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Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 47.68 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-140-050-gn-1000000.txt
Download as CSV file: xf-cp-140-050-gn-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=14% T=5% R=0.96                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.3353   0.10354   0.10106  -0.2275   0.9345   0.0192
 -11.750   0.3401   0.10157   0.09909  -0.2274   0.9308   0.0193
 -11.500   0.3471   0.09951   0.09701  -0.2283   0.9272   0.0194
 -11.250   0.3599   0.09703   0.09452  -0.2298   0.9247   0.0195
 -11.000   0.3773   0.09475   0.09221  -0.2328   0.9225   0.0196
 -10.750   0.3977   0.09245   0.08988  -0.2365   0.9204   0.0199
 -10.500   0.4103   0.09065   0.08807  -0.2380   0.9174   0.0202
 -10.250   0.4160   0.08924   0.08666  -0.2373   0.9136   0.0206
 -10.000   0.4267   0.08738   0.08479  -0.2382   0.9102   0.0215
  -9.750   0.4423   0.08497   0.08234  -0.2409   0.9072   0.0220
  -9.500   0.4618   0.08238   0.07969  -0.2454   0.9041   0.0222
  -9.000   0.4709   0.07915   0.07648  -0.2432   0.8964   0.0223
  -8.750   0.4838   0.07744   0.07475  -0.2443   0.8933   0.0225
  -8.500   0.5017   0.07569   0.07296  -0.2466   0.8902   0.0228
  -8.250   0.5126   0.07418   0.07144  -0.2472   0.8867   0.0230
  -8.000   0.5182   0.07300   0.07027  -0.2461   0.8828   0.0236
  -7.750   0.5272   0.07155   0.06881  -0.2460   0.8790   0.0238
  -7.500   0.5405   0.06957   0.06679  -0.2477   0.8752   0.0250
  -7.250   0.5493   0.06808   0.06528  -0.2482   0.8712   0.0251
  -7.000   0.5507   0.06703   0.06425  -0.2465   0.8667   0.0251
  -6.750   0.5558   0.06543   0.06264  -0.2457   0.8625   0.0252
  -6.500   0.5697   0.06360   0.06079  -0.2464   0.8593   0.0253
  -6.250   0.5791   0.06233   0.05951  -0.2459   0.8557   0.0255
  -6.000   0.5789   0.06154   0.05875  -0.2430   0.8515   0.0257
  -5.750   0.5820   0.06061   0.05782  -0.2410   0.8474   0.0259
  -5.500   0.5943   0.05929   0.05647  -0.2416   0.8436   0.0265
  -5.250   0.6050   0.05796   0.05513  -0.2417   0.8399   0.0272
  -5.000   0.6072   0.05690   0.05409  -0.2397   0.8357   0.0279
  -4.750   0.6151   0.05563   0.05281  -0.2396   0.8315   0.0281
  -4.500   0.6325   0.05408   0.05122  -0.2423   0.8276   0.0282
  -4.250   0.6462   0.05237   0.04949  -0.2436   0.8239   0.0282
  -4.000   0.6479   0.05113   0.04829  -0.2406   0.8201   0.0283
  -3.750   0.6541   0.05000   0.04717  -0.2386   0.8164   0.0285
  -3.500   0.6691   0.04874   0.04589  -0.2390   0.8130   0.0288
  -3.250   0.6959   0.04715   0.04425  -0.2425   0.8096   0.0292
  -3.000   0.6902   0.04652   0.04366  -0.2376   0.8055   0.0295
  -2.750   0.6954   0.04549   0.04265  -0.2355   0.8015   0.0301
  -2.500   0.7139   0.04397   0.04111  -0.2369   0.7980   0.0310
  -2.250   0.7586   0.04185   0.03889  -0.2456   0.7948   0.0314
  -2.000   0.7790   0.03996   0.03699  -0.2473   0.7915   0.0315
  -1.750   0.7804   0.03885   0.03592  -0.2435   0.7876   0.0316
  -1.500   0.7926   0.03772   0.03479  -0.2424   0.7840   0.0318
  -1.250   0.8161   0.03643   0.03347  -0.2439   0.7798   0.0321
  -1.000   0.8408   0.03517   0.03218  -0.2457   0.7753   0.0326
  -0.750   0.8533   0.03414   0.03116  -0.2445   0.7706   0.0331
  -0.500   0.8823   0.03268   0.02966  -0.2472   0.7658   0.0344
  -0.250   0.9537   0.03039   0.02721  -0.2603   0.7623   0.0347
   0.000   0.9642   0.02890   0.02574  -0.2583   0.7577   0.0349
   0.250   0.9769   0.02796   0.02482  -0.2565   0.7520   0.0350
   0.500   0.9991   0.02703   0.02383  -0.2569   0.7459   0.0353
   0.750   1.0190   0.02620   0.02299  -0.2567   0.7389   0.0357
   1.000   1.0423   0.02534   0.02208  -0.2572   0.7309   0.0362
   1.250   1.0666   0.02448   0.02118  -0.2578   0.7226   0.0371
   2.750   1.1314   0.02373   0.01944  -0.2432   0.5579   0.0391
   3.000   1.1055   0.02574   0.02098  -0.2337   0.4704   0.0391
   3.250   1.0798   0.02806   0.02276  -0.2248   0.3668   0.0391
   3.500   1.0552   0.03061   0.02474  -0.2166   0.2421   0.0391
