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BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il)
Reynolds number: 50,000
Max Cl/Cd: 22.61 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b707b-il-50000-n5.txt
Download as CSV file: xf-b707b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .19 SPAN AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6945   0.10355   0.09665  -0.0111   1.0000   0.0625
 -11.750  -0.6962   0.09859   0.09169  -0.0131   1.0000   0.0620
 -11.500  -0.7058   0.09295   0.08603  -0.0160   1.0000   0.0614
 -11.250  -0.7208   0.08730   0.08034  -0.0189   1.0000   0.0609
 -11.000  -0.7391   0.08203   0.07500  -0.0211   1.0000   0.0603
 -10.750  -0.7586   0.07739   0.07026  -0.0222   1.0000   0.0599
 -10.500  -0.7767   0.07339   0.06614  -0.0220   1.0000   0.0595
 -10.250  -0.7930   0.06986   0.06247  -0.0206   1.0000   0.0591
 -10.000  -0.8061   0.06661   0.05904  -0.0186   1.0000   0.0588
  -9.750  -0.8135   0.06332   0.05553  -0.0169   1.0000   0.0584
  -9.500  -0.8169   0.06011   0.05206  -0.0151   1.0000   0.0580
  -9.250  -0.8161   0.05703   0.04870  -0.0134   1.0000   0.0577
  -9.000  -0.8113   0.05407   0.04545  -0.0118   1.0000   0.0574
  -8.750  -0.8031   0.05126   0.04232  -0.0103   1.0000   0.0571
  -8.500  -0.7914   0.04860   0.03936  -0.0091   1.0000   0.0569
  -8.250  -0.7768   0.04610   0.03656  -0.0080   1.0000   0.0567
  -8.000  -0.7591   0.04376   0.03393  -0.0073   1.0000   0.0566
  -7.750  -0.7391   0.04159   0.03151  -0.0067   1.0000   0.0566
  -7.500  -0.7170   0.03960   0.02927  -0.0063   1.0000   0.0568
  -7.250  -0.6934   0.03779   0.02727  -0.0061   1.0000   0.0570
  -7.000  -0.6637   0.03605   0.02535  -0.0069   0.9787   0.0573
  -6.750  -0.6243   0.03432   0.02342  -0.0091   0.9538   0.0580
  -6.500  -0.5834   0.03282   0.02175  -0.0113   0.9394   0.0590
  -6.250  -0.5440   0.03155   0.02032  -0.0132   0.9283   0.0602
  -6.000  -0.5089   0.03050   0.01906  -0.0145   0.9184   0.0618
  -5.750  -0.4800   0.02944   0.01794  -0.0151   0.9093   0.0643
  -5.500  -0.4556   0.02851   0.01692  -0.0151   0.9011   0.0677
  -5.250  -0.4334   0.02768   0.01592  -0.0147   0.8941   0.0719
  -5.000  -0.4136   0.02674   0.01487  -0.0140   0.8880   0.0775
  -4.750  -0.3943   0.02585   0.01388  -0.0131   0.8828   0.0859
  -4.500  -0.3769   0.02482   0.01295  -0.0121   0.8778   0.1002
  -4.250  -0.3604   0.02358   0.01204  -0.0111   0.8738   0.1534
  -4.000  -0.3624   0.02134   0.01165  -0.0071   0.8696   0.4541
  -3.750  -0.3481   0.02132   0.01232  -0.0033   0.8663   0.6074
  -3.500  -0.3264   0.02154   0.01254  -0.0013   0.8631   0.6590
  -3.250  -0.2993   0.02189   0.01287   0.0001   0.8601   0.6989
  -3.000  -0.2700   0.02234   0.01323   0.0012   0.8570   0.7334
  -2.750  -0.2405   0.02282   0.01364   0.0022   0.8534   0.7632
  -2.500  -0.2066   0.02349   0.01423   0.0029   0.8498   0.7930
  -2.250  -0.1652   0.02400   0.01460   0.0018   0.8462   0.8125
  -2.000  -0.1328   0.02409   0.01455   0.0012   0.8422   0.8255
  -1.750  -0.1050   0.02409   0.01444   0.0011   0.8380   0.8373
  -1.500  -0.0712   0.02412   0.01436  -0.0001   0.8328   0.8461
  -1.250  -0.0395   0.02409   0.01421  -0.0006   0.8261   0.8553
  -1.000  -0.0125   0.02406   0.01411  -0.0005   0.8177   0.8659
  -0.750   0.0213   0.02400   0.01395  -0.0012   0.8088   0.8745
  -0.500   0.0537   0.02399   0.01389  -0.0021   0.8000   0.8834
