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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=9


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: 55.98 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-160-050-gn-1000000.txt
Download as CSV file: xf-cp-160-050-gn-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250   0.4381   0.10704   0.10446  -0.2563   0.9162   0.0156
 -13.000   0.4465   0.10513   0.10253  -0.2571   0.9134   0.0157
 -12.750   0.4594   0.10274   0.10012  -0.2594   0.9109   0.0158
 -12.500   0.4752   0.10015   0.09749  -0.2628   0.9087   0.0158
 -12.250   0.4936   0.09735   0.09465  -0.2665   0.9068   0.0160
 -12.000   0.4997   0.09601   0.09332  -0.2661   0.9039   0.0160
 -11.750   0.5050   0.09473   0.09204  -0.2653   0.9006   0.0163
 -11.500   0.5146   0.09324   0.09054  -0.2658   0.8976   0.0168
 -11.250   0.5286   0.09124   0.08850  -0.2679   0.8950   0.0172
 -11.000   0.5461   0.08883   0.08605  -0.2712   0.8926   0.0182
 -10.750   0.5566   0.08705   0.08426  -0.2721   0.8898   0.0183
 -10.500   0.5584   0.08571   0.08294  -0.2706   0.8862   0.0184
 -10.250   0.5646   0.08416   0.08137  -0.2706   0.8827   0.0185
 -10.000   0.5763   0.08214   0.07932  -0.2722   0.8797   0.0185
  -9.750   0.5939   0.07988   0.07702  -0.2747   0.8772   0.0187
  -9.500   0.6017   0.07867   0.07581  -0.2743   0.8743   0.0189
  -9.250   0.6048   0.07758   0.07474  -0.2727   0.8708   0.0190
  -9.000   0.6118   0.07638   0.07353  -0.2721   0.8674   0.0194
  -8.750   0.6240   0.07480   0.07192  -0.2731   0.8643   0.0198
  -8.500   0.6421   0.07287   0.06995  -0.2759   0.8614   0.0206
  -8.250   0.6422   0.07183   0.06894  -0.2734   0.8580   0.0210
  -8.000   0.6432   0.07069   0.06781  -0.2714   0.8542   0.0212
  -7.750   0.6481   0.06944   0.06654  -0.2706   0.8505   0.0213
  -7.500   0.6606   0.06795   0.06501  -0.2720   0.8470   0.0213
  -7.250   0.6658   0.06628   0.06335  -0.2709   0.8439   0.0214
  -7.000   0.6616   0.06557   0.06267  -0.2669   0.8402   0.0215
  -6.750   0.6572   0.06496   0.06207  -0.2628   0.8362   0.0216
  -6.500   0.6649   0.06389   0.06098  -0.2621   0.8327   0.0219
  -6.250   0.6784   0.06257   0.05963  -0.2631   0.8294   0.0223
  -6.000   0.6508   0.06299   0.06012  -0.2529   0.8247   0.0224
  -5.750   0.6451   0.06236   0.05951  -0.2486   0.8207   0.0227
  -5.500   0.6530   0.06111   0.05823  -0.2482   0.8172   0.0232
  -5.250   0.6693   0.05947   0.05655  -0.2501   0.8139   0.0240
  -5.000   0.6524   0.05926   0.05640  -0.2429   0.8097   0.0241
  -4.750   0.6477   0.05856   0.05572  -0.2394   0.8054   0.0242
  -4.500   0.6584   0.05724   0.05437  -0.2403   0.8018   0.0243
  -4.250   0.6793   0.05497   0.05205  -0.2431   0.7987   0.0244
  -4.000   0.6657   0.05454   0.05168  -0.2365   0.7948   0.0245
  -3.750   0.6655   0.05367   0.05083  -0.2335   0.7911   0.0245
  -3.500   0.6740   0.05261   0.04977  -0.2325   0.7879   0.0248
  -3.250   0.6926   0.05115   0.04828  -0.2342   0.7849   0.0251
  -3.000   0.7135   0.04965   0.04675  -0.2365   0.7818   0.0256
  -2.750   0.7088   0.04899   0.04614  -0.2322   0.7779   0.0260
  -2.500   0.7195   0.04776   0.04491  -0.2319   0.7744   0.0266
  -2.250   0.7434   0.04609   0.04321  -0.2349   0.7713   0.0272
  -2.000   0.7884   0.04392   0.04096  -0.2436   0.7687   0.0274
  -1.750   0.8108   0.04179   0.03880  -0.2456   0.7659   0.0275
  -1.500   0.8127   0.04094   0.03800  -0.2425   0.7624   0.0276
  -1.250   0.8297   0.03978   0.03685  -0.2430   0.7594   0.0278
  -1.000   0.8537   0.03852   0.03556  -0.2451   0.7564   0.0282
  -0.750   0.8861   0.03703   0.03404  -0.2490   0.7538   0.0288
  -0.500   0.9297   0.03524   0.03218  -0.2556   0.7513   0.0301
  -0.250   0.9948   0.03324   0.03010  -0.2675   0.7490   0.0305
   0.000   1.0090   0.03210   0.02898  -0.2670   0.7431   0.0306
   0.250   1.0266   0.03083   0.02769  -0.2669   0.7393   0.0308
   0.500   1.0552   0.02975   0.02655  -0.2692   0.7335   0.0310
   0.750   1.0804   0.02893   0.02574  -0.2708   0.7303   0.0315
   1.000   1.1088   0.02808   0.02488  -0.2729   0.7253   0.0322
   1.250   1.1600   0.02690   0.02359  -0.2800   0.7206   0.0336
