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BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il)
Reynolds number: 50,000
Max Cl/Cd: 20.68 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b707a-il-50000-n5.txt
Download as CSV file: xf-b707a-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7901   0.09362   0.08526  -0.0148   1.0000   0.0499
 -12.000  -0.8178   0.08588   0.07737  -0.0195   1.0000   0.0495
 -11.750  -0.8432   0.07937   0.07069  -0.0231   1.0000   0.0492
 -11.500  -0.8666   0.07388   0.06500  -0.0255   1.0000   0.0491
 -11.250  -0.8855   0.06945   0.06037  -0.0265   1.0000   0.0490
 -11.000  -0.9021   0.06565   0.05634  -0.0262   1.0000   0.0490
 -10.750  -0.9151   0.06241   0.05288  -0.0248   1.0000   0.0492
 -10.500  -0.9251   0.05943   0.04965  -0.0227   1.0000   0.0495
 -10.250  -0.9290   0.05645   0.04637  -0.0208   1.0000   0.0500
 -10.000  -0.9286   0.05351   0.04309  -0.0189   1.0000   0.0507
  -9.750  -0.9232   0.05071   0.03994  -0.0172   1.0000   0.0517
  -9.500  -0.9073   0.04852   0.03768  -0.0162   1.0000   0.0530
  -9.250  -0.8922   0.04635   0.03534  -0.0150   1.0000   0.0550
  -9.000  -0.8784   0.04410   0.03268  -0.0134   1.0000   0.0579
  -8.750  -0.8571   0.04234   0.03100  -0.0127   1.0000   0.0613
  -8.500  -0.8360   0.04048   0.02894  -0.0115   1.0000   0.0660
  -8.250  -0.8130   0.03882   0.02723  -0.0105   1.0000   0.0721
  -8.000  -0.7916   0.03726   0.02575  -0.0092   1.0000   0.0784
  -7.750  -0.7759   0.03586   0.02434  -0.0075   1.0000   0.0856
  -7.500  -0.7650   0.03451   0.02303  -0.0056   1.0000   0.0952
  -7.250  -0.7548   0.03320   0.02178  -0.0036   1.0000   0.1058
  -7.000  -0.7431   0.03198   0.02057  -0.0016   1.0000   0.1159
  -6.750  -0.7316   0.03076   0.01941   0.0005   1.0000   0.1245
  -6.500  -0.7192   0.02961   0.01828   0.0026   1.0000   0.1310
  -6.250  -0.7059   0.02852   0.01718   0.0047   1.0000   0.1364
  -6.000  -0.6922   0.02745   0.01610   0.0067   1.0000   0.1430
  -5.750  -0.6787   0.02631   0.01501   0.0086   1.0000   0.1522
  -5.500  -0.6645   0.02513   0.01394   0.0104   1.0000   0.1657
  -5.250  -0.6505   0.02379   0.01282   0.0122   1.0000   0.1944
  -5.000  -0.6383   0.02241   0.01197   0.0143   1.0000   0.2610
  -4.750  -0.6243   0.02231   0.01232   0.0172   1.0000   0.3993
  -4.500  -0.6060   0.02228   0.01216   0.0194   1.0000   0.4389
  -4.250  -0.5876   0.02232   0.01218   0.0217   1.0000   0.4690
  -4.000  -0.5673   0.02225   0.01206   0.0236   1.0000   0.4897
  -3.750  -0.5463   0.02207   0.01174   0.0251   1.0000   0.5053
  -3.500  -0.5239   0.02195   0.01165   0.0268   1.0000   0.5188
  -3.250  -0.5018   0.02175   0.01139   0.0282   1.0000   0.5312
  -3.000  -0.4796   0.02155   0.01114   0.0295   1.0000   0.5435
  -2.750  -0.4567   0.02134   0.01096   0.0309   1.0000   0.5540
  -2.500  -0.4346   0.02112   0.01069   0.0321   1.0000   0.5662
  -2.250  -0.4121   0.02098   0.01064   0.0337   1.0000   0.5790
  -2.000  -0.3904   0.02081   0.01053   0.0352   1.0000   0.5933
  -1.750  -0.3683   0.02064   0.01040   0.0366   1.0000   0.6066
  -1.500  -0.3449   0.02043   0.01026   0.0377   1.0000   0.6158
