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RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il)
Reynolds number: 100,000
Max Cl/Cd: 40.2 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5212-il-100000-n5.txt
Download as CSV file: xf-rae5212-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE(NPL) 5212 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5135   0.09284   0.08728  -0.0459   1.0000   0.0325
 -10.750  -0.5277   0.08495   0.07942  -0.0501   1.0000   0.0320
 -10.500  -0.5536   0.07603   0.07049  -0.0556   1.0000   0.0315
 -10.250  -0.5829   0.06915   0.06354  -0.0593   1.0000   0.0310
 -10.000  -0.6128   0.06402   0.05833  -0.0607   1.0000   0.0306
  -9.750  -0.6429   0.06045   0.05468  -0.0594   1.0000   0.0305
  -9.500  -0.6689   0.05746   0.05157  -0.0565   1.0000   0.0303
  -9.250  -0.6872   0.05422   0.04815  -0.0538   1.0000   0.0302
  -9.000  -0.6995   0.05115   0.04485  -0.0511   1.0000   0.0303
  -8.750  -0.7070   0.04813   0.04158  -0.0485   1.0000   0.0304
  -8.500  -0.7101   0.04524   0.03840  -0.0460   1.0000   0.0306
  -8.250  -0.7092   0.04256   0.03540  -0.0436   1.0000   0.0311
  -8.000  -0.7052   0.04006   0.03254  -0.0413   1.0000   0.0320
  -7.750  -0.6990   0.03748   0.02947  -0.0391   1.0000   0.0331
  -7.500  -0.6887   0.03525   0.02688  -0.0372   1.0000   0.0339
  -7.250  -0.6749   0.03364   0.02515  -0.0356   1.0000   0.0346
  -7.000  -0.6558   0.03203   0.02336  -0.0350   0.9990   0.0354
  -6.750  -0.6257   0.03030   0.02140  -0.0362   0.9954   0.0365
  -6.500  -0.5958   0.02875   0.01959  -0.0372   0.9918   0.0383
  -6.250  -0.5657   0.02737   0.01794  -0.0380   0.9880   0.0406
  -6.000  -0.5349   0.02625   0.01682  -0.0393   0.9846   0.0427
  -5.750  -0.5058   0.02517   0.01566  -0.0399   0.9805   0.0447
  -5.500  -0.4755   0.02427   0.01459  -0.0406   0.9761   0.0478
  -5.250  -0.4447   0.02330   0.01372  -0.0418   0.9727   0.0511
  -5.000  -0.4183   0.02251   0.01290  -0.0419   0.9675   0.0545
  -4.750  -0.3892   0.02174   0.01210  -0.0426   0.9628   0.0590
  -4.500  -0.3569   0.02106   0.01142  -0.0439   0.9592   0.0656
  -4.250  -0.3329   0.02039   0.01075  -0.0436   0.9527   0.0725
  -4.000  -0.3029   0.01974   0.01013  -0.0445   0.9482   0.0850
  -3.750  -0.2710   0.01904   0.00953  -0.0459   0.9446   0.1102
  -3.500  -0.2492   0.01804   0.00896  -0.0456   0.9376   0.1853
  -3.250  -0.2270   0.01649   0.00889  -0.0456   0.9330   0.4688
  -3.000  -0.1990   0.01665   0.00920  -0.0452   0.9280   0.5610
  -2.750  -0.1728   0.01687   0.00937  -0.0446   0.9215   0.6021
  -2.500  -0.1425   0.01727   0.00979  -0.0442   0.9173   0.6398
  -2.250  -0.1192   0.01768   0.01024  -0.0424   0.9112   0.6720
  -2.000  -0.0925   0.01784   0.01038  -0.0416   0.9056   0.6905
  -1.750  -0.0578   0.01776   0.01016  -0.0430   0.9021   0.6987
  -1.500  -0.0296   0.01770   0.01003  -0.0431   0.8965   0.7036
  -1.250  -0.0007   0.01763   0.00990  -0.0433   0.8908   0.7089
  -1.000   0.0347   0.01752   0.00969  -0.0449   0.8871   0.7149
  -0.750   0.0718   0.01740   0.00952  -0.0466   0.8845   0.7194
  -0.500   0.0928   0.01742   0.00952  -0.0454   0.8758   0.7243
  -0.250   0.1276   0.01732   0.00938  -0.0468   0.8717   0.7299
   0.000   0.1651   0.01719   0.00923  -0.0486   0.8687   0.7345
   0.250   0.1872   0.01723   0.00928  -0.0475   0.8600   0.7392
   0.500   0.2225   0.01710   0.00915  -0.0489   0.8551   0.7444
   0.750   0.2548   0.01700   0.00905  -0.0497   0.8485   0.7496
