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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=9


Details Polar file
Airfoil: Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 58.33 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-160-050-gn-500000.txt
Download as CSV file: xf-cp-160-050-gn-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.4073   0.10716   0.10391  -0.2370   0.9147   0.0202
 -11.750   0.4206   0.10484   0.10158  -0.2391   0.9127   0.0208
 -11.500   0.4382   0.10213   0.09884  -0.2427   0.9113   0.0212
 -11.250   0.4573   0.09955   0.09622  -0.2468   0.9100   0.0213
 -11.000   0.4766   0.09686   0.09351  -0.2511   0.9087   0.0214
 -10.750   0.4977   0.09388   0.09048  -0.2551   0.9076   0.0215
 -10.500   0.5197   0.09135   0.08792  -0.2593   0.9064   0.0218
 -10.250   0.4952   0.09213   0.08877  -0.2495   0.8995   0.0220
 -10.000   0.5087   0.09018   0.08680  -0.2513   0.8971   0.0223
  -9.750   0.5272   0.08791   0.08451  -0.2545   0.8953   0.0228
  -9.500   0.5474   0.08549   0.08205  -0.2582   0.8937   0.0236
  -9.250   0.5689   0.08307   0.07958  -0.2623   0.8921   0.0240
  -9.000   0.5512   0.08326   0.07982  -0.2547   0.8863   0.0241
  -8.750   0.5564   0.08201   0.07857  -0.2541   0.8827   0.0242
  -8.500   0.5728   0.06388   0.06058  -0.2414   0.8666   0.0244
  -8.250   0.5879   0.06160   0.05827  -0.2431   0.8646   0.0247
  -8.000   0.6049   0.05939   0.05603  -0.2456   0.8628   0.0252
  -7.750   0.6226   0.05720   0.05380  -0.2483   0.8608   0.0257
  -7.500   0.5948   0.05821   0.05490  -0.2379   0.8542   0.0257
  -7.250   0.6017   0.05666   0.05335  -0.2375   0.8511   0.0263
  -7.000   0.6157   0.05460   0.05125  -0.2392   0.8488   0.0270
  -6.750   0.6325   0.05253   0.04914  -0.2417   0.8467   0.0272
  -6.500   0.6050   0.05343   0.05012  -0.2317   0.8405   0.0272
  -6.250   0.5934   0.05324   0.04995  -0.2264   0.8358   0.0273
  -5.250   0.5590   0.05090   0.04768  -0.2084   0.8188   0.0275
  -5.000   0.5782   0.04842   0.04517  -0.2108   0.8171   0.0277
  -4.750   0.6022   0.04607   0.04278  -0.2146   0.8155   0.0281
  -4.500   0.5348   0.04919   0.04604  -0.1948   0.8057   0.0279
  -4.250   0.5484   0.04739   0.04422  -0.1960   0.8032   0.0283
  -4.000   0.5698   0.04518   0.04198  -0.1991   0.8015   0.0289
  -3.750   0.5955   0.04282   0.03957  -0.2033   0.8001   0.0296
  -3.500   0.5362   0.04551   0.04240  -0.1861   0.7904   0.0292
  -3.250   0.5525   0.04363   0.04049  -0.1879   0.7879   0.0299
  -3.000   0.5809   0.04134   0.03816  -0.1930   0.7863   0.0304
  -2.250   0.6708   0.05320   0.04978  -0.2193   0.7893   0.0306
  -2.000   0.6862   0.05073   0.04729  -0.2194   0.7874   0.0308
  -1.750   0.7179   0.04858   0.04511  -0.2237   0.7859   0.0311
  -1.500   0.7580   0.04642   0.04290  -0.2300   0.7847   0.0317
  -1.250   0.8042   0.04417   0.04059  -0.2377   0.7834   0.0326
  -1.000   0.7669   0.04504   0.04157  -0.2256   0.7755   0.0325
  -0.750   0.8111   0.04320   0.03967  -0.2327   0.7735   0.0336
   0.000   0.9537   0.03662   0.03293  -0.2552   0.7694   0.0343
   0.250   1.0021   0.03483   0.03108  -0.2623   0.7681   0.0350
   0.500   1.0608   0.03297   0.02915  -0.2717   0.7670   0.0365
   0.750   1.0701   0.03293   0.02914  -0.2698   0.7621   0.0372
   1.000   1.1314   0.03147   0.02759  -0.2797   0.7592   0.0374
