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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=5


Details Polar file
Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 46.7 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-180-050-gn-500000-n5.txt
Download as CSV file: xf-cp-180-050-gn-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500   0.5156   0.10922   0.10555  -0.2680   0.8810   0.0143
 -13.250   0.5123   0.10812   0.10448  -0.2651   0.8775   0.0144
 -13.000   0.5104   0.10713   0.10350  -0.2626   0.8740   0.0144
 -12.750   0.5161   0.10530   0.10166  -0.2627   0.8712   0.0145
 -12.500   0.5273   0.10326   0.09959  -0.2642   0.8690   0.0146
 -12.250   0.5427   0.10124   0.09753  -0.2669   0.8671   0.0149
 -12.000   0.5585   0.09906   0.09532  -0.2697   0.8653   0.0149
 -11.750   0.5469   0.09888   0.09519  -0.2640   0.8612   0.0150
 -11.500   0.5477   0.09782   0.09414  -0.2621   0.8579   0.0153
 -11.250   0.5552   0.09626   0.09256  -0.2623   0.8552   0.0161
 -11.000   0.5668   0.09428   0.09055  -0.2638   0.8528   0.0167
 -10.750   0.5817   0.09203   0.08826  -0.2664   0.8509   0.0169
 -10.500   0.5729   0.09160   0.08788  -0.2616   0.8470   0.0169
 -10.250   0.5689   0.09072   0.08701  -0.2583   0.8434   0.0170
  -9.500   0.5964   0.08565   0.08186  -0.2602   0.8357   0.0174
  -9.250   0.5833   0.08557   0.08185  -0.2541   0.8315   0.0175
  -9.000   0.5760   0.08515   0.08146  -0.2497   0.8276   0.0177
  -8.750   0.5794   0.08405   0.08034  -0.2484   0.8246   0.0180
  -8.500   0.5886   0.08255   0.07882  -0.2487   0.8221   0.0185
  -8.250   0.5979   0.08103   0.07726  -0.2492   0.8196   0.0191
  -8.000   0.5750   0.08145   0.07777  -0.2405   0.8145   0.0195
  -7.750   0.5701   0.08081   0.07714  -0.2370   0.8108   0.0195
  -7.500   0.5730   0.07956   0.07587  -0.2357   0.8078   0.0197
  -7.250   0.5813   0.07801   0.07428  -0.2361   0.8053   0.0199
  -7.000   0.5612   0.07838   0.07473  -0.2283   0.8005   0.0198
  -6.750   0.5470   0.07829   0.07467  -0.2224   0.7960   0.0199
  -6.500   0.5431   0.07759   0.07397  -0.2194   0.7927   0.0199
  -6.250   0.5455   0.07643   0.07279  -0.2182   0.7899   0.0199
  -6.000   0.5242   0.07682   0.07325  -0.2105   0.7850   0.0199
  -5.750   0.5112   0.07657   0.07304  -0.2048   0.7805   0.0200
  -5.500   0.5134   0.07547   0.07193  -0.2032   0.7774   0.0202
  -5.250   0.5232   0.07398   0.07041  -0.2034   0.7750   0.0204
  -5.000   0.5297   0.07271   0.06913  -0.2029   0.7723   0.0207
  -4.750   0.5059   0.07321   0.06972  -0.1948   0.7666   0.0207
  -4.500   0.5067   0.07227   0.06879  -0.1928   0.7628   0.0212
  -4.250   0.5170   0.07069   0.06718  -0.1932   0.7602   0.0219
  -4.000   0.5333   0.06868   0.06513  -0.1952   0.7581   0.0225
  -3.750   0.5237   0.06833   0.06483  -0.1909   0.7537   0.0226
  -3.500   0.5197   0.06769   0.06422  -0.1879   0.7490   0.0227
  -3.250   0.5317   0.06607   0.06258  -0.1888   0.7460   0.0227
  -3.000   0.5511   0.06403   0.06050  -0.1914   0.7438   0.0228
  -2.750   0.5778   0.06165   0.05806  -0.1959   0.7419   0.0228
  -2.500   0.5728   0.06113   0.05760  -0.1924   0.7376   0.0229
  -2.250   0.5760   0.06031   0.05680  -0.1908   0.7335   0.0230
  -2.000   0.5929   0.05891   0.05538  -0.1922   0.7306   0.0234
  -1.750   0.6180   0.05712   0.05355  -0.1956   0.7284   0.0241
  -1.500   0.6491   0.05505   0.05143  -0.2003   0.7267   0.0251
