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BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il)
Reynolds number: 500,000
Max Cl/Cd: 52.43 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b707a-il-500000-n5.txt
Download as CSV file: xf-b707a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .08 SPAN AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.0066   0.12589   0.12242   0.0053   1.0000   0.0114
 -17.750  -1.0330   0.11550   0.11184  -0.0007   1.0000   0.0113
 -17.500  -1.0526   0.10719   0.10335  -0.0054   1.0000   0.0113
 -17.250  -1.0691   0.09996   0.09597  -0.0093   1.0000   0.0113
 -17.000  -1.0831   0.09357   0.08943  -0.0126   1.0000   0.0112
 -16.750  -1.0946   0.08791   0.08364  -0.0154   1.0000   0.0112
 -16.500  -1.1058   0.08251   0.07809  -0.0180   1.0000   0.0112
 -16.250  -1.1143   0.07773   0.07320  -0.0201   1.0000   0.0112
 -16.000  -1.1219   0.07328   0.06864  -0.0220   1.0000   0.0113
 -15.750  -1.1286   0.06907   0.06430  -0.0237   1.0000   0.0113
 -15.500  -1.1358   0.06497   0.06006  -0.0251   1.0000   0.0112
 -15.250  -1.1390   0.06151   0.05651  -0.0262   1.0000   0.0113
 -15.000  -1.1415   0.05821   0.05312  -0.0273   1.0000   0.0114
 -14.750  -1.1436   0.05500   0.04981  -0.0281   1.0000   0.0114
 -14.500  -1.1439   0.05203   0.04673  -0.0289   1.0000   0.0114
 -14.250  -1.1439   0.04914   0.04374  -0.0295   1.0000   0.0115
 -14.000  -1.1418   0.04656   0.04107  -0.0299   1.0000   0.0115
 -13.750  -1.1397   0.04402   0.03842  -0.0302   1.0000   0.0115
 -13.500  -1.1362   0.04169   0.03600  -0.0303   1.0000   0.0115
 -13.250  -1.1319   0.03951   0.03373  -0.0303   1.0000   0.0115
 -13.000  -1.1271   0.03744   0.03157  -0.0301   1.0000   0.0115
 -12.750  -1.1220   0.03546   0.02951  -0.0298   1.0000   0.0115
 -12.500  -1.1162   0.03364   0.02761  -0.0293   1.0000   0.0116
 -12.250  -1.1098   0.03197   0.02587  -0.0286   1.0000   0.0116
 -10.250  -0.9913   0.02279   0.01526  -0.0258   0.6030   0.0119
 -10.000  -0.9852   0.02237   0.01453  -0.0225   0.5035   0.0119
  -9.750  -0.9747   0.02190   0.01374  -0.0201   0.3664   0.0120
  -9.250  -0.9447   0.02069   0.01234  -0.0164   0.3333   0.0121
  -9.000  -0.9277   0.02010   0.01168  -0.0148   0.3301   0.0122
  -8.750  -0.9099   0.01952   0.01104  -0.0133   0.3278   0.0123
  -8.500  -0.8909   0.01899   0.01046  -0.0119   0.3257   0.0124
  -8.250  -0.8713   0.01848   0.00989  -0.0106   0.3239   0.0126
  -8.000  -0.8509   0.01800   0.00936  -0.0094   0.3226   0.0126
  -7.500  -0.8081   0.01714   0.00840  -0.0072   0.3206   0.0129
  -7.250  -0.7858   0.01675   0.00796  -0.0063   0.3200   0.0131
  -7.000  -0.7639   0.01630   0.00747  -0.0052   0.3194   0.0133
  -6.750  -0.7412   0.01592   0.00704  -0.0043   0.3189   0.0135
  -6.500  -0.7180   0.01556   0.00664  -0.0034   0.3184   0.0137
  -6.250  -0.6947   0.01520   0.00624  -0.0026   0.3179   0.0142
  -6.000  -0.6707   0.01490   0.00589  -0.0018   0.3176   0.0146
  -5.750  -0.6464   0.01461   0.00557  -0.0011   0.3172   0.0149
  -5.500  -0.6218   0.01434   0.00526  -0.0004   0.3166   0.0154
  -5.250  -0.5972   0.01407   0.00495   0.0003   0.3156   0.0161
  -5.000  -0.5727   0.01378   0.00463   0.0011   0.3144   0.0173
  -4.750  -0.5491   0.01338   0.00431   0.0019   0.3136   0.0262
  -4.500  -0.5232   0.01323   0.00421   0.0023   0.3130   0.0422
  -4.250  -0.4969   0.01313   0.00409   0.0028   0.3118   0.0461
  -4.000  -0.4708   0.01301   0.00397   0.0033   0.3102   0.0493
  -3.750  -0.4444   0.01293   0.00386   0.0037   0.3090   0.0518
  -3.500  -0.4184   0.01277   0.00370   0.0042   0.3083   0.0538
  -3.250  -0.3922   0.01266   0.00357   0.0047   0.3074   0.0554
  -2.750  -0.3394   0.01244   0.00332   0.0056   0.3045   0.0592
  -2.500  -0.3129   0.01230   0.00318   0.0060   0.3028   0.0617
  -2.250  -0.2862   0.01219   0.00307   0.0064   0.3011   0.0649
  -2.000  -0.2597   0.01204   0.00294   0.0068   0.2989   0.0700
  -1.750  -0.2332   0.01192   0.00283   0.0073   0.2962   0.0762
  -1.500  -0.2098   0.01140   0.00258   0.0081   0.2932   0.1594
  -1.250  -0.1870   0.01082   0.00230   0.0089   0.2910   0.2560
