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Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=100,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn)
Reynolds number: 100,000
Max Cl/Cd: 30.06 at α=8°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-080-050-gn-100000-n1.txt
Download as CSV file: xf-cp-080-050-gn-100000-n1.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=8% T=5% R=1.6                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1522   0.10724   0.10048  -0.0804   0.9065   0.0292
  -7.500  -0.1449   0.10490   0.09815  -0.0811   0.9018   0.0293
  -7.250  -0.1362   0.10234   0.09559  -0.0824   0.8976   0.0299
  -7.000  -0.1271   0.09950   0.09276  -0.0841   0.8939   0.0307
  -6.750  -0.1165   0.09718   0.09044  -0.0854   0.8903   0.0311
  -6.500  -0.1098   0.09509   0.08837  -0.0858   0.8848   0.0315
  -6.250  -0.1009   0.09279   0.08608  -0.0868   0.8799   0.0317
  -6.000  -0.0906   0.09036   0.08366  -0.0882   0.8758   0.0319
  -5.750  -0.0824   0.08811   0.08143  -0.0891   0.8711   0.0322
  -5.500  -0.0769   0.08608   0.07942  -0.0892   0.8649   0.0323
  -5.250  -0.0695   0.08381   0.07715  -0.0901   0.8596   0.0329
  -5.000  -0.0628   0.08142   0.07476  -0.0911   0.8545   0.0337
  -4.750  -0.0628   0.07967   0.07306  -0.0902   0.8469   0.0341
  -4.500  -0.0582   0.07781   0.07122  -0.0901   0.8408   0.0344
  -4.250  -0.0517   0.07574   0.06917  -0.0906   0.8351   0.0347
  -4.000  -0.0483   0.07388   0.06733  -0.0903   0.8278   0.0349
  -3.750  -0.0393   0.07170   0.06516  -0.0913   0.8221   0.0351
  -3.500  -0.0292   0.06951   0.06297  -0.0924   0.8169   0.0353
  -3.250  -0.0235   0.06755   0.06102  -0.0924   0.8098   0.0356
  -3.000  -0.0120   0.06518   0.05864  -0.0938   0.8040   0.0364
  -2.750   0.0026   0.06253   0.05595  -0.0959   0.7991   0.0373
  -2.500   0.0121   0.06069   0.05412  -0.0959   0.7925   0.0376
  -2.250   0.0274   0.05859   0.05201  -0.0970   0.7870   0.0379
  -2.000   0.0468   0.05633   0.04971  -0.0988   0.7824   0.0382
  -1.750   0.0623   0.05433   0.04768  -0.0995   0.7769   0.0384
  -1.500   0.0794   0.05232   0.04565  -0.1003   0.7711   0.0387
  -1.250   0.1014   0.05006   0.04333  -0.1021   0.7662   0.0396
  -1.000   0.1272   0.04749   0.04065  -0.1046   0.7623   0.0407
  -0.750   0.1455   0.04572   0.03885  -0.1048   0.7564   0.0411
  -0.500   0.1678   0.04394   0.03702  -0.1056   0.7512   0.0414
  -0.250   0.1933   0.04209   0.03511  -0.1069   0.7468   0.0417
   0.000   0.2202   0.04026   0.03320  -0.1082   0.7429   0.0420
   0.250   0.2422   0.03866   0.03153  -0.1084   0.7372   0.0429
   0.500   0.2704   0.03663   0.02936  -0.1097   0.7292   0.0441
   0.750   0.3057   0.03445   0.02694  -0.1117   0.7069   0.0447
   1.000   0.3626   0.03242   0.02385  -0.1171   0.5570   0.0451
   1.250   0.3430   0.03485   0.02424  -0.1092   0.1096   0.0452
   1.500   0.3624   0.03411   0.02315  -0.1082   0.0567   0.0456
   1.750   0.3861   0.03291   0.02177  -0.1077   0.0525   0.0467
   2.000   0.4106   0.03152   0.02015  -0.1072   0.0500   0.0479
   2.250   0.4344   0.03039   0.01882  -0.1065   0.0479   0.0484
   2.500   0.4577   0.02946   0.01774  -0.1057   0.0464   0.0487
   2.750   0.4805   0.02879   0.01693  -0.1046   0.0452   0.0490
   3.000   0.5030   0.02819   0.01619  -0.1035   0.0440   0.0496
   3.250   0.5261   0.02755   0.01537  -0.1024   0.0428   0.0507
