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STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: STRAND AIRFOIL (strand-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.69 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-strand-il-1000000.txt
Download as CSV file: xf-strand-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: STRAND AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4842   0.09160   0.08807   0.0251   0.3785   0.0218
  -8.250  -0.4846   0.08643   0.08292   0.0216   0.3784   0.0221
  -8.000  -0.4880   0.08002   0.07652   0.0167   0.3783   0.0224
  -7.750  -0.5363   0.05144   0.04731  -0.0242   0.3787   0.0235
  -7.500  -0.5235   0.04769   0.04317  -0.0284   0.3785   0.0236
  -7.250  -0.5046   0.04493   0.04014  -0.0305   0.3783   0.0237
  -7.000  -0.4833   0.04246   0.03743  -0.0321   0.3780   0.0237
  -6.750  -0.4603   0.04022   0.03495  -0.0333   0.3777   0.0237
  -6.500  -0.4403   0.03464   0.02912  -0.0354   0.3776   0.0240
  -6.250  -0.4152   0.03244   0.02689  -0.0361   0.3774   0.0241
  -6.000  -0.3892   0.03072   0.02511  -0.0367   0.3772   0.0243
  -5.750  -0.3625   0.02925   0.02355  -0.0372   0.3770   0.0244
  -5.500  -0.3354   0.02793   0.02214  -0.0378   0.3768   0.0246
  -5.250  -0.3078   0.02673   0.02085  -0.0382   0.3766   0.0248
  -5.000  -0.2798   0.02564   0.01964  -0.0387   0.3764   0.0250
  -4.750  -0.2514   0.02464   0.01853  -0.0391   0.3762   0.0254
  -4.500  -0.2227   0.02378   0.01756  -0.0394   0.3760   0.0259
  -4.250  -0.1934   0.02316   0.01680  -0.0396   0.3758   0.0267
  -4.000  -0.1626   0.02403   0.01736  -0.0396   0.3756   0.0276
  -3.750  -0.1330   0.02373   0.01690  -0.0398   0.3755   0.0277
  -3.500  -0.1047   0.02096   0.01408  -0.0404   0.3753   0.0283
  -3.250  -0.0760   0.02012   0.01330  -0.0406   0.3751   0.0286
  -3.000  -0.0470   0.01957   0.01275  -0.0409   0.3750   0.0291
  -2.750  -0.0178   0.01918   0.01236  -0.0411   0.3749   0.0298
  -2.500   0.0118   0.01898   0.01209  -0.0412   0.3748   0.0311
  -2.250   0.0418   0.01858   0.01155  -0.0413   0.3748   0.0329
  -2.000   0.0706   0.01786   0.01094  -0.0415   0.3748   0.0337
  -1.750   0.0999   0.01752   0.01062  -0.0416   0.3747   0.0349
  -1.500   0.1298   0.01746   0.01045  -0.0418   0.3747   0.0381
  -1.250   0.1587   0.01684   0.00998  -0.0420   0.3747   0.0395
  -1.000   0.1883   0.01674   0.00989  -0.0421   0.3747   0.0416
  -0.750   0.2176   0.01628   0.00950  -0.0425   0.3746   0.0461
  -0.500   0.2473   0.01621   0.00946  -0.0426   0.3746   0.0485
   0.000   0.3077   0.01612   0.00928  -0.0425   0.3746   0.0314
   0.250   0.3378   0.01591   0.00909  -0.0428   0.3746   0.0299
   0.500   0.3678   0.01586   0.00905  -0.0431   0.3745   0.0294
   0.750   0.3978   0.01579   0.00899  -0.0433   0.3744   0.0295
   1.000   0.4277   0.01573   0.00894  -0.0435   0.3743   0.0299
   1.250   0.4575   0.01576   0.00898  -0.0438   0.3742   0.0304
   1.500   0.4871   0.01587   0.00911  -0.0440   0.3742   0.0309
   1.750   0.5167   0.01600   0.00926  -0.0442   0.3741   0.0314
   2.000   0.5461   0.01616   0.00944  -0.0444   0.3741   0.0319
   2.250   0.5756   0.01630   0.00960  -0.0446   0.3740   0.0331
   2.500   0.6050   0.01648   0.00981  -0.0449   0.3739   0.0345
   2.750   0.6343   0.01671   0.01005  -0.0451   0.3738   0.0360
