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Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 47.54 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-180-050-gn-1000000-n5.txt
Download as CSV file: xf-cp-180-050-gn-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750   0.5192   0.10767   0.10471  -0.2713   0.8647   0.0089
 -13.500   0.5250   0.10586   0.10292  -0.2713   0.8622   0.0091
 -13.250   0.5309   0.10399   0.10104  -0.2714   0.8593   0.0101
 -13.000   0.5378   0.10223   0.09926  -0.2717   0.8564   0.0096
 -12.750   0.5482   0.10109   0.09811  -0.2725   0.8538   0.0118
 -12.500   0.5561   0.09929   0.09627  -0.2731   0.8511   0.0106
 -12.250   0.5624   0.09757   0.09456  -0.2731   0.8488   0.0119
 -12.000   0.5665   0.09580   0.09279  -0.2726   0.8459   0.0102
 -11.750   0.5742   0.09474   0.09173  -0.2725   0.8429   0.0112
 -11.500   0.5792   0.09300   0.08997  -0.2722   0.8398   0.0107
 -11.250   0.5858   0.09147   0.08841  -0.2721   0.8369   0.0112
 -11.000   0.5914   0.08991   0.08685  -0.2718   0.8343   0.0113
 -10.750   0.5952   0.08849   0.08544  -0.2709   0.8315   0.0115
 -10.500   0.5992   0.08717   0.08412  -0.2700   0.8283   0.0111
 -10.250   0.6027   0.08577   0.08271  -0.2690   0.8250   0.0116
 -10.000   0.6076   0.08456   0.08149  -0.2682   0.8220   0.0125
  -9.750   0.6138   0.08368   0.08060  -0.2674   0.8193   0.0132
  -9.500   0.6138   0.08223   0.07916  -0.2655   0.8164   0.0127
  -9.250   0.6137   0.08133   0.07827  -0.2631   0.8128   0.0143
  -8.750   0.6141   0.07947   0.07640  -0.2587   0.8059   0.0138
  -8.500   0.6142   0.07837   0.07530  -0.2566   0.8030   0.0141
  -8.250   0.6135   0.07745   0.07440  -0.2542   0.7999   0.0137
  -7.750   0.6060   0.07587   0.07283  -0.2476   0.7922   0.0141
  -7.500   0.6042   0.07495   0.07190  -0.2450   0.7889   0.0140
  -7.250   0.6028   0.07438   0.07136  -0.2422   0.7861   0.0151
  -7.000   0.5873   0.07335   0.07036  -0.2367   0.7819   0.0145
  -6.750   0.5842   0.07305   0.07006  -0.2332   0.7780   0.0147
  -6.250   0.5750   0.07278   0.06981  -0.2256   0.7712   0.0167
  -6.000   0.5644   0.07227   0.06934  -0.2208   0.7676   0.0169
  -5.750   0.5615   0.07139   0.06847  -0.2179   0.7637   0.0169
  -5.500   0.5571   0.07060   0.06766  -0.2146   0.7598   0.0169
  -5.250   0.5568   0.06976   0.06683  -0.2123   0.7564   0.0161
  -5.000   0.5575   0.06866   0.06575  -0.2104   0.7534   0.0161
  -4.750   0.5575   0.06755   0.06466  -0.2083   0.7499   0.0159
  -4.500   0.5573   0.06657   0.06367  -0.2061   0.7461   0.0164
  -4.250   0.5610   0.06536   0.06244  -0.2049   0.7425   0.0165
  -4.000   0.5667   0.06406   0.06115  -0.2042   0.7395   0.0165
  -3.750   0.5721   0.06231   0.05942  -0.2038   0.7364   0.0173
  -3.500   0.5778   0.06149   0.05861  -0.2027   0.7330   0.0175
  -3.250   0.5886   0.05928   0.05637  -0.2039   0.7296   0.0172
  -3.000   0.6006   0.05798   0.05504  -0.2043   0.7263   0.0173
  -2.750   0.6127   0.05731   0.05438  -0.2042   0.7236   0.0177
  -2.500   0.6264   0.05603   0.05311  -0.2050   0.7207   0.0180
  -2.250   0.6418   0.05455   0.05163  -0.2063   0.7178   0.0181
  -2.000   0.6603   0.05311   0.05017  -0.2082   0.7147   0.0186
  -1.750   0.6823   0.05146   0.04848  -0.2109   0.7116   0.0188
  -1.500   0.7074   0.04975   0.04673  -0.2143   0.7088   0.0189
  -0.750   0.7925   0.04516   0.04211  -0.2257   0.7017   0.0211
  -0.500   0.8248   0.04361   0.04053  -0.2303   0.6988   0.0218
  -0.250   0.8614   0.04195   0.03883  -0.2357   0.6961   0.0222
   0.000   0.9003   0.04032   0.03714  -0.2416   0.6936   0.0221