   1.000   0.2846   0.01689   0.00898  -0.0498   0.8406   0.7542
   1.250   0.3234   0.01665   0.00876  -0.0515   0.8355   0.7594
   1.500   0.3500   0.01655   0.00869  -0.0511   0.8237   0.7652
   1.750   0.3809   0.01630   0.00849  -0.0510   0.8117   0.7699
   2.000   0.4146   0.01600   0.00823  -0.0515   0.7989   0.7754
   2.250   0.4449   0.01566   0.00789  -0.0512   0.7785   0.7814
   2.500   0.4760   0.01523   0.00745  -0.0506   0.7503   0.7865
   2.750   0.5040   0.01498   0.00715  -0.0498   0.7175   0.7926
   3.000   0.5305   0.01486   0.00699  -0.0489   0.6851   0.7989
   3.250   0.5556   0.01481   0.00694  -0.0479   0.6503   0.8057
   3.500   0.5808   0.01483   0.00685  -0.0469   0.5989   0.8133
   3.750   0.6038   0.01502   0.00671  -0.0454   0.5199   0.8202
   4.250   0.6359   0.01632   0.00712  -0.0408   0.3428   0.8394
   4.500   0.6511   0.01709   0.00752  -0.0387   0.2697   0.8518
   4.750   0.6685   0.01780   0.00796  -0.0371   0.2135   0.8672
   5.000   0.6885   0.01846   0.00845  -0.0360   0.1754   0.8880
   5.250   0.7155   0.01908   0.00900  -0.0362   0.1513   0.9223
   5.500   0.7436   0.01972   0.00957  -0.0369   0.1378   1.0000
   6.000   0.7865   0.02107   0.01080  -0.0354   0.1227   1.0000
   6.250   0.8075   0.02177   0.01143  -0.0346   0.1169   1.0000
   6.500   0.8287   0.02251   0.01213  -0.0338   0.1124   1.0000
   6.750   0.8508   0.02321   0.01287  -0.0330   0.1084   1.0000
   7.000   0.8728   0.02396   0.01360  -0.0323   0.1049   1.0000
   7.250   0.8944   0.02482   0.01440  -0.0316   0.1017   1.0000
   7.500   0.9176   0.02567   0.01528  -0.0311   0.0988   1.0000
   7.750   0.9411   0.02648   0.01618  -0.0307   0.0958   1.0000
   8.000   0.9649   0.02739   0.01713  -0.0303   0.0934   1.0000
   8.250   0.9885   0.02833   0.01810  -0.0299   0.0911   1.0000
   8.500   1.0122   0.02938   0.01912  -0.0296   0.0888   1.0000
   8.750   1.0365   0.03054   0.02034  -0.0294   0.0866   1.0000
   9.000   1.0592   0.03163   0.02162  -0.0289   0.0845   1.0000
   9.250   1.0819   0.03284   0.02301  -0.0284   0.0826   1.0000
   9.500   1.1039   0.03411   0.02443  -0.0278   0.0808   1.0000
   9.750   1.1248   0.03537   0.02579  -0.0272   0.0791   1.0000
  10.000   1.1453   0.03663   0.02711  -0.0266   0.0774   1.0000
  10.250   1.1678   0.03829   0.02876  -0.0265   0.0756   1.0000
  10.500   1.1817   0.03987   0.03067  -0.0248   0.0742   1.0000
  10.750   1.1943   0.04169   0.03283  -0.0232   0.0729   1.0000
  11.000   1.2044   0.04354   0.03498  -0.0213   0.0714   1.0000
  11.250   1.2129   0.04536   0.03706  -0.0193   0.0699   1.0000
  11.500   1.2195   0.04705   0.03897  -0.0172   0.0684   1.0000
  11.750   1.2250   0.04868   0.04075  -0.0149   0.0671   1.0000
  12.000   1.2304   0.05035   0.04255  -0.0128   0.0660   1.0000
  12.250   1.2385   0.05211   0.04437  -0.0113   0.0649   1.0000
  12.500   1.2368   0.05455   0.04699  -0.0090   0.0639   1.0000
  12.750   1.2182   0.05740   0.05021  -0.0055   0.0632   1.0000
  13.000   1.1971   0.06084   0.05400  -0.0028   0.0625   1.0000
  13.250   1.1736   0.06487   0.05834  -0.0012   0.0618   1.0000
  13.500   1.1467   0.06975   0.06351  -0.0007   0.0614   1.0000
  13.750   1.1138   0.07591   0.06995  -0.0017   0.0612   1.0000
  14.000   1.0709   0.08444   0.07874  -0.0053   0.0613   1.0000
  14.250   1.0041   0.09933   0.09389  -0.0146   0.0622   1.0000
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