   3.000   0.6634   0.01695   0.01033  -0.0453   0.3738   0.0378
   3.250   0.6925   0.01720   0.01064  -0.0455   0.3737   0.0480
   3.500   0.7241   0.01657   0.01101  -0.0470   0.3736   0.4418
   3.750   0.7533   0.01668   0.01143  -0.0474   0.3734   0.5397
   4.000   0.7826   0.01669   0.01164  -0.0477   0.3730   0.6007
   4.250   0.8118   0.01662   0.01179  -0.0479   0.3723   0.6692
   4.500   0.8403   0.01658   0.01204  -0.0480   0.3717   0.7629
   4.750   0.8654   0.01661   0.01243  -0.0474   0.3713   0.8726
   5.000   0.8897   0.01677   0.01278  -0.0465   0.3709   1.0000
   5.250   0.9186   0.01702   0.01305  -0.0468   0.3703   1.0000
   5.500   0.9474   0.01727   0.01331  -0.0470   0.3696   1.0000
   5.750   0.9761   0.01756   0.01362  -0.0472   0.3690   1.0000
   6.000   1.0047   0.01782   0.01390  -0.0474   0.3685   1.0000
   6.250   1.0332   0.01810   0.01421  -0.0476   0.3680   1.0000
   6.500   1.0615   0.01845   0.01458  -0.0478   0.3676   1.0000
   6.750   1.0901   0.01866   0.01480  -0.0479   0.3671   1.0000
   7.000   1.1189   0.01875   0.01489  -0.0480   0.3666   1.0000
   7.250   1.1477   0.01882   0.01496  -0.0481   0.3661   1.0000
   7.500   1.1761   0.01901   0.01517  -0.0482   0.3657   1.0000
   7.750   1.2047   0.01913   0.01530  -0.0483   0.3653   1.0000
   8.000   1.2343   0.01886   0.01500  -0.0482   0.3647   1.0000
   8.250   1.2646   0.01832   0.01438  -0.0481   0.3638   1.0000
   8.500   1.2916   0.01898   0.01499  -0.0482   0.3618   1.0000
   8.750   1.3220   0.01822   0.01428  -0.0482   0.3608   1.0000
   9.000   1.3514   0.01791   0.01403  -0.0483   0.3594   1.0000
   9.250   1.3818   0.01726   0.01338  -0.0482   0.3574   1.0000
   9.500   1.4142   0.01597   0.01199  -0.0480   0.3550   1.0000
   9.750   1.4464   0.01474   0.01066  -0.0479   0.3529   1.0000
  10.000   1.4772   0.01404   0.00989  -0.0479   0.3514   1.0000
  10.250   1.5065   0.01385   0.00967  -0.0479   0.3498   1.0000
  10.500   1.5357   0.01358   0.00951  -0.0481   0.3480   1.0000
  10.750   1.5652   0.01326   0.00928  -0.0483   0.3454   1.0000
  11.000   1.5952   0.01284   0.00889  -0.0484   0.3428   1.0000
  11.250   1.6259   0.01224   0.00829  -0.0485   0.3399   1.0000
  11.500   1.6550   0.01214   0.00828  -0.0487   0.3347   1.0000
  11.750   1.6847   0.01189   0.00810  -0.0489   0.3240   1.0000
  12.000   1.7073   0.01307   0.00878  -0.0496   0.2524   1.0000
  12.250   1.7264   0.01509   0.01067  -0.0503   0.2167   1.0000
  12.500   1.7408   0.01791   0.01333  -0.0514   0.1786   1.0000
  12.750   1.7525   0.02116   0.01651  -0.0531   0.1516   1.0000
  13.000   1.7450   0.03013   0.02569  -0.0602   0.1359   1.0000
  13.250   1.6523   0.04819   0.04425  -0.0740   0.1537   1.0000
  13.500   1.6163   0.05475   0.05088  -0.0756   0.1511   1.0000
  13.750   1.5873   0.06069   0.05683  -0.0769   0.1453   1.0000
  14.000   1.5718   0.06528   0.06140  -0.0778   0.1368   1.0000
  14.250   1.5581   0.06971   0.06577  -0.0785   0.1272   1.0000
  14.500   1.5469   0.07397   0.07000  -0.0793   0.1181   1.0000
  14.750   1.5393   0.07781   0.07379  -0.0799   0.1092   1.0000
  15.000   1.5338   0.08142   0.07735  -0.0805   0.1002   1.0000
  15.250   1.5283   0.08504   0.08092  -0.0810   0.0913   1.0000
  15.500   1.5227   0.08876   0.08459  -0.0817   0.0830   1.0000
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