  -1.250  -0.3213   0.02017   0.01003   0.0385   1.0000   0.6222
  -1.000  -0.2970   0.01989   0.00974   0.0390   1.0000   0.6270
  -0.750  -0.2724   0.01963   0.00950   0.0393   1.0000   0.6311
  -0.500  -0.2476   0.01941   0.00937   0.0398   1.0000   0.6346
  -0.250  -0.2020   0.01927   0.00933   0.0360   0.9776   0.6390
   0.000  -0.1544   0.01900   0.00916   0.0323   0.9159   0.6445
   0.250  -0.0590   0.01901   0.00876   0.0207   0.7026   0.6516
   0.500  -0.0235   0.01944   0.00865   0.0201   0.5895   0.6575
   0.750   0.0025   0.01976   0.00864   0.0209   0.5339   0.6651
   1.000   0.0285   0.01998   0.00868   0.0214   0.4936   0.6740
   1.250   0.0547   0.02014   0.00877   0.0220   0.4597   0.6839
   1.500   0.0808   0.02027   0.00885   0.0226   0.4299   0.6961
   1.750   0.1066   0.02044   0.00893   0.0232   0.4053   0.7105
   2.000   0.1330   0.02065   0.00911   0.0238   0.3837   0.7273
   2.250   0.1606   0.02096   0.00940   0.0241   0.3643   0.7483
   2.500   0.1912   0.02138   0.00985   0.0239   0.3457   0.7747
   2.750   0.2271   0.02191   0.01049   0.0228   0.3275   0.8063
   3.000   0.2686   0.02257   0.01128   0.0206   0.3097   0.8439
   3.250   0.3148   0.02332   0.01213   0.0173   0.2922   0.8852
   3.500   0.3604   0.02397   0.01299   0.0140   0.2748   0.9282
   3.750   0.4043   0.02441   0.01363   0.0107   0.2551   0.9685
   4.000   0.4451   0.02441   0.01371   0.0078   0.2346   1.0000
   4.250   0.4629   0.02436   0.01353   0.0094   0.2215   1.0000
   4.500   0.4817   0.02449   0.01347   0.0108   0.2098   1.0000
   4.750   0.5023   0.02499   0.01389   0.0120   0.1988   1.0000
   5.000   0.5233   0.02572   0.01466   0.0132   0.1879   1.0000
   5.250   0.5441   0.02650   0.01537   0.0143   0.1783   1.0000
   5.500   0.5649   0.02734   0.01624   0.0155   0.1687   1.0000
   5.750   0.5857   0.02839   0.01740   0.0166   0.1599   1.0000
   6.000   0.6065   0.02933   0.01834   0.0177   0.1535   1.0000
   6.250   0.6267   0.03066   0.01986   0.0189   0.1472   1.0000
   6.500   0.6468   0.03182   0.02111   0.0200   0.1419   1.0000
   6.750   0.6673   0.03289   0.02215   0.0210   0.1380   1.0000
   7.000   0.6846   0.03472   0.02436   0.0223   0.1335   1.0000
   7.250   0.7024   0.03630   0.02614   0.0234   0.1301   1.0000
   7.500   0.7207   0.03779   0.02773   0.0245   0.1278   1.0000
   7.750   0.7386   0.03933   0.02935   0.0256   0.1256   1.0000
   8.000   0.7469   0.04224   0.03277   0.0270   0.1227   1.0000
   8.250   0.7562   0.04473   0.03557   0.0282   0.1196   1.0000
   8.500   0.7730   0.04581   0.03670   0.0293   0.1161   1.0000
   8.750   0.7832   0.04780   0.03886   0.0304   0.1129   1.0000
   9.000   0.7755   0.05219   0.04371   0.0315   0.1107   1.0000
   9.250   0.7626   0.05700   0.04884   0.0321   0.1093   1.0000
   9.500   0.7319   0.06387   0.05596   0.0313   0.1095   1.0000
   9.750   0.6869   0.07267   0.06482   0.0283   0.1115   1.0000
  10.000   0.6530   0.08309   0.07520   0.0209   0.1129   1.0000
  10.250   0.6325   0.09105   0.08311   0.0158   0.1127   1.0000
  10.500   0.6174   0.09783   0.08983   0.0117   0.1119   1.0000
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