817   0.7094   0.0117
  -5.250   0.3990   0.07282   0.06873  -0.1796   0.7057   0.0122
  -5.000   0.3979   0.07179   0.06771  -0.1772   0.7024   0.0123
  -4.750   0.3995   0.07058   0.06651  -0.1756   0.6987   0.0125
  -4.500   0.4028   0.06932   0.06526  -0.1743   0.6945   0.0127
  -4.250   0.4058   0.06811   0.06405  -0.1730   0.6904   0.0128
  -4.000   0.4104   0.06681   0.06275  -0.1721   0.6870   0.0130
  -3.750   0.4175   0.06544   0.06138  -0.1717   0.6838   0.0131
  -3.500   0.4270   0.06392   0.05986  -0.1719   0.6802   0.0134
  -3.250   0.4364   0.06259   0.05853  -0.1718   0.6762   0.0135
  -3.000   0.4475   0.06113   0.05706  -0.1723   0.6724   0.0143
  -2.750   0.4618   0.05955   0.05546  -0.1734   0.6698   0.0146
  -2.500   0.4781   0.05793   0.05382  -0.1749   0.6669   0.0148
  -2.250   0.4971   0.05625   0.05213  -0.1769   0.6636   0.0149
  -2.000   0.5169   0.05457   0.05043  -0.1792   0.6598   0.0153
  -1.750   0.5385   0.05292   0.04875  -0.1817   0.6561   0.0155
  -1.500   0.5639   0.05115   0.04695  -0.1850   0.6534   0.0158
  -1.250   0.5901   0.04958   0.04535  -0.1882   0.6507   0.0161
  -1.000   0.6201   0.04792   0.04366  -0.1922   0.6477   0.0169
  -0.750   0.6523   0.04623   0.04193  -0.1967   0.6444   0.0172
  -0.500   0.6858   0.04462   0.04028  -0.2012   0.6408   0.0174
  -0.250   0.7222   0.04298   0.03859  -0.2063   0.6384   0.0177
   0.000   0.7597   0.04140   0.03696  -0.2115   0.6359   0.0181
   0.250   0.7991   0.03983   0.03535  -0.2171   0.6327   0.0186
   0.500   0.8376   0.03847   0.03395  -0.2221   0.6295   0.0196
   0.750   0.8784   0.03708   0.03251  -0.2275   0.6266   0.0200
   1.000   0.9191   0.03579   0.03117  -0.2328   0.6237   0.0203
   1.250   0.9593   0.03460   0.02993  -0.2378   0.6206   0.0208
   1.500   1.0004   0.03343   0.02869  -0.2429   0.6176   0.0213
   1.750   1.0374   0.03255   0.02777  -0.2468   0.6127   0.0221
   2.000   1.0636   0.03218   0.02730  -0.2485   0.5991   0.0225
   2.250   1.0791   0.03239   0.02736  -0.2480   0.5753   0.0227
   2.500   1.0822   0.03330   0.02805  -0.2451   0.5399   0.0229
   2.750   1.0686   0.03526   0.02972  -0.2392   0.4855   0.0231
   3.000   1.0575   0.03734   0.03148  -0.2340   0.4264   0.0232
   3.250   1.0162   0.04154   0.03510  -0.2239   0.3007   0.0231
   3.500   0.9908   0.04509   0.03813  -0.2171   0.1563   0.0231
   3.750   0.9957   0.04682   0.03952  -0.2154   0.0185   0.0234
   4.000   1.0279   0.04671   0.03933  -0.2181   0.0134   0.0239
   4.250   1.0598   0.04663   0.03919  -0.2206   0.0130   0.0244
   4.500   1.0885   0.04675   0.03926  -0.2224   0.0126   0.0253
   4.750   1.1169   0.04693   0.03938  -0.2240   0.0123   0.0255
   5.000   1.1450   0.04715   0.03954  -0.2256   0.0121   0.0258
   5.250   1.1729   0.04740   0.03973  -0.2270   0.0119   0.0263
   5.500   1.2002   0.04771   0.03997  -0.2282   0.0117   0.0267
   5.750   1.2280   0.04802   0.04020  -0.2295   0.0116   0.0273
   6.000   1.2521   0.04854   0.04067  -0.2300   0.0113   0.0282
   6.250   1.2762   0.04909   0.04116  -0.2305   0.0113   0.0285
   6.500   1.3002   0.04966   0.04166  -0.2309   0.0112   0.0288
   6.750   1.3240   0.05024   0.04216  -0.2312   0.0111   0.0291
   7.000   1.3477   0.05084   0.04267  -0.2314   0.0109   0.0296
   7.250   1.3751   0.05126   0.04293  -0.2321   0.0109   0.0306
   7.500   1.3985   0.05187   0.04338  -0.2321   0.0108   0.0314
   7.750   1.4257   0.05211   0.04327  -0.2326   0.0107   0.0323
   8.000   1.4434   0.05298   0.04395  -0.2317   0.0107   0.0330
   8.250   1.4584   0.05407   0.04496  -0.2304   0.0107   0.0335
   8.750   1.4837   0.05676   0.04767  -0.2273   0.0105   0.0341
   9.000   1.4959   0.05816   0.04910  -0.2258   0.0104   0.0342
   9.250   1.5081   0.05958   0.05053  -0.2243   0.0103   0.0343
   9.500   1.5195   0.06111   0.05208  -0.2227   0.0102   0.0343
   9.750   1.5307   0.06268   0.05368  -0.2211   0.0101   0.0344
  10.000   1.5421   0.06424   0.05528  -0.2196   0.0100   0.0345
  10.250   1.5531   0.06584   0.05692  -0.2181   0.0099   0.0346
  10.500   1.5629   0.06761   0.05874  -0.2165   0.0099   0.0347
  10.750   1.5729   0.06936   0.06054  -0.2150   0.0098   0.0348
  11.000   1.5829   0.07112   0.06234  -0.2134   0.0098   0.0349
  11.250   1.5918   0.07304   0.06432  -0.2119   0.0097   0.0351
  11.500   1.6006   0.07499   0.06633  -0.2104   0.0097   0.0352
  11.750   1.6097   0.07690   0.06829  -0.2089   0.0096   0.0355
  12.000   1.6177   0.07901   0.07046  -0.2075   0.0095   0.0358
  12.250   1.6258   0.08111   0.07262  -0.2060   0.0095   0.0360
  12.500   1.6338   0.08323   0.07480  -0.2046   0.0094   0.0363
  12.750   1.6410   0.08547   0.07711  -0.2033   0.0093   0.0366
  13.000   1.6482   0.08773   0.07944  -0.2019   0.0092   0.0381
  13.250   1.6554   0.08998   0.08176  -0.2006   0.0092   0.0402
  13.500   1.6618   0.09236   0.08421  -0.1993   0.0091   0.0417
  13.750   1.6682   0.09472   0.08665  -0.1981   0.0090   0.0446
  14.000   1.6751   0.09703   0.08907  -0.1969   0.0089   0.0675
  14.250   1.6813   0.09950   0.09173  -0.1959   0.0088   0.1972
  14.500   1.6874   0.10189   0.09421  -0.1947   0.0088   0.2384
  14.750   1.6938   0.10421   0.09662  -0.1937   0.0087   0.2774
  15.000   1.7004   0.10665   0.09929  -0.1928   0.0085   0.5640
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