   3.500   0.5495   0.02685   0.01446  -0.1012   0.0415   0.0519
   3.750   0.5719   0.02639   0.01384  -0.0999   0.0406   0.0522
   4.000   0.5940   0.02604   0.01334  -0.0986   0.0397   0.0525
   4.250   0.6157   0.02584   0.01304  -0.0972   0.0394   0.0528
   4.500   0.6367   0.02584   0.01300  -0.0957   0.0390   0.0534
   4.750   0.6574   0.02587   0.01298  -0.0941   0.0387   0.0542
   5.000   0.6780   0.02590   0.01297  -0.0925   0.0384   0.0551
   5.250   0.6985   0.02596   0.01299  -0.0909   0.0381   0.0558
   5.500   0.7189   0.02609   0.01309  -0.0894   0.0379   0.0560
   5.750   0.7384   0.02627   0.01327  -0.0876   0.0376   0.0562
   6.000   0.7571   0.02650   0.01349  -0.0858   0.0374   0.0565
   6.250   0.7753   0.02678   0.01379  -0.0839   0.0372   0.0568
   6.500   0.7944   0.02712   0.01411  -0.0822   0.0368   0.0571
   6.750   0.8134   0.02752   0.01452  -0.0805   0.0364   0.0574
   7.000   0.8317   0.02798   0.01500  -0.0787   0.0359   0.0581
   7.250   0.8498   0.02845   0.01548  -0.0770   0.0354   0.0590
   7.500   0.8678   0.02895   0.01598  -0.0752   0.0350   0.0599
   7.750   0.8856   0.02948   0.01650  -0.0734   0.0346   0.0609
   8.000   0.9032   0.03005   0.01706  -0.0717   0.0343   0.0613
   8.250   0.9207   0.03067   0.01768  -0.0699   0.0341   0.0617
   8.500   0.9383   0.03133   0.01836  -0.0682   0.0339   0.0621
   8.750   0.9563   0.03203   0.01909  -0.0666   0.0337   0.0625
   9.000   0.9746   0.03276   0.01985  -0.0650   0.0335   0.0630
   9.250   0.9934   0.03351   0.02063  -0.0635   0.0334   0.0640
   9.500   1.0128   0.03430   0.02144  -0.0621   0.0331   0.0656
   9.750   1.0327   0.03511   0.02229  -0.0608   0.0330   0.0675
  10.000   1.0532   0.03594   0.02318  -0.0596   0.0327   0.0692
  10.250   1.0741   0.03681   0.02409  -0.0584   0.0324   0.0710
  10.500   1.0951   0.03770   0.02505  -0.0573   0.0321   0.0741
  10.750   1.1159   0.03861   0.02604  -0.0562   0.0316   0.0779
  11.000   1.1361   0.03954   0.02706  -0.0550   0.0311   0.0844
  11.750   1.1984   0.04166   0.03067  -0.0526   0.0303   1.0000
  12.000   1.2154   0.04286   0.03192  -0.0512   0.0302   1.0000
  12.250   1.2319   0.04414   0.03328  -0.0497   0.0300   1.0000
  12.500   1.2493   0.04567   0.03495  -0.0483   0.0298   1.0000
  12.750   1.2651   0.04738   0.03683  -0.0469   0.0296   1.0000
  13.000   1.2789   0.04929   0.03893  -0.0453   0.0293   1.0000
  13.250   1.2897   0.05138   0.04127  -0.0434   0.0289   1.0000
  13.500   1.2972   0.05367   0.04380  -0.0414   0.0284   1.0000
  13.750   1.3013   0.05606   0.04642  -0.0392   0.0279   1.0000
  14.000   1.3021   0.05860   0.04920  -0.0370   0.0275   1.0000
  14.250   1.3001   0.06128   0.05212  -0.0347   0.0273   1.0000
  14.500   1.2954   0.06419   0.05526  -0.0326   0.0270   1.0000
  14.750   1.2877   0.06740   0.05871  -0.0306   0.0269   1.0000
  15.000   1.2770   0.07094   0.06249  -0.0289   0.0268   1.0000
  15.250   1.2633   0.07492   0.06671  -0.0276   0.0267   1.0000
  15.500   1.2459   0.07948   0.07152  -0.0269   0.0266   1.0000
  15.750   1.2253   0.08466   0.07695  -0.0270   0.0265   1.0000
  16.000   1.1987   0.09106   0.08363  -0.0282   0.0264   1.0000
  16.250   1.1652   0.09928   0.09214  -0.0312   0.0263   1.0000
  16.500   1.1129   0.11260   0.10582  -0.0389   0.0263   1.0000
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