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BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il)
Reynolds number: 500,000
Max Cl/Cd: 51.79 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bacj-il-500000.txt
Download as CSV file: xf-bacj-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING AIRFOIL J                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6814   0.10236   0.09977  -0.0405   1.0000   0.0264
 -13.000  -0.6795   0.10052   0.09796  -0.0407   1.0000   0.0267
 -12.750  -0.8004   0.06821   0.06536  -0.0610   1.0000   0.0240
 -12.500  -0.8583   0.05826   0.05515  -0.0651   1.0000   0.0232
 -12.250  -0.8943   0.05308   0.04978  -0.0648   1.0000   0.0233
 -12.000  -0.9900   0.04432   0.04041  -0.0596   1.0000   0.0223
 -11.750  -0.9542   0.04641   0.04278  -0.0592   1.0000   0.0233
 -11.500  -1.0120   0.04282   0.03888  -0.0511   1.0000   0.0227
 -11.250  -1.0484   0.03874   0.03437  -0.0447   1.0000   0.0224
 -11.000  -1.0446   0.03774   0.03331  -0.0420   1.0000   0.0227
 -10.750  -1.0397   0.03663   0.03212  -0.0395   1.0000   0.0230
 -10.500  -1.0367   0.03273   0.02775  -0.0383   0.9987   0.0227
 -10.250  -1.0163   0.03097   0.02581  -0.0388   0.9971   0.0230
 -10.000  -0.9949   0.02908   0.02370  -0.0393   0.9955   0.0233
  -9.750  -0.9723   0.02761   0.02205  -0.0396   0.9935   0.0235
  -9.500  -0.9478   0.02626   0.02053  -0.0401   0.9919   0.0241
  -9.250  -0.9225   0.02506   0.01917  -0.0406   0.9908   0.0245
  -9.000  -0.9017   0.02379   0.01774  -0.0400   0.9888   0.0249
  -8.750  -0.8767   0.02311   0.01694  -0.0402   0.9871   0.0255
  -8.500  -0.8503   0.02228   0.01597  -0.0405   0.9859   0.0259
  -8.250  -0.8262   0.02072   0.01430  -0.0406   0.9850   0.0267
  -8.000  -0.8057   0.01985   0.01340  -0.0398   0.9828   0.0273
  -7.750  -0.7804   0.01917   0.01270  -0.0399   0.9810   0.0281
  -7.500  -0.7528   0.01853   0.01202  -0.0404   0.9796   0.0291
  -7.250  -0.7238   0.01797   0.01140  -0.0411   0.9787   0.0299
  -7.000  -0.7029   0.01750   0.01088  -0.0401   0.9759   0.0309
  -6.750  -0.6764   0.01690   0.01020  -0.0403   0.9741   0.0321
  -6.500  -0.6491   0.01611   0.00941  -0.0408   0.9727   0.0337
  -6.250  -0.6184   0.01571   0.00900  -0.0418   0.9718   0.0356
  -6.000  -0.5995   0.01544   0.00869  -0.0401   0.9685   0.0381
  -5.750  -0.5747   0.01485   0.00811  -0.0400   0.9666   0.0411
  -5.500  -0.5452   0.01456   0.00781  -0.0406   0.9654   0.0445
  -5.250  -0.5153   0.01416   0.00741  -0.0413   0.9644   0.0500
  -5.000  -0.4959   0.01391   0.00715  -0.0398   0.9611   0.0555
  -4.750  -0.4701   0.01352   0.00682  -0.0396   0.9589   0.0668
  -4.500  -0.4421   0.01312   0.00658  -0.0400   0.9574   0.0910
  -4.250  -0.4117   0.01279   0.00639  -0.0409   0.9563   0.1217
  -4.000  -0.3881   0.01256   0.00626  -0.0403   0.9538   0.1469
  -3.750  -0.3672   0.01234   0.00614  -0.0390   0.9506   0.1733
  -3.500  -0.3407   0.01207   0.00602  -0.0390   0.9488   0.2092
  -3.250  -0.3129   0.01168   0.00588  -0.0393   0.9474   0.2649
  -2.750  -0.2792   0.01047   0.00560  -0.0355   0.9403   0.4964
  -2.500  -0.2540   0.01021   0.00567  -0.0349   0.9381   0.5886
  -2.250  -0.2234   0.01018   0.00573  -0.0353   0.9368   0.6283
  -2.000  -0.1915   0.01022   0.00580  -0.0361   0.9358   0.6500
  -1.750  -0.1739   0.01033   0.00591  -0.0338   0.9314   0.6647
  -1.500  -0.1488   0.01041   0.00601  -0.0331   0.9285   0.6810