  -0.250   0.0844   0.02395   0.01381  -0.0026   0.7935   0.8931
   0.000   0.1145   0.02396   0.01381  -0.0033   0.7876   0.9036
   0.250   0.1505   0.02395   0.01380  -0.0048   0.7796   0.9134
   0.500   0.1852   0.02387   0.01371  -0.0057   0.7675   0.9242
   0.750   0.2193   0.02374   0.01357  -0.0064   0.7530   0.9355
   1.000   0.2527   0.02355   0.01337  -0.0070   0.7369   0.9464
   1.250   0.2864   0.02335   0.01319  -0.0078   0.7216   0.9568
   1.500   0.3198   0.02311   0.01299  -0.0086   0.7045   0.9668
   1.750   0.3516   0.02275   0.01264  -0.0091   0.6805   0.9765
   2.000   0.3828   0.02231   0.01222  -0.0094   0.6511   0.9857
   2.250   0.4152   0.02188   0.01186  -0.0103   0.6178   0.9946
   2.500   0.4427   0.02164   0.01183  -0.0111   0.5735   1.0000
   2.750   0.4537   0.02115   0.01093  -0.0073   0.4403   1.0000
   3.000   0.4640   0.02145   0.01053  -0.0041   0.3975   1.0000
   3.250   0.4778   0.02198   0.01086  -0.0023   0.3656   1.0000
   3.500   0.4932   0.02247   0.01127  -0.0008   0.3377   1.0000
   4.000   0.5212   0.02352   0.01214   0.0027   0.2837   1.0000
   4.250   0.5334   0.02415   0.01259   0.0047   0.2602   1.0000
   4.500   0.5469   0.02467   0.01312   0.0066   0.2309   1.0000
   4.750   0.5610   0.02514   0.01361   0.0086   0.2006   1.0000
   5.000   0.5736   0.02575   0.01404   0.0107   0.1816   1.0000
   5.250   0.5861   0.02641   0.01452   0.0128   0.1705   1.0000
   5.500   0.6000   0.02708   0.01513   0.0149   0.1618   1.0000
   5.750   0.6144   0.02778   0.01575   0.0169   0.1558   1.0000
   6.000   0.6305   0.02849   0.01642   0.0188   0.1515   1.0000
   6.250   0.6491   0.02918   0.01720   0.0204   0.1474   1.0000
   6.500   0.6687   0.02991   0.01799   0.0218   0.1441   1.0000
   6.750   0.6893   0.03068   0.01880   0.0230   0.1414   1.0000
   7.000   0.7108   0.03151   0.01968   0.0241   0.1392   1.0000
   7.250   0.7328   0.03241   0.02058   0.0251   0.1373   1.0000
   7.500   0.7542   0.03338   0.02172   0.0261   0.1351   1.0000
   7.750   0.7737   0.03441   0.02296   0.0272   0.1321   1.0000
   8.000   0.7915   0.03542   0.02413   0.0284   0.1288   1.0000
   8.250   0.8080   0.03632   0.02512   0.0297   0.1252   1.0000
   8.500   0.8253   0.03724   0.02596   0.0308   0.1220   1.0000
   8.750   0.8398   0.03851   0.02757   0.0322   0.1192   1.0000
   9.000   0.8544   0.03984   0.02915   0.0336   0.1169   1.0000
   9.250   0.8676   0.04110   0.03064   0.0350   0.1143   1.0000
   9.500   0.8806   0.04225   0.03191   0.0363   0.1117   1.0000
   9.750   0.8949   0.04327   0.03297   0.0376   0.1094   1.0000
  10.000   0.9074   0.04476   0.03460   0.0389   0.1079   1.0000
  10.250   0.9146   0.04675   0.03694   0.0404   0.1071   1.0000
  10.500   0.9188   0.04893   0.03943   0.0421   0.1063   1.0000
  10.750   0.9187   0.05134   0.04215   0.0438   0.1055   1.0000
  11.000   0.9134   0.05400   0.04509   0.0457   0.1049   1.0000
  11.250   0.9000   0.05690   0.04823   0.0479   0.1044   1.0000
  11.500   0.8802   0.06054   0.05208   0.0492   0.1042   1.0000
  11.750   0.8512   0.06557   0.05731   0.0488   0.1042   1.0000
  12.000   0.8084   0.07317   0.06505   0.0461   0.1049   1.0000
  12.250   0.7499   0.08525   0.07715   0.0393   0.1060   1.0000
  12.500   0.7060   0.09857   0.09044   0.0312   0.1066   1.0000
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