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Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 55.32 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-180-050-gn-500000.txt
Download as CSV file: xf-cp-180-050-gn-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=18% T=5% R=0.78                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000   0.4701   0.11027   0.10719  -0.2465   0.9028   0.0149
 -14.750   0.4810   0.10812   0.10503  -0.2483   0.9012   0.0152
 -14.500   0.4945   0.10565   0.10253  -0.2510   0.9000   0.0156
 -14.250   0.5094   0.10292   0.09976  -0.2542   0.8990   0.0163
 -14.000   0.5249   0.10020   0.09701  -0.2575   0.8980   0.0166
 -13.750   0.5409   0.09734   0.09412  -0.2610   0.8971   0.0169
 -13.500   0.5566   0.09454   0.09127  -0.2644   0.8961   0.0171
  -8.500   0.6409   0.08104   0.07753  -0.2648   0.8545   0.0214
  -8.250   0.6619   0.07883   0.07528  -0.2685   0.8529   0.0220
  -8.000   0.6861   0.07649   0.07289  -0.2732   0.8514   0.0226
  -7.750   0.6174   0.07975   0.07631  -0.2512   0.8429   0.0223
  -7.500   0.6259   0.07820   0.07474  -0.2514   0.8402   0.0226
  -7.250   0.6422   0.07652   0.07302  -0.2540   0.8382   0.0228
  -5.750   0.5441   0.07681   0.07351  -0.2144   0.8111   0.0229
  -5.500   0.5575   0.07477   0.07145  -0.2155   0.8091   0.0231
  -5.250   0.5779   0.07257   0.06922  -0.2185   0.8076   0.0235
  -5.000   0.6019   0.07026   0.06687  -0.2224   0.8062   0.0239
  -4.750   0.5263   0.07397   0.07073  -0.2009   0.7958   0.0235
  -4.500   0.5409   0.07210   0.06884  -0.2024   0.7938   0.0241
  -4.250   0.5628   0.06982   0.06652  -0.2057   0.7923   0.0246
  -4.000   0.5893   0.06733   0.06399  -0.2101   0.7910   0.0254
  -3.750   0.5235   0.07055   0.06734  -0.1917   0.7809   0.0250
  -3.500   0.5407   0.06859   0.06536  -0.1937   0.7786   0.0255
  -3.250   0.5683   0.06620   0.06293  -0.1985   0.7772   0.0257
  -2.750   0.6340   0.06076   0.05739  -0.2103   0.7750   0.0259
  -2.500   0.6647   0.05817   0.05476  -0.2149   0.7739   0.0263
  -0.500   0.8007   0.04886   0.04539  -0.2263   0.7473   0.0290
  -0.250   0.8352   0.04664   0.04313  -0.2309   0.7461   0.0293
   0.000   0.8822   0.04453   0.04097  -0.2383   0.7453   0.0300
   0.250   0.9379   0.04225   0.03862  -0.2477   0.7446   0.0310
   0.500   1.0164   0.04003   0.03630  -0.2622   0.7441   0.0319
   0.750   1.0882   0.03768   0.03385  -0.2751   0.7436   0.0321
   1.000   1.1267   0.03564   0.03178  -0.2799   0.7425   0.0324
   1.250   1.1845   0.03386   0.02994  -0.2890   0.7418   0.0332
   2.250   1.3351   0.03083   0.02681  -0.3066   0.7297   0.0357
   2.500   1.3966   0.02881   0.02466  -0.3154   0.7260   0.0365
   2.750   1.3890   0.02962   0.02555  -0.3098   0.7192   0.0367
   3.000   1.4222   0.02895   0.02482  -0.3125   0.7134   0.0379
   3.250   1.5120   0.02733   0.02296  -0.3268   0.7088   0.0395
   3.500   1.4999   0.02813   0.02387  -0.3201   0.7023   0.0397
   3.750   1.5185   0.02770   0.02340  -0.3196   0.6953   0.0402
   4.000   1.5342   0.02789   0.02360  -0.3185   0.6883   0.0410
   4.250   1.5520   0.02810   0.02377  -0.3178   0.6800   0.0420
   4.500   1.5647   0.02872   0.02436  -0.3160   0.6691   0.0432
   4.750   1.5928   0.02930   0.02478  -0.3171   0.6546   0.0442
   5.000   1.5903   0.03030   0.02574  -0.3125   0.6368   0.0445
   5.250   1.5816   0.03196   0.02726  -0.3069   0.6109   0.0447
   5.500   1.5661   0.03435   0.02948  -0.3002   0.5769   0.0450
   5.750   1.5433   0.03752   0.03242  -0.2926   0.5336   0.0452
   6.000   1.5175   0.04126   0.03591  -0.2849   0.4882   0.0453
   6.250   1.4881   0.04564   0.03999  -0.2771   0.4338   0.0454
   6.500   1.4565   0.05052   0.04454  -0.2695   0.3691   0.0454
   6.750   1.4198   0.05620   0.04978  -0.2616   0.2806   0.0452
   7.000   1.3914   0.06148   0.05464  -0.2553   0.1843   0.0452
   7.250   1.3671   0.06670   0.05944  -0.2500   0.0502   0.0454
   7.500   1.3811   0.06849   0.06115  -0.2495   0.0304   0.0465
   7.750   1.4154   0.07023   0.06277  -0.2517   0.0286   0.0494
   8.000   1.4295   0.07139   0.06397  -0.2513   0.0275   0.0500
   8.250   1.4440   0.07278   0.06540  -0.2507   0.0267   0.0508
   8.500   1.4601   0.07430   0.06694  -0.2503   0.0260   0.0523
   8.750   1.4873   0.07615   0.06866  -0.2515   0.0252   0.0559
   9.000   1.4961   0.07806   0.07063  -0.2502   0.0244   0.0567
   9.250   1.5058   0.08007   0.07268  -0.2490   0.0240   0.0582
   9.500   1.5248   0.08237   0.07487  -0.2490   0.0237   0.0635
   9.750   1.5291   0.08488   0.07748  -0.2474   0.0234   0.0646
  10.000   1.5377   0.08700   0.07966  -0.2461   0.0233   0.0667
  10.250   1.5533   0.08925   0.08181  -0.2457   0.0232   0.0731
  10.500   1.5598   0.09168   0.08432  -0.2443   0.0230   0.0745
  10.750   1.5670   0.09410   0.08679  -0.2430   0.0229   0.0772
  11.000   1.5769   0.09665   0.08930  -0.2420   0.0227   0.0847
  11.250   1.5817   0.09935   0.09207  -0.2406   0.0226   0.0872
  11.500   1.5891   0.10198   0.09470  -0.2394   0.0225   0.0968
  11.750   1.5937   0.10472   0.09752  -0.2381   0.0224   0.1000
  12.000   1.5994   0.10743   0.10024  -0.2368   0.0224   0.1107
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