  -1.250   0.6908   0.05254   0.04886  -0.2077   0.7253   0.0257
  -1.000   0.7006   0.05189   0.04824  -0.2077   0.7210   0.0258
  -0.750   0.7290   0.05039   0.04672  -0.2118   0.7177   0.0258
  -0.500   0.7610   0.04851   0.04481  -0.2164   0.7153   0.0259
  -0.250   0.7900   0.04696   0.04323  -0.2199   0.7132   0.0263
   0.000   0.8287   0.04530   0.04152  -0.2255   0.7116   0.0271
   0.250   0.8786   0.04328   0.03943  -0.2336   0.7101   0.0285
   0.750   0.9791   0.03999   0.03603  -0.2502   0.7058   0.0289
   1.250   1.0429   0.03774   0.03377  -0.2575   0.7003   0.0293
   1.500   1.0809   0.03673   0.03273  -0.2622   0.6981   0.0304
   1.750   1.1335   0.03534   0.03127  -0.2700   0.6963   0.0316
   2.000   1.1983   0.03384   0.02967  -0.2804   0.6948   0.0319
   2.500   1.2792   0.03197   0.02773  -0.2902   0.6893   0.0323
   3.000   1.3344   0.03131   0.02697  -0.2938   0.6753   0.0333
   3.500   1.4047   0.03104   0.02654  -0.3004   0.6592   0.0353
   4.000   1.4538   0.03113   0.02653  -0.3024   0.6414   0.0357
   4.250   1.4659   0.03156   0.02695  -0.3009   0.6302   0.0362
   4.500   1.4797   0.03225   0.02757  -0.2996   0.6156   0.0367
   4.750   1.4860   0.03344   0.02862  -0.2970   0.5946   0.0373
   5.000   1.4926   0.03478   0.02984  -0.2946   0.5734   0.0380
   5.250   1.4998   0.03681   0.03164  -0.2923   0.5438   0.0392
   5.500   1.4927   0.03951   0.03412  -0.2877   0.5084   0.0393
   5.750   1.4749   0.04300   0.03736  -0.2815   0.4631   0.0393
   6.000   1.4449   0.04754   0.04157  -0.2738   0.4034   0.0393
   6.250   1.4142   0.05246   0.04612  -0.2664   0.3305   0.0393
   6.500   1.3839   0.05762   0.05087  -0.2596   0.2421   0.0393
   6.750   1.3481   0.06355   0.05632  -0.2524   0.1073   0.0393
   7.000   1.3520   0.06659   0.05910  -0.2508   0.0241   0.0394
   7.500   1.3844   0.06878   0.06130  -0.2503   0.0189   0.0405
   7.750   1.4025   0.07015   0.06267  -0.2503   0.0182   0.0424
   8.000   1.4343   0.07160   0.06401  -0.2522   0.0178   0.0439
   8.250   1.4579   0.07292   0.06526  -0.2529   0.0174   0.0440
   8.500   1.4798   0.07426   0.06656  -0.2534   0.0171   0.0440
   9.000   1.5078   0.07742   0.06975  -0.2521   0.0164   0.0419
   9.250   1.5276   0.07904   0.07130  -0.2522   0.0160   0.0427
   9.500   1.5463   0.08070   0.07288  -0.2521   0.0156   0.0421
   9.750   1.5727   0.08226   0.07416  -0.2531   0.0153   0.0404
  10.000   1.5841   0.08433   0.07617  -0.2520   0.0151   0.0406
  10.250   1.5939   0.08648   0.07829  -0.2507   0.0149   0.0408
  10.500   1.6023   0.08873   0.08054  -0.2493   0.0147   0.0412
  10.750   1.6090   0.09120   0.08302  -0.2478   0.0145   0.0416
  11.000   1.6171   0.09342   0.08525  -0.2464   0.0145   0.0425
  11.250   1.6253   0.09564   0.08749  -0.2450   0.0144   0.0430
  11.500   1.6321   0.09807   0.08996  -0.2436   0.0143   0.0430
  11.750   1.6387   0.10052   0.09244  -0.2423   0.0142   0.0430
  12.000   1.6456   0.10292   0.09489  -0.2409   0.0140   0.0431
  12.250   1.6511   0.10553   0.09756  -0.2396   0.0139   0.0433
  12.500   1.6567   0.10811   0.10020  -0.2383   0.0138   0.0435
  12.750   1.6627   0.11064   0.10280  -0.2371   0.0137   0.0438
  13.000   1.6678   0.11334   0.10558  -0.2359   0.0135   0.0443
  13.250   1.6731   0.11595   0.10825  -0.2348   0.0134   0.0452
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