  -1.250  -0.1175   0.01046   0.00605  -0.0337   0.9266   0.6956
  -1.000  -0.0823   0.01042   0.00604  -0.0350   0.9253   0.7031
  -0.750  -0.0488   0.01044   0.00604  -0.0362   0.9243   0.7109
  -0.500  -0.0283   0.01046   0.00610  -0.0344   0.9186   0.7176
  -0.250   0.0072   0.01031   0.00598  -0.0357   0.9154   0.7249
   0.000   0.0488   0.01005   0.00573  -0.0382   0.9135   0.7308
   0.250   0.0896   0.00983   0.00556  -0.0406   0.9122   0.7364
   0.500   0.1332   0.00955   0.00530  -0.0436   0.9113   0.7452
   0.750   0.1560   0.00938   0.00520  -0.0420   0.9033   0.7510
   1.000   0.2343   0.00815   0.00402  -0.0516   0.8985   0.7551
   1.250   0.2648   0.00776   0.00363  -0.0515   0.8857   0.7592
   1.500   0.2984   0.00745   0.00331  -0.0521   0.8706   0.7627
   1.750   0.3236   0.00726   0.00315  -0.0511   0.8489   0.7662
   2.000   0.3698   0.00714   0.00287  -0.0545   0.7813   0.7686
   2.250   0.3768   0.00784   0.00285  -0.0495   0.6221   0.7718
   2.500   0.3624   0.00886   0.00308  -0.0405   0.4456   0.7758
   2.750   0.3659   0.00988   0.00338  -0.0357   0.2771   0.7792
   3.000   0.3758   0.01097   0.00372  -0.0325   0.1000   0.7819
   3.250   0.3952   0.01152   0.00404  -0.0308   0.0582   0.7847
   3.500   0.4176   0.01180   0.00433  -0.0297   0.0511   0.7879
   3.750   0.4394   0.01215   0.00465  -0.0284   0.0462   0.7914
   4.000   0.4612   0.01249   0.00498  -0.0271   0.0426   0.7947
   4.250   0.4843   0.01273   0.00523  -0.0261   0.0402   0.7975
   4.500   0.5057   0.01318   0.00568  -0.0249   0.0376   0.8003
   4.750   0.5267   0.01374   0.00628  -0.0235   0.0361   0.8036
   5.000   0.5498   0.01407   0.00665  -0.0225   0.0345   0.8071
   5.250   0.5729   0.01436   0.00692  -0.0216   0.0324   0.8108
   5.500   0.5955   0.01513   0.00767  -0.0207   0.0304   0.8140
   5.750   0.6214   0.01599   0.00857  -0.0206   0.0300   0.8174
   6.000   0.6461   0.01629   0.00896  -0.0199   0.0289   0.8210
   6.250   0.6721   0.01687   0.00957  -0.0196   0.0274   0.8247
   6.500   0.7013   0.01775   0.01051  -0.0200   0.0271   0.8280
   6.750   0.7278   0.01830   0.01108  -0.0200   0.0259   0.8312
   7.000   0.7572   0.01936   0.01217  -0.0206   0.0252   0.8346
   7.250   0.7903   0.02118   0.01408  -0.0220   0.0248   0.8381
   7.500   0.8178   0.02295   0.01606  -0.0221   0.0244   0.8421
   7.750   0.8396   0.02337   0.01669  -0.0210   0.0236   0.8463
   8.000   0.8647   0.02559   0.01919  -0.0206   0.0237   0.8501
   8.250   0.8854   0.02740   0.02125  -0.0195   0.0236   0.8548
   8.500   0.9010   0.02989   0.02410  -0.0175   0.0235   0.8595
   8.750   0.9158   0.03249   0.02703  -0.0157   0.0236   0.8648
   9.000   0.8043   0.03008   0.02641   0.0035   0.0329   0.8586
   9.250   0.8057   0.03276   0.02926   0.0061   0.0321   0.8641
   9.500   0.8010   0.03547   0.03209   0.0094   0.0318   0.8711
   9.750   0.7893   0.03892   0.03575   0.0129   0.0317   0.8784
  10.000   0.7843   0.04173   0.03869   0.0149   0.0314   0.8859
  10.250   0.7811   0.04471   0.04179   0.0161   0.0311   0.8942
  10.500   0.7676   0.04865   0.04589   0.0172   0.0309   0.9033
  10.750   0.7461   0.05338   0.05079   0.0176   0.0309   0.9140
  11.000   0.7307   0.05868   0.05624   0.0163   0.0307   0.9209
  11.250   0.5777   0.08579   0.08362   0.0015   0.0320   0.9059
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