   0.250   0.9369   0.03903   0.03583  -0.2466   0.6915   0.0236
   0.500   0.9831   0.03729   0.03406  -0.2538   0.6897   0.0236
   0.750   1.0239   0.03600   0.03275  -0.2595   0.6874   0.0242
   1.000   1.0685   0.03461   0.03131  -0.2660   0.6848   0.0245
   1.250   1.1089   0.03349   0.03013  -0.2715   0.6798   0.0248
   1.750   1.1838   0.03179   0.02833  -0.2806   0.6671   0.0266
   2.000   1.2197   0.03110   0.02758  -0.2846   0.6616   0.0268
   2.250   1.2628   0.03033   0.02675  -0.2900   0.6570   0.0287
   2.500   1.2935   0.02987   0.02626  -0.2927   0.6502   0.0282
   2.750   1.3384   0.02931   0.02558  -0.2985   0.6413   0.0288
   3.000   1.3631   0.02908   0.02531  -0.2997   0.6324   0.0286
   3.250   1.3860   0.02923   0.02538  -0.3005   0.6194   0.0286
   3.500   1.4062   0.02958   0.02564  -0.3008   0.6077   0.0293
   3.750   1.4131   0.03053   0.02649  -0.2983   0.5865   0.0298
   4.000   1.4219   0.03159   0.02744  -0.2963   0.5655   0.0299
   4.250   1.4270   0.03290   0.02860  -0.2936   0.5425   0.0304
   4.500   1.4139   0.03538   0.03086  -0.2878   0.5000   0.0310
   4.750   1.3813   0.03926   0.03439  -0.2788   0.4353   0.0306
   5.000   1.3672   0.04226   0.03711  -0.2734   0.3828   0.0307
   5.250   1.3353   0.04666   0.04110  -0.2653   0.3014   0.0309
   5.500   1.3056   0.05123   0.04526  -0.2580   0.2046   0.0309
   5.750   1.2790   0.05598   0.04954  -0.2516   0.0599   0.0306
   6.000   1.2990   0.05731   0.05073  -0.2523   0.0173   0.0310
   6.250   1.3278   0.05814   0.05150  -0.2542   0.0153   0.0314
   6.500   1.3553   0.05897   0.05229  -0.2558   0.0144   0.0312
   6.750   1.3904   0.05973   0.05295  -0.2587   0.0140   0.0323
   7.000   1.4072   0.06075   0.05397  -0.2583   0.0137   0.0327
   7.250   1.4281   0.06176   0.05496  -0.2585   0.0135   0.0333
   7.500   1.4507   0.06287   0.05603  -0.2590   0.0133   0.0335
   7.750   1.4726   0.06408   0.05721  -0.2594   0.0131   0.0344
   8.000   1.4970   0.06521   0.05827  -0.2602   0.0128   0.0337
   8.250   1.5221   0.06632   0.05930  -0.2610   0.0126   0.0339
   8.500   1.5492   0.06739   0.06025  -0.2620   0.0124   0.0346
   8.750   1.5879   0.06796   0.06041  -0.2647   0.0123   0.0353
   9.000   1.6039   0.06938   0.06169  -0.2640   0.0121   0.0357
   9.250   1.6156   0.07106   0.06335  -0.2626   0.0120   0.0360
   9.500   1.6270   0.07272   0.06501  -0.2611   0.0119   0.0363
   9.750   1.6380   0.07442   0.06671  -0.2596   0.0118   0.0366
  10.000   1.6471   0.07638   0.06869  -0.2580   0.0117   0.0369
  10.250   1.6563   0.07834   0.07066  -0.2564   0.0115   0.0371
  10.500   1.6653   0.08032   0.07267  -0.2549   0.0114   0.0373
  10.750   1.6725   0.08254   0.07492  -0.2532   0.0113   0.0376
  11.000   1.6782   0.08499   0.07744  -0.2514   0.0112   0.0380
  11.250   1.6860   0.08715   0.07964  -0.2498   0.0111   0.0383
  11.500   1.6941   0.08930   0.08182  -0.2483   0.0110   0.0383
  11.750   1.7011   0.09161   0.08418  -0.2468   0.0110   0.0384
  12.000   1.7094   0.09373   0.08635  -0.2454   0.0109   0.0385
  12.250   1.7165   0.09601   0.08868  -0.2440   0.0108   0.0386
  12.500   1.7223   0.09850   0.09123  -0.2425   0.0108   0.0388
  12.750   1.7288   0.10086   0.09365  -0.2411   0.0107   0.0391
  13.000   1.7350   0.10326   0.09610  -0.2397   0.0106   0.0393
  13.250   1.7404   0.10582   0.09871  -0.2384   0.0105   0.0402
  13.500   1.7469   0.10816   0.10111  -0.2372   0.0103   0.0414
  13.750   1.7534   0.11048   0.10349  -0.2359   0.0102   0.0431
  14.000   1.7581   0.11308   0.10615  -0.2347   0.0101   0.0462
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