   1.250   1.1552   0.02983   0.02595  -0.2806   0.7556   0.0377
   1.500   1.2130   0.02777   0.02375  -0.2888   0.7505   0.0385
   1.750   1.2095   0.02796   0.02400  -0.2836   0.7443   0.0390
   2.000   1.2433   0.02708   0.02306  -0.2864   0.7385   0.0403
   2.500   1.3214   0.02539   0.02123  -0.2940   0.7269   0.0418
   2.750   1.3459   0.02462   0.02040  -0.2945   0.7195   0.0424
   3.000   1.3570   0.02458   0.02038  -0.2921   0.7112   0.0431
   3.250   1.3821   0.02414   0.01983  -0.2925   0.7003   0.0443
   3.500   1.4170   0.02432   0.01986  -0.2944   0.6879   0.0461
   3.750   1.4174   0.02430   0.01980  -0.2900   0.6710   0.0464
   4.000   1.4114   0.02504   0.02042  -0.2842   0.6439   0.0466
   4.250   1.3992   0.02630   0.02150  -0.2774   0.6079   0.0469
   4.500   1.3802   0.02828   0.02322  -0.2696   0.5636   0.0470
   4.750   1.3548   0.03096   0.02560  -0.2611   0.5093   0.0471
   5.000   1.3259   0.03427   0.02856  -0.2525   0.4453   0.0471
   5.250   1.2991   0.03781   0.03171  -0.2448   0.3706   0.0472
   5.500   1.2710   0.04178   0.03522  -0.2373   0.2756   0.0472
   5.750   1.2425   0.04615   0.03907  -0.2303   0.1482   0.0472
   6.000   1.2341   0.04911   0.04169  -0.2262   0.0370   0.0476
   6.250   1.2541   0.04989   0.04244  -0.2262   0.0337   0.0490
   6.500   1.2898   0.05057   0.04296  -0.2284   0.0317   0.0518
   6.750   1.3046   0.05127   0.04372  -0.2275   0.0310   0.0523
   7.000   1.3195   0.05222   0.04469  -0.2265   0.0301   0.0536
   7.250   1.3378   0.05326   0.04571  -0.2260   0.0292   0.0558
   7.500   1.3641   0.05415   0.04648  -0.2266   0.0285   0.0584
   7.750   1.3764   0.05538   0.04774  -0.2253   0.0280   0.0593
   8.000   1.3889   0.05680   0.04917  -0.2240   0.0275   0.0607
   8.250   1.4093   0.05812   0.05035  -0.2237   0.0272   0.0659
   8.500   1.4176   0.05984   0.05214  -0.2219   0.0268   0.0670
   8.750   1.4251   0.06185   0.05419  -0.2201   0.0265   0.0689
   9.000   1.4362   0.06393   0.05618  -0.2187   0.0263   0.0751
   9.250   1.4412   0.06617   0.05851  -0.2168   0.0261   0.0767
   9.500   1.4499   0.06816   0.06052  -0.2152   0.0260   0.0809
   9.750   1.4606   0.07013   0.06245  -0.2138   0.0259   0.0867
  10.000   1.4680   0.07225   0.06462  -0.2122   0.0258   0.0894
  10.250   1.4765   0.07444   0.06680  -0.2106   0.0257   0.0982
  10.500   1.4832   0.07668   0.06910  -0.2090   0.0256   0.1015
  10.750   1.4914   0.07884   0.07125  -0.2075   0.0256   0.1119
  11.000   1.4999   0.08090   0.07335  -0.2060   0.0254   0.1180
  11.250   1.5098   0.08280   0.07527  -0.2046   0.0251   0.1292
  11.500   1.5308   0.08413   0.07621  -0.2037   0.0249   0.0632
  11.750   1.5419   0.08585   0.07795  -0.2023   0.0248   0.0623
  12.000   1.5543   0.08734   0.07946  -0.2009   0.0248   0.0619
  12.250   1.5687   0.08851   0.08065  -0.1996   0.0248   0.0620
  12.500   1.5867   0.08918   0.08133  -0.1984   0.0250   0.0627
  12.750   1.6100   0.08916   0.08130  -0.1973   0.0251   0.0643
  13.000   1.6501   0.08723   0.07932  -0.1971   0.0256   0.0717
  13.250   1.6915   0.08521   0.07791  -0.1975   0.0268   1.0000
  18.000   1.5938   0.13400   0.13093  -0.1562   0.0249   1.0000
  18.250   1.5667   0.14013   0.13727  -0.1563   0.0249   1.0000
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