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


Details Polar file
Airfoil: Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 48.91 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-160-050-gn-1000000-n5.txt
Download as CSV file: xf-cp-160-050-gn-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500   0.3972   0.10995   0.10716  -0.2456   0.8878   0.0103
 -13.250   0.4069   0.10833   0.10553  -0.2465   0.8851   0.0116
 -13.000   0.4123   0.10507   0.10225  -0.2474   0.8821   0.0110
 -12.750   0.4234   0.10298   0.10013  -0.2490   0.8792   0.0111
 -12.500   0.4368   0.10111   0.09822  -0.2510   0.8766   0.0112
 -12.250   0.4464   0.09980   0.09692  -0.2515   0.8741   0.0115
 -12.000   0.4554   0.09837   0.09548  -0.2520   0.8713   0.0119
 -11.750   0.4637   0.09651   0.09362  -0.2526   0.8681   0.0121
 -11.500   0.4733   0.09455   0.09163  -0.2535   0.8651   0.0129
 -11.250   0.4844   0.09266   0.08970  -0.2548   0.8620   0.0126
 -11.000   0.4939   0.09113   0.08818  -0.2554   0.8594   0.0139
 -10.750   0.4989   0.08912   0.08616  -0.2552   0.8564   0.0128
 -10.500   0.5043   0.08710   0.08413  -0.2551   0.8529   0.0134
 -10.250   0.5161   0.08624   0.08326  -0.2556   0.8498   0.0140
 -10.000   0.5236   0.08412   0.08111  -0.2561   0.8464   0.0137
  -9.750   0.5318   0.08292   0.07991  -0.2559   0.8436   0.0140
  -9.500   0.5381   0.08164   0.07863  -0.2553   0.8404   0.0145
  -9.250   0.5434   0.08009   0.07708  -0.2547   0.8370   0.0143
  -9.000   0.5502   0.07871   0.07568  -0.2543   0.8334   0.0147
  -8.750   0.5570   0.07723   0.07417  -0.2540   0.8299   0.0147
  -8.500   0.5608   0.07589   0.07285  -0.2528   0.8269   0.0148
  -8.250   0.5645   0.07462   0.07158  -0.2516   0.8234   0.0150
  -8.000   0.5675   0.07327   0.07023  -0.2502   0.8197   0.0152
  -7.750   0.5686   0.07168   0.06861  -0.2487   0.8159   0.0160
  -7.500   0.5739   0.07093   0.06787  -0.2473   0.8126   0.0162
  -7.250   0.5772   0.07015   0.06711  -0.2454   0.8093   0.0165
  -7.000   0.5765   0.06911   0.06609  -0.2429   0.8055   0.0165
  -6.750   0.5747   0.06823   0.06519  -0.2400   0.8015   0.0165
  -6.500   0.5713   0.06761   0.06457  -0.2365   0.7975   0.0168
  -6.250   0.5628   0.06721   0.06421  -0.2317   0.7937   0.0170
  -6.000   0.5552   0.06660   0.06361  -0.2273   0.7895   0.0171
  -5.750   0.5535   0.06564   0.06265  -0.2244   0.7855   0.0173
  -5.500   0.5516   0.06463   0.06164  -0.2216   0.7817   0.0173
  -5.250   0.5516   0.06363   0.06066  -0.2192   0.7781   0.0177
  -5.000   0.5519   0.06253   0.05958  -0.2170   0.7742   0.0177
  -4.750   0.5509   0.06120   0.05824  -0.2148   0.7701   0.0187
  -4.500   0.5567   0.06034   0.05736  -0.2134   0.7664   0.0189
  -4.250   0.5619   0.05928   0.05633  -0.2121   0.7633   0.0191
  -4.000   0.5660   0.05818   0.05524  -0.2106   0.7595   0.0192
  -3.750   0.5723   0.05691   0.05397  -0.2097   0.7559   0.0193
  -3.500   0.5822   0.05576   0.05280  -0.2094   0.7525   0.0199
  -3.250   0.5938   0.05426   0.05129  -0.2098   0.7493   0.0199
  -3.000   0.6046   0.05291   0.04995  -0.2098   0.7459   0.0203
  -2.750   0.6171   0.05142   0.04846  -0.2102   0.7424   0.0203
  -2.500   0.6377   0.04904   0.04604  -0.2133   0.7390   0.0212
  -2.250   0.6577   0.04737   0.04434  -0.2154   0.7357   0.0214
  -2.000   0.6742   0.04666   0.04363  -0.2156   0.7330   0.0219
  -1.750   0.6961   0.04514   0.04211  -0.2178   0.7300   0.0221
  -1.500   0.7182   0.04374   0.04070  -0.2199   0.7268   0.0224
  -1.250   0.7447   0.04214   0.03907  -0.2230   0.7238   0.0226
  -1.000   0.7735   0.04054   0.03744  -0.2265   0.7208   0.0230
  -0.750   0.8062   0.03883   0.03568  -0.2309   0.7179   0.0233
  -0.500   0.8601   0.03585   0.03264  -0.2408   0.7159   0.0243
  -0.250   0.8876   0.03486   0.03165  -0.2432   0.7133   0.0245
   0.000   0.9165   0.03392   0.03070  -0.2458   0.7098   0.0249
   0.250   0.9496   0.03278   0.02952  -0.2494   0.7057   0.0253