   3.750   1.0271   0.03368   0.02714  -0.2081   0.0391   0.0392
   4.000   1.0507   0.03357   0.02697  -0.2084   0.0312   0.0397
   4.250   1.0751   0.03347   0.02682  -0.2087   0.0283   0.0407
   4.750   1.1387   0.03248   0.02562  -0.2116   0.0263   0.0428
   5.000   1.1573   0.03269   0.02582  -0.2107   0.0256   0.0432
   5.250   1.1773   0.03289   0.02599  -0.2100   0.0251   0.0438
   5.500   1.1978   0.03309   0.02615  -0.2094   0.0244   0.0448
   6.250   1.2618   0.03361   0.02645  -0.2074   0.0234   0.0483
   6.500   1.2771   0.03427   0.02709  -0.2058   0.0230   0.0492
   6.750   1.2976   0.03451   0.02711  -0.2046   0.0227   0.0527
   7.000   1.3093   0.03549   0.02811  -0.2026   0.0226   0.0532
   7.250   1.3227   0.03637   0.02901  -0.2008   0.0225   0.0538
   7.500   1.3348   0.03740   0.03003  -0.1988   0.0225   0.0551
   7.750   1.3483   0.03860   0.03110  -0.1967   0.0224   0.0581
   9.250   1.4190   0.04539   0.03767  -0.1851   0.0220   0.0522
   9.500   1.4300   0.04672   0.03902  -0.1832   0.0219   0.0520
   9.750   1.4398   0.04822   0.04054  -0.1812   0.0217   0.0522
  10.000   1.4488   0.04980   0.04215  -0.1792   0.0217   0.0522
  10.250   1.4584   0.05135   0.04374  -0.1773   0.0216   0.0520
  10.500   1.4693   0.05279   0.04522  -0.1755   0.0214   0.0521
  10.750   1.4800   0.05428   0.04674  -0.1737   0.0211   0.0521
  11.000   1.4920   0.05562   0.04812  -0.1721   0.0207   0.0530
  11.250   1.5038   0.05703   0.04957  -0.1705   0.0206   0.0540
  11.500   1.5163   0.05838   0.05096  -0.1689   0.0205   0.0546
  11.750   1.5301   0.05961   0.05222  -0.1675   0.0203   0.0557
  12.000   1.5452   0.06072   0.05336  -0.1661   0.0202   0.0572
  12.250   1.5629   0.06160   0.05427  -0.1649   0.0202   0.0591
  12.500   1.5836   0.06223   0.05494  -0.1639   0.0202   0.0645
  12.750   1.6166   0.06207   0.05577  -0.1649   0.0201   1.0000
  13.000   1.6512   0.06158   0.05528  -0.1647   0.0204   1.0000
  13.250   1.7108   0.06006   0.05378  -0.1666   0.0210   1.0000
  13.500   1.9264   0.06060   0.05425  -0.1881   0.0224   1.0000
  13.750   1.9097   0.06183   0.05564  -0.1822   0.0223   1.0000
  14.000   1.8774   0.06270   0.05668  -0.1747   0.0219   1.0000
  14.250   1.8697   0.06439   0.05856  -0.1705   0.0213   1.0000
  14.500   1.8766   0.06632   0.06062  -0.1682   0.0207   1.0000
  14.750   1.8845   0.06837   0.06280  -0.1662   0.0203   1.0000
  15.000   1.8910   0.07048   0.06501  -0.1642   0.0200   1.0000
  15.250   1.8963   0.07264   0.06727  -0.1621   0.0197   1.0000
  15.500   1.8996   0.07494   0.06968  -0.1600   0.0195   1.0000
  15.750   1.9019   0.07729   0.07213  -0.1579   0.0194   1.0000
  16.000   1.9035   0.07973   0.07467  -0.1558   0.0192   1.0000
  16.250   1.9052   0.08215   0.07718  -0.1539   0.0191   1.0000
  16.500   1.9100   0.08443   0.07952  -0.1524   0.0190   1.0000
  16.750   1.9186   0.08665   0.08177  -0.1512   0.0188   1.0000
  17.000   1.9016   0.09810   0.09366  -0.1495   0.0183   1.0000
  17.250   1.8831   0.10189   0.09764  -0.1467   0.0183   1.0000
  17.500   1.8646   0.10575   0.10169  -0.1442   0.0183   1.0000
  17.750   1.8450   0.10980   0.10592  -0.1421   0.0182   1.0000
  18.000   1.8244   0.11401   0.11031  -0.1403   0.0182   1.0000
  18.250   1.8040   0.11838   0.11486  -0.1390   0.0182   1.0000
  18.500   1.7825   0.12294   0.11960  -0.1380   0.0182   1.0000
  18.750   1.7613   0.12772   0.12455  -0.1376   0.0182   1.0000
  19.000   1.7389   0.13278   0.12979  -0.1376   0.0182   1.0000
  19.250   1.7172   0.13805   0.13523  -0.1382   0.0181   1.0000
  19.500   1.6783   0.14605   0.14364  -0.1395   0.0169   1.0000
  19.750   1.6554   0.15282   0.15057  -0.1418   0.0167   1.0000
  20.000   1.6321   0.16008   0.15798  -0.1447   0.0166   1.0000
  20.250   1.6069   0.16821   0.16626  -0.1487   0.0166   1.0000
  20.500   1.5789   0.17764   0.17585  -0.1541   0.0166   1.0000
  20.750   1.5465   0.18932   0.18769  -0.1616   0.0166   1.0000
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