  -1.000  -0.1629   0.01035   0.00226   0.0096   0.2888   0.3695
  -0.750  -0.1353   0.01031   0.00226   0.0099   0.2850   0.3834
  -0.500  -0.1078   0.01029   0.00224   0.0102   0.2808   0.3912
  -0.250  -0.0802   0.01029   0.00224   0.0105   0.2766   0.3987
   0.000  -0.0519   0.01026   0.00222   0.0107   0.2710   0.4038
   0.250  -0.0242   0.01020   0.00218   0.0110   0.2644   0.4084
   0.500   0.0038   0.01014   0.00219   0.0113   0.2510   0.4136
   0.750   0.0315   0.01013   0.00198   0.0115   0.2071   0.4187
   1.000   0.0586   0.01025   0.00203   0.0119   0.1933   0.4222
   1.250   0.0857   0.01035   0.00209   0.0122   0.1834   0.4247
   1.500   0.1126   0.01041   0.00215   0.0126   0.1730   0.4294
   1.750   0.1393   0.01052   0.00223   0.0130   0.1577   0.4344
   2.000   0.1659   0.01068   0.00230   0.0134   0.1376   0.4387
   2.250   0.1928   0.01084   0.00238   0.0138   0.1237   0.4424
   2.500   0.2196   0.01095   0.00247   0.0142   0.1149   0.4453
   2.750   0.2464   0.01105   0.00256   0.0146   0.1068   0.4482
   3.000   0.2732   0.01119   0.00267   0.0150   0.0959   0.4511
   3.250   0.2989   0.01148   0.00282   0.0155   0.0656   0.4540
   3.500   0.3249   0.01173   0.00302   0.0160   0.0564   0.4570
   3.750   0.3515   0.01191   0.00319   0.0164   0.0531   0.4602
   4.000   0.3783   0.01207   0.00337   0.0168   0.0509   0.4633
   4.250   0.4049   0.01220   0.00354   0.0172   0.0491   0.4676
   4.500   0.4312   0.01237   0.00373   0.0177   0.0471   0.4729
   4.750   0.4578   0.01251   0.00391   0.0181   0.0447   0.4795
   5.250   0.5103   0.01280   0.00428   0.0190   0.0385   0.4959
   5.750   0.5604   0.01341   0.00485   0.0202   0.0148   0.5183
   6.000   0.5855   0.01366   0.00519   0.0208   0.0137   0.5337
   6.250   0.6104   0.01387   0.00552   0.0215   0.0132   0.5568
   6.500   0.6347   0.01403   0.00585   0.0222   0.0129   0.5952
   6.750   0.6580   0.01415   0.00621   0.0232   0.0126   0.6538
   7.000   0.6806   0.01430   0.00660   0.0244   0.0123   0.7128
   7.250   0.7026   0.01445   0.00699   0.0256   0.0122   0.7682
   7.500   0.7234   0.01458   0.00742   0.0272   0.0119   0.8373
   7.750   0.7736   0.01500   0.00816   0.0225   0.0116   0.9483
   8.000   0.8158   0.01561   0.00885   0.0193   0.0114   0.9804
   8.250   0.8493   0.01620   0.00952   0.0179   0.0112   0.9938
   8.500   0.8768   0.01682   0.01020   0.0177   0.0111   1.0000
   8.750   0.8977   0.01732   0.01076   0.0190   0.0110   1.0000
   9.000   0.9183   0.01786   0.01136   0.0203   0.0110   1.0000
   9.250   0.9385   0.01844   0.01201   0.0216   0.0109   1.0000
   9.500   0.9583   0.01905   0.01267   0.0229   0.0108   1.0000
   9.750   0.9776   0.01970   0.01339   0.0243   0.0108   1.0000
  10.000   0.9964   0.02040   0.01415   0.0257   0.0107   1.0000
  10.250   1.0144   0.02115   0.01497   0.0271   0.0107   1.0000
  10.500   1.0317   0.02195   0.01584   0.0286   0.0106   1.0000
  10.750   1.0483   0.02278   0.01675   0.0301   0.0106   1.0000
  11.000   1.0639   0.02367   0.01771   0.0317   0.0105   1.0000
  11.250   1.0781   0.02463   0.01875   0.0334   0.0105   1.0000
  11.500   1.0911   0.02565   0.01985   0.0352   0.0105   1.0000
  11.750   1.1032   0.02667   0.02096   0.0370   0.0105   1.0000
  12.000   1.1121   0.02785   0.02223   0.0391   0.0104   1.0000
  12.250   1.1191   0.02907   0.02353   0.0413   0.0104   1.0000
  12.500   1.1194   0.03036   0.02491   0.0444   0.0104   1.0000
  12.750   1.1173   0.03187   0.02651   0.0472   0.0104   1.0000
  13.000   1.1128   0.03379   0.02855   0.0492   0.0104   1.0000
  13.250   1.1041   0.03654   0.03143   0.0498   0.0104   1.0000
  13.500   1.0889   0.04193   0.03702   0.0458   0.0104   1.0000
  13.750   1.0718   0.05083   0.04615   0.0377   0.0104   1.0000
  14.000   1.0443   0.05941   0.05487   0.0317   0.0104   1.0000
  14.250   1.0165   0.06705   0.06262   0.0271   0.0105   1.0000
  14.500   0.9945   0.07383   0.06949   0.0232   0.0105   1.0000
  14.750   0.9749   0.08044   0.07620   0.0196   0.0105   1.0000
  15.000   0.9606   0.08625   0.08207   0.0166   0.0105   1.0000
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