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BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il)
Reynolds number: 200,000
Max Cl/Cd: 70.35 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707d-il-200000.txt
Download as CSV file: xf-b707d-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .54 SPAN AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4581   0.08848   0.08502  -0.0381   1.0000   0.0311
  -8.500  -0.4663   0.08534   0.08187  -0.0395   1.0000   0.0311
  -8.250  -0.4691   0.08226   0.07874  -0.0405   1.0000   0.0312
  -8.000  -0.4709   0.07929   0.07571  -0.0408   1.0000   0.0313
  -7.750  -0.4711   0.07637   0.07272  -0.0405   1.0000   0.0314
  -7.500  -0.4716   0.07354   0.06978  -0.0396   1.0000   0.0314
  -7.250  -0.4795   0.06616   0.06248  -0.0391   1.0000   0.0322
  -7.000  -0.4790   0.06245   0.05883  -0.0374   1.0000   0.0329
  -6.750  -0.4804   0.05979   0.05619  -0.0351   1.0000   0.0336
  -6.500  -0.4842   0.05762   0.05400  -0.0321   1.0000   0.0341
  -6.250  -0.4886   0.05561   0.05195  -0.0290   1.0000   0.0348
  -6.000  -0.4915   0.05355   0.04984  -0.0261   1.0000   0.0357
  -5.750  -0.4663   0.05003   0.04612  -0.0288   0.9959   0.0386
  -5.500  -0.4225   0.04981   0.04515  -0.0317   0.9894   0.0437
  -5.250  -0.3992   0.04271   0.03784  -0.0349   0.9845   0.0453
  -5.000  -0.3731   0.03885   0.03398  -0.0372   0.9796   0.0474
  -4.750  -0.3429   0.03615   0.03110  -0.0393   0.9739   0.0511
  -4.500  -0.3044   0.03436   0.02863  -0.0413   0.9697   0.0589
  -4.250  -0.2797   0.03097   0.02530  -0.0426   0.9631   0.0629
  -4.000  -0.2456   0.02910   0.02303  -0.0443   0.9584   0.0742
  -3.750  -0.2100   0.02692   0.02065  -0.0469   0.9556   0.0887
  -3.500  -0.1839   0.02504   0.01873  -0.0477   0.9483   0.1056
  -3.250  -0.1509   0.02341   0.01698  -0.0499   0.9443   0.1390
  -3.000  -0.1177   0.02123   0.01473  -0.0521   0.9414   0.1752
  -2.500  -0.0315   0.01873   0.01108  -0.0508   0.9313   0.0564
  -2.250   0.0058   0.01670   0.00894  -0.0521   0.9281   0.0491
  -2.000   0.0352   0.01575   0.00787  -0.0518   0.9213   0.0467
  -1.750   0.0659   0.01484   0.00699  -0.0523   0.9157   0.0484
  -1.500   0.0942   0.01419   0.00636  -0.0523   0.9096   0.0518
  -1.250   0.1200   0.01360   0.00576  -0.0518   0.9022   0.0528
  -1.000   0.1471   0.01312   0.00522  -0.0515   0.8963   0.0554
  -0.750   0.1717   0.01276   0.00477  -0.0507   0.8884   0.0606
  -0.500   0.1989   0.01238   0.00443  -0.0504   0.8827   0.0887
  -0.250   0.2120   0.00993   0.00478  -0.0462   0.8760   0.9087
   0.000   0.3169   0.01007   0.00481  -0.0607   0.8794   0.9836
   0.250   0.3867   0.00987   0.00451  -0.0694   0.8737   1.0000
   0.500   0.4023   0.00974   0.00431  -0.0670   0.8594   1.0000
   0.750   0.4189   0.00961   0.00407  -0.0645   0.8439   1.0000
   1.000   0.4368   0.00950   0.00387  -0.0623   0.8285   1.0000
   1.250   0.4560   0.00946   0.00376  -0.0604   0.8148   1.0000
   1.500   0.4761   0.00945   0.00369  -0.0587   0.8015   1.0000
   1.750   0.4970   0.00945   0.00367  -0.0572   0.7887   1.0000
   2.000   0.5177   0.00938   0.00351  -0.0554   0.7711   1.0000
   2.250   0.5377   0.00934   0.00342  -0.0535   0.7502   1.0000
   2.500   0.5591   0.00933   0.00336  -0.0519   0.7315   1.0000
   2.750   0.5815   0.00936   0.00338  -0.0507   0.7153   1.0000
   3.000   0.6038   0.00941   0.00342  -0.0494   0.6978   1.0000
   3.250   0.6261   0.00947   0.00348  -0.0482   0.6782   1.0000
   3.500   0.6485   0.00955   0.00353  -0.0469   0.6567   1.0000
   3.750   0.6701   0.00966   0.00360  -0.0455   0.6280   1.0000
   4.000   0.6908   0.00982   0.00370  -0.0439   0.5876   1.0000
   4.250   0.7090   0.01013   0.00378  -0.0419   0.5182   1.0000
   4.500   0.7209   0.01093   0.00400  -0.0389   0.4062   1.0000
   4.750   0.7356   0.01172   0.00443  -0.0367   0.3319   1.0000
   5.000   0.7533   0.01238   0.00487  -0.0350   0.2819   1.0000
   5.250   0.7720   0.01298   0.00536  -0.0336   0.2403   1.0000
   5.500   0.7901   0.01368   0.00588  -0.0321   0.1887   1.0000
   5.750   0.7992   0.01533   0.00675  -0.0293   0.0707   1.0000
   6.000   0.8143   0.01652   0.00794  -0.0271   0.0554   1.0000
   6.250   0.8308   0.01752   0.00902  -0.0253   0.0469   1.0000
   6.500   0.8457   0.01868   0.01018  -0.0233   0.0389   1.0000
   6.750   0.8658   0.01936   0.01099  -0.0219   0.0335   1.0000
   7.000   0.8799   0.02079   0.01239  -0.0198   0.0301   1.0000
   7.250   0.8971   0.02246   0.01412  -0.0180   0.0286   1.0000
   7.500   0.9187   0.02420   0.01594  -0.0168   0.0273   1.0000
   7.750   0.9407   0.02570   0.01755  -0.0159   0.0255   1.0000
   8.000   0.9608   0.02726   0.01917  -0.0150   0.0233   1.0000
   8.250   0.9841   0.02972   0.02190  -0.0142   0.0233   1.0000
   8.500   1.0061   0.03276   0.02532  -0.0129   0.0240   1.0000
   8.750   1.0203   0.03737   0.03058  -0.0103   0.0266   1.0000
   9.000   1.0299   0.04236   0.03590  -0.0084   0.0288   1.0000
  14.000   0.6520   0.14881   0.14556  -0.0288   0.0528   1.0000
  14.250   0.6633   0.15138   0.14815  -0.0280   0.0515   1.0000
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