   1.500   1.2169   0.02575   0.02234  -0.2884   0.7154   0.0338
   1.750   1.2421   0.02465   0.02123  -0.2896   0.7092   0.0339
   2.000   1.2615   0.02408   0.02060  -0.2893   0.7023   0.0341
   2.250   1.2813   0.02371   0.02024  -0.2891   0.6939   0.0344
   2.500   1.2978   0.02359   0.02005  -0.2880   0.6823   0.0348
   2.750   1.3120   0.02362   0.01999  -0.2865   0.6661   0.0354
   3.000   1.3274   0.02371   0.01997  -0.2851   0.6486   0.0365
   3.250   1.3376   0.02465   0.02064  -0.2825   0.6101   0.0373
   3.500   1.3221   0.02634   0.02206  -0.2752   0.5636   0.0373
   3.750   1.3096   0.02814   0.02358  -0.2687   0.5137   0.0373
   4.000   1.2723   0.03152   0.02649  -0.2581   0.4288   0.0373
   4.250   1.2494   0.03442   0.02897  -0.2505   0.3479   0.0373
   4.500   1.2193   0.03805   0.03211  -0.2422   0.2415   0.0373
   4.750   1.1891   0.04206   0.03558  -0.2343   0.0857   0.0373
   5.000   1.2035   0.04315   0.03647  -0.2335   0.0260   0.0374
   5.250   1.2229   0.04315   0.03647  -0.2336   0.0244   0.0378
   5.500   1.2431   0.04355   0.03685  -0.2334   0.0234   0.0381
   5.750   1.2639   0.04408   0.03736  -0.2334   0.0226   0.0387
   6.000   1.2849   0.04472   0.03798  -0.2334   0.0217   0.0397
   6.250   1.3252   0.04481   0.03790  -0.2363   0.0212   0.0417
   6.500   1.3412   0.04550   0.03860  -0.2354   0.0211   0.0420
   6.750   1.3582   0.04626   0.03935  -0.2346   0.0209   0.0424
   7.000   1.3745   0.04719   0.04028  -0.2337   0.0208   0.0431
   7.250   1.3932   0.04806   0.04112  -0.2330   0.0206   0.0447
   7.500   1.4236   0.04839   0.04126  -0.2340   0.0204   0.0467
   7.750   1.4370   0.04951   0.04240  -0.2326   0.0203   0.0472
   8.000   1.4507   0.05070   0.04360  -0.2312   0.0201   0.0480
   8.250   1.4727   0.05150   0.04419  -0.2308   0.0199   0.0521
   8.500   1.4841   0.05288   0.04561  -0.2291   0.0197   0.0527
   8.750   1.4959   0.05427   0.04702  -0.2275   0.0195   0.0536
   9.000   1.5066   0.05587   0.04861  -0.2258   0.0193   0.0555
   9.250   1.5191   0.05735   0.05002  -0.2243   0.0191   0.0591
   9.500   1.5289   0.05901   0.05171  -0.2226   0.0189   0.0602
   9.750   1.5371   0.06092   0.05363  -0.2207   0.0188   0.0623
  10.000   1.5430   0.06311   0.05582  -0.2184   0.0186   0.0650
  10.250   1.5598   0.06427   0.05679  -0.2175   0.0183   0.0504
  10.500   1.5679   0.06625   0.05878  -0.2157   0.0181   0.0500
  10.750   1.5742   0.06847   0.06102  -0.2139   0.0179   0.0496
  11.000   1.5796   0.07081   0.06340  -0.2119   0.0177   0.0497
  11.250   1.5836   0.07338   0.06601  -0.2100   0.0176   0.0500
  11.500   1.5895   0.07570   0.06839  -0.2082   0.0175   0.0502
  11.750   1.5938   0.07823   0.07096  -0.2063   0.0174   0.0501
  12.000   1.6002   0.08053   0.07330  -0.2046   0.0174   0.0500
  12.250   1.6077   0.08265   0.07544  -0.2030   0.0173   0.0501
  12.500   1.6178   0.08441   0.07724  -0.2015   0.0173   0.0504
  12.750   1.6297   0.08588   0.07873  -0.2001   0.0172   0.0508
  13.000   1.6449   0.08688   0.07974  -0.1988   0.0172   0.0522
  13.250   1.6647   0.08723   0.08009  -0.1977   0.0172   0.0568
  13.500   1.6896   0.08709   0.08013  -0.1971   0.0172   0.2515
  13.750   1.7208   0.08603   0.07968  -0.1970   0.0171   1.0000
  14.000   1.7664   0.08358   0.07716  -0.1973   0.0171   1.0000
  14.250   1.8050   0.08249   0.07612  -0.1976   0.0168   1.0000
  14.500   1.8113   0.08447   0.07820  -0.1959   0.0167   1.0000
  17.000   1.9956   0.09860   0.09373  -0.1870   0.0159   1.0000
  17.250   1.9933   0.10138   0.09668  -0.1850   0.0154   1.0000
  17.500   1.9895   0.10431   0.09976  -0.1831   0.0151   1.0000
  17.750   1.9848   0.10726   0.10286  -0.1814   0.0149   1.0000
  18.000   1.9789   0.11031   0.10604  -0.1797   0.0147   1.0000
  18.250   1.9725   0.11343   0.10929  -0.1782   0.0146   1.0000
  18.500   1.9651   0.11660   0.11260  -0.1769   0.0144   1.0000
  18.750   1.9571   0.11987   0.11599  -0.1757   0.0143   1.0000
  19.000   1.9483   0.12329   0.11954  -0.1746   0.0143   1.0000
  19.250   1.9393   0.12666   0.12302  -0.1738   0.0142   1.0000
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