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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 100,000
Max Cl/Cd: 40.45 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bacnlf-il-100000-n5.txt
Download as CSV file: xf-bacnlf-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING HSNLF AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5442   0.09251   0.08742  -0.0403   1.0014   0.0184
  -9.500  -0.5509   0.08723   0.08220  -0.0429   1.0014   0.0180
  -9.250  -0.5617   0.08167   0.07667  -0.0459   1.0014   0.0177
  -9.000  -0.5772   0.07699   0.07202  -0.0476   1.0014   0.0175
  -8.750  -0.5971   0.07337   0.06840  -0.0474   1.0014   0.0173
  -8.500  -0.6194   0.07063   0.06565  -0.0453   1.0014   0.0172
  -8.250  -0.6356   0.06738   0.06234  -0.0434   1.0014   0.0169
  -8.000  -0.6484   0.06402   0.05887  -0.0414   1.0014   0.0166
  -7.750  -0.6577   0.06047   0.05515  -0.0393   1.0014   0.0162
  -7.500  -0.6632   0.05671   0.05117  -0.0372   1.0014   0.0157
  -7.250  -0.6649   0.05276   0.04694  -0.0351   1.0014   0.0152
  -7.000  -0.6627   0.04854   0.04232  -0.0329   1.0014   0.0145
  -6.750  -0.6558   0.04443   0.03769  -0.0307   1.0014   0.0138
  -6.500  -0.6440   0.04135   0.03418  -0.0289   1.0014   0.0135
  -6.250  -0.6298   0.03859   0.03100  -0.0274   1.0014   0.0134
  -6.000  -0.6135   0.03593   0.02793  -0.0260   1.0014   0.0133
  -5.750  -0.5954   0.03325   0.02484  -0.0249   1.0014   0.0133
  -5.500  -0.5754   0.03066   0.02187  -0.0239   1.0014   0.0134
  -5.250  -0.5538   0.02832   0.01922  -0.0230   1.0014   0.0137
  -5.000  -0.5314   0.02637   0.01705  -0.0222   1.0014   0.0142
  -4.750  -0.5085   0.02484   0.01531  -0.0215   1.0014   0.0151
  -4.500  -0.4855   0.02373   0.01406  -0.0208   1.0014   0.0175
  -4.250  -0.4620   0.02283   0.01297  -0.0201   1.0014   0.0206
  -4.000  -0.4394   0.02149   0.01167  -0.0198   1.0014   0.0273
  -3.750  -0.4150   0.02021   0.01024  -0.0194   1.0014   0.0331
  -3.500  -0.3900   0.01927   0.00921  -0.0192   1.0014   0.0454
  -3.250  -0.3636   0.01822   0.00823  -0.0195   1.0014   0.0793
  -3.000  -0.3373   0.01553   0.00805  -0.0209   1.0014   0.5922
  -2.750  -0.3202   0.01605   0.00869  -0.0177   1.0014   0.6878
  -2.500  -0.3009   0.01668   0.00940  -0.0143   0.9984   0.7465
  -2.250  -0.2702   0.01679   0.00928  -0.0149   0.9960   0.7586
  -2.000  -0.2397   0.01677   0.00907  -0.0158   0.9930   0.7638
  -1.750  -0.2079   0.01679   0.00892  -0.0171   0.9901   0.7693
  -1.500  -0.1739   0.01683   0.00879  -0.0190   0.9873   0.7749
  -1.250  -0.1419   0.01688   0.00871  -0.0202   0.9843   0.7796
  -1.000  -0.1113   0.01689   0.00862  -0.0213   0.9802   0.7850
  -0.750  -0.0785   0.01695   0.00860  -0.0229   0.9765   0.7901
  -0.500  -0.0446   0.01704   0.00864  -0.0246   0.9735   0.7951
  -0.250  -0.0140   0.01709   0.00862  -0.0257   0.9695   0.8009
   0.000   0.0156   0.01714   0.00867  -0.0265   0.9652   0.8058
   0.250   0.0486   0.01723   0.00876  -0.0280   0.9617   0.8116
   0.500   0.0808   0.01733   0.00887  -0.0294   0.9582   0.8174
   0.750   0.1083   0.01739   0.00898  -0.0298   0.9529   0.8231
   1.000   0.1419   0.01749   0.00912  -0.0314   0.9491   0.8298
   1.250   0.1721   0.01757   0.00928  -0.0322   0.9443   0.8358
   1.500   0.2021   0.01763   0.00942  -0.0331   0.9381   0.8431
   1.750   0.2374   0.01769   0.00961  -0.0348   0.9340   0.8496
   2.000   0.2628   0.01774   0.00978  -0.0347   0.9262   0.8583
   2.250   0.2968   0.01776   0.00995  -0.0361   0.9212   0.8662
   2.500   0.3249   0.01770   0.01006  -0.0362   0.9115   0.8756
   2.750   0.3583   0.01754   0.01013  -0.0372   0.9019   0.8858
   3.000   0.3970   0.01721   0.01003  -0.0389   0.8926   0.8959
   3.250   0.4359   0.01617   0.00922  -0.0394   0.8671   0.9061
   3.500   0.4675   0.01508   0.00837  -0.0381   0.8295   0.9196
   3.750   0.5010   0.01439   0.00789  -0.0379   0.7856   0.9369
   4.000   0.5590   0.01382   0.00653  -0.0407   0.5475   0.9385
   4.250   0.5746   0.01582   0.00705  -0.0389   0.2588   0.9650
   4.500   0.5957   0.01731   0.00785  -0.0387   0.1266   0.9986
   4.750   0.6167   0.01835   0.00868  -0.0379   0.0885   0.9986
   5.000   0.6382   0.01936   0.00965  -0.0371   0.0667   0.9986
   5.250   0.6597   0.02037   0.01064  -0.0363   0.0458   0.9986
   5.500   0.6813   0.02144   0.01170  -0.0355   0.0316   0.9986
   5.750   0.7025   0.02276   0.01308  -0.0345   0.0249   0.9986
   6.000   0.7251   0.02423   0.01472  -0.0337   0.0218   0.9986
   6.250   0.7487   0.02588   0.01647  -0.0331   0.0200   0.9986
   6.500   0.7735   0.02844   0.01919  -0.0327   0.0188   0.9986
   6.750   0.7993   0.03084   0.02192  -0.0321   0.0182   0.9986
   7.000   0.8224   0.03361   0.02513  -0.0311   0.0178   0.9986
   7.250   0.8416   0.03670   0.02872  -0.0295   0.0176   0.9986
   7.500   0.8566   0.04010   0.03263  -0.0275   0.0174   0.9986
   7.750   0.8674   0.04374   0.03677  -0.0250   0.0174   0.9986
   8.000   0.8743   0.04754   0.04109  -0.0223   0.0172   0.9986
   8.250   0.8777   0.05144   0.04544  -0.0194   0.0168   0.9986
   8.500   0.8775   0.05545   0.04983  -0.0166   0.0165   0.9986
   8.750   0.8737   0.05953   0.05425  -0.0138   0.0161   0.9986
   9.000   0.8663   0.06362   0.05860  -0.0112   0.0159   0.9986
   9.250   0.8540   0.06754   0.06273  -0.0085   0.0158   0.9986
   9.500   0.8385   0.07156   0.06692  -0.0063   0.0159   0.9986
   9.750   0.8215   0.07600   0.07149  -0.0054   0.0160   0.9986
  10.000   0.8039   0.08114   0.07675  -0.0062   0.0162   0.9986
  10.250   0.7878   0.08702   0.08270  -0.0089   0.0167   0.9986
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