   0.500   0.9766   0.03192   0.02860  -0.2517   0.6960   0.0257
   0.750   1.0126   0.03078   0.02740  -0.2559   0.6900   0.0262
   1.000   1.0583   0.02925   0.02577  -0.2623   0.6850   0.0271
   1.250   1.0960   0.02822   0.02472  -0.2665   0.6801   0.0278
   1.500   1.1186   0.02790   0.02433  -0.2672   0.6700   0.0283
   1.750   1.1544   0.02704   0.02342  -0.2707   0.6637   0.0286
   2.000   1.1783   0.02667   0.02296  -0.2716   0.6511   0.0287
   2.250   1.2057   0.02624   0.02246  -0.2732   0.6390   0.0297
   2.500   1.2300   0.02595   0.02205  -0.2741   0.6225   0.0298
   2.750   1.2560   0.02568   0.02157  -0.2755   0.5979   0.0307
   3.000   1.2630   0.02625   0.02203  -0.2726   0.5743   0.0309
   3.250   1.2495   0.02797   0.02349  -0.2660   0.5266   0.0309
   3.500   1.2327   0.03010   0.02529  -0.2590   0.4671   0.0310
   3.750   1.2123   0.03266   0.02747  -0.2517   0.3949   0.0310
   4.000   1.1714   0.03674   0.03099  -0.2413   0.2757   0.0310
   4.250   1.1518   0.03987   0.03365  -0.2350   0.1596   0.0310
   4.500   1.1430   0.04238   0.03579  -0.2304   0.0249   0.0312
   4.750   1.1686   0.04261   0.03595  -0.2315   0.0194   0.0314
   5.000   1.1955   0.04279   0.03608  -0.2326   0.0178   0.0317
   5.250   1.2215   0.04304   0.03628  -0.2335   0.0170   0.0325
   5.500   1.2513   0.04314   0.03631  -0.2351   0.0167   0.0326
   5.750   1.2840   0.04317   0.03624  -0.2371   0.0164   0.0333
   6.000   1.3187   0.04311   0.03604  -0.2393   0.0161   0.0340
   6.250   1.3369   0.04382   0.03673  -0.2386   0.0160   0.0343
   6.500   1.3531   0.04463   0.03754  -0.2375   0.0156   0.0347
   6.750   1.3744   0.04522   0.03807  -0.2373   0.0153   0.0352
   7.000   1.4014   0.04551   0.03824  -0.2378   0.0151   0.0354
   7.250   1.4338   0.04536   0.03780  -0.2391   0.0150   0.0364
   7.750   1.4732   0.04656   0.03858  -0.2376   0.0147   0.0376
   8.000   1.4876   0.04762   0.03960  -0.2361   0.0145   0.0379
   8.250   1.5014   0.04875   0.04072  -0.2346   0.0144   0.0382
   8.500   1.5134   0.05008   0.04205  -0.2328   0.0142   0.0384
   8.750   1.5251   0.05145   0.04344  -0.2311   0.0141   0.0388
   9.000   1.5369   0.05281   0.04481  -0.2294   0.0140   0.0390
   9.250   1.5481   0.05428   0.04629  -0.2276   0.0138   0.0393
   9.500   1.5577   0.05594   0.04798  -0.2257   0.0137   0.0395
   9.750   1.5673   0.05761   0.04968  -0.2239   0.0136   0.0397
  10.000   1.5759   0.05943   0.05155  -0.2220   0.0134   0.0400
  10.250   1.5833   0.06141   0.05358  -0.2200   0.0133   0.0404
  10.500   1.5927   0.06316   0.05537  -0.2183   0.0133   0.0407
  10.750   1.6023   0.06491   0.05716  -0.2167   0.0132   0.0408
  11.000   1.6108   0.06683   0.05913  -0.2150   0.0131   0.0408
  11.250   1.6198   0.06869   0.06104  -0.2133   0.0130   0.0410
  11.500   1.6277   0.07072   0.06312  -0.2117   0.0130   0.0410
  11.750   1.6361   0.07271   0.06516  -0.2101   0.0128   0.0413
  12.000   1.6448   0.07467   0.06717  -0.2086   0.0127   0.0417
  12.250   1.6534   0.07666   0.06920  -0.2071   0.0125   0.0424
  12.500   1.6591   0.07904   0.07165  -0.2055   0.0124   0.0432
  12.750   1.6664   0.08122   0.07388  -0.2040   0.0123   0.0441
  13.000   1.6732   0.08347   0.07619  -0.2025   0.0122   0.0460
  13.250   1.6789   0.08591   0.07870  -0.2010   0.0121   0.0505
  13.500   1.6857   0.08820   0.08106  -0.1997   0.0120   0.0642
  13.750   1.6926   0.09048   0.08345  -0.1984   0.0119   0.1249
  14.000   1.6987   0.09290   0.08599  -0.1971   0.0118   0.1986
  14.250   1.7060   0.09515   0.08847  -0.1960   0.0117   0.4066
  14.750   1.7225   0.09932   0.09321  -0.1942   0.0115   1.0000
  15.000   1.7293   0.10153   0.09545  -0.1930   0.0114   1.0000
  15.250   1.7368   0.10359   0.09756  -0.1918   0.0113   1.0000
  15.500   1.7449   0.10555   0.09956  -0.1908   0.0113   1.0000
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