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BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il)
Reynolds number: 500,000
Max Cl/Cd: 80.09 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707d-il-500000.txt
Download as CSV file: xf-b707d-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3711   0.08576   0.08362  -0.0319   1.0000   0.0150
  -9.250  -0.3722   0.08148   0.07935  -0.0337   1.0000   0.0150
  -8.750  -0.4515   0.08300   0.08079  -0.0368   1.0000   0.0149
  -8.500  -0.4599   0.07905   0.07683  -0.0401   1.0000   0.0150
  -8.250  -0.4653   0.07563   0.07338  -0.0407   1.0000   0.0150
  -8.000  -0.4675   0.07211   0.06981  -0.0410   1.0000   0.0150
  -7.750  -0.4680   0.06888   0.06653  -0.0406   1.0000   0.0150
  -7.500  -0.4847   0.06260   0.06023  -0.0396   1.0000   0.0154
  -7.250  -0.4901   0.05984   0.05746  -0.0372   1.0000   0.0156
  -7.000  -0.4817   0.05660   0.05418  -0.0377   0.9979   0.0158
  -6.750  -0.4581   0.05264   0.05011  -0.0413   0.9934   0.0163
  -6.500  -0.4334   0.04880   0.04612  -0.0445   0.9878   0.0169
  -6.250  -0.4050   0.04493   0.04208  -0.0478   0.9836   0.0179
  -6.000  -0.3768   0.04139   0.03830  -0.0498   0.9773   0.0196
  -5.750  -0.3370   0.04016   0.03673  -0.0511   0.9729   0.0214
  -5.500  -0.3059   0.03759   0.03386  -0.0528   0.9677   0.0216
  -5.250  -0.2793   0.03483   0.03083  -0.0536   0.9591   0.0217
  -5.000  -0.2628   0.02795   0.02364  -0.0543   0.9492   0.0229
  -4.750  -0.2368   0.02579   0.02135  -0.0550   0.9412   0.0236
  -4.500  -0.2140   0.02409   0.01948  -0.0545   0.9299   0.0245
  -4.250  -0.1907   0.02255   0.01775  -0.0538   0.9193   0.0261
  -4.000  -0.1659   0.02126   0.01623  -0.0530   0.9098   0.0283
  -3.750  -0.1370   0.02231   0.01703  -0.0519   0.9004   0.0313
  -3.500  -0.1175   0.01841   0.01275  -0.0506   0.8906   0.0330
  -3.250  -0.0934   0.01688   0.01114  -0.0502   0.8823   0.0350
  -3.000  -0.0685   0.01600   0.01017  -0.0497   0.8733   0.0379
  -2.750  -0.0411   0.01684   0.01085  -0.0491   0.8651   0.0436
  -2.500  -0.0173   0.01419   0.00808  -0.0487   0.8576   0.0485
  -2.250   0.0089   0.01351   0.00733  -0.0482   0.8496   0.0528
  -2.000   0.0383   0.01159   0.00518  -0.0467   0.8430   0.0273
  -1.750   0.0631   0.01077   0.00431  -0.0459   0.8355   0.0265
  -1.500   0.0878   0.01022   0.00369  -0.0451   0.8285   0.0274
  -1.250   0.1127   0.00980   0.00323  -0.0445   0.8211   0.0286
  -1.000   0.1384   0.00954   0.00291  -0.0440   0.8145   0.0304
  -0.750   0.1640   0.00925   0.00260  -0.0435   0.8073   0.0320
  -0.500   0.1888   0.00884   0.00208  -0.0428   0.7999   0.0357
  -0.250   0.2145   0.00864   0.00183  -0.0423   0.7894   0.0421
   0.000   0.2282   0.00689   0.00157  -0.0402   0.7770   0.5747
   0.250   0.2402   0.00603   0.00162  -0.0363   0.7634   0.8293
   0.500   0.2702   0.00588   0.00169  -0.0360   0.7493   0.9301
   0.750   0.3132   0.00596   0.00171  -0.0391   0.7371   0.9597
   1.000   0.3614   0.00607   0.00173  -0.0433   0.7185   0.9771
   1.250   0.4030   0.00618   0.00166  -0.0463   0.6861   0.9861
   1.500   0.4408   0.00625   0.00164  -0.0486   0.6636   0.9915
   1.750   0.4782   0.00633   0.00163  -0.0508   0.6406   0.9964
   2.000   0.5132   0.00646   0.00160  -0.0527   0.6047   1.0000
   2.250   0.5326   0.00665   0.00159  -0.0511   0.5561   1.0000
   2.500   0.5491   0.00711   0.00166  -0.0490   0.4659   1.0000
   2.750   0.5647   0.00776   0.00188  -0.0470   0.3690   1.0000
   3.000   0.5830   0.00826   0.00209  -0.0454   0.3050   1.0000
   3.250   0.6032   0.00863   0.00228  -0.0442   0.2642   1.0000
   3.500   0.6243   0.00894   0.00247  -0.0430   0.2334   1.0000
   3.750   0.6449   0.00932   0.00268  -0.0418   0.1969   1.0000
   4.000   0.6656   0.00970   0.00292  -0.0407   0.1615   1.0000
   4.250   0.6861   0.01012   0.00318  -0.0395   0.1266   1.0000
   4.500   0.7044   0.01074   0.00353  -0.0379   0.0686   1.0000
   4.750   0.7256   0.01113   0.00388  -0.0368   0.0551   1.0000
   5.000   0.7483   0.01140   0.00419  -0.0359   0.0482   1.0000
   5.250   0.7701   0.01176   0.00457  -0.0348   0.0384   1.0000
   5.500   0.7918   0.01213   0.00488  -0.0338   0.0289   1.0000
   5.750   0.8136   0.01251   0.00527  -0.0328   0.0261   1.0000
   6.000   0.8347   0.01299   0.00578  -0.0316   0.0233   1.0000
   6.250   0.8543   0.01364   0.00654  -0.0302   0.0207   1.0000
   6.500   0.8687   0.01482   0.00784  -0.0279   0.0166   1.0000
   6.750   0.8849   0.01583   0.00895  -0.0259   0.0146   1.0000
   7.000   0.9034   0.01661   0.00980  -0.0244   0.0134   1.0000
   7.250   0.9214   0.01747   0.01072  -0.0229   0.0122   1.0000
   7.500   0.9382   0.01851   0.01180  -0.0212   0.0115   1.0000
   7.750   0.9533   0.02008   0.01339  -0.0194   0.0109   1.0000
   8.000   0.9707   0.02206   0.01552  -0.0179   0.0103   1.0000
   8.250   0.9906   0.02350   0.01711  -0.0167   0.0101   1.0000
   8.500   1.0099   0.02530   0.01910  -0.0155   0.0100   1.0000
   8.750   1.0278   0.02769   0.02171  -0.0142   0.0101   1.0000
   9.000   1.0465   0.03230   0.02651  -0.0134   0.0107   1.0000
   9.250   1.0620   0.03282   0.02724  -0.0115   0.0110   1.0000
  16.500   0.8279   0.19801   0.19559  -0.0557   0.0127   1.0000
  16.750   0.8337   0.20191   0.19949  -0.0578   0.0121   1.0000
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