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STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: STRAND AIRFOIL (strand-il)
Reynolds number: 100,000
Max Cl/Cd: 14.17 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-strand-il-100000-n5.txt
Download as CSV file: xf-strand-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4534   0.13198   0.12556   0.0361   0.4348   0.0827
  -9.750  -0.4453   0.12895   0.12255   0.0349   0.4346   0.0853
  -9.500  -0.4716   0.12458   0.11826   0.0249   0.4347   0.0907
  -9.250  -0.4519   0.12091   0.11460   0.0272   0.4344   0.0920
  -9.000  -0.4326   0.11858   0.11227   0.0289   0.4341   0.0942
  -8.750  -0.4228   0.11587   0.10957   0.0281   0.4339   0.0982
  -8.500  -0.4392   0.11092   0.10472   0.0208   0.4339   0.1043
  -8.250  -0.4167   0.10886   0.10264   0.0234   0.4336   0.1066
  -8.000  -0.4056   0.10623   0.10003   0.0227   0.4334   0.1104
  -7.750  -0.4166   0.10148   0.09537   0.0162   0.4334   0.1176
  -7.500  -0.3980   0.09926   0.09315   0.0177   0.4331   0.1198
  -7.250  -0.3878   0.09649   0.09041   0.0164   0.4328   0.1240
  -7.000  -0.4513   0.06279   0.05602  -0.0264   0.4337   0.0594
  -6.750  -0.4333   0.05934   0.05247  -0.0282   0.4334   0.0552
  -6.500  -0.4201   0.05269   0.04491  -0.0349   0.4332   0.0492
  -6.250  -0.3985   0.04981   0.04190  -0.0364   0.4327   0.0483
  -6.000  -0.3754   0.04702   0.03882  -0.0381   0.4322   0.0472
  -5.750  -0.3506   0.04443   0.03586  -0.0397   0.4317   0.0460
  -5.500  -0.3241   0.04220   0.03320  -0.0410   0.4312   0.0449
  -5.250  -0.2963   0.04049   0.03104  -0.0420   0.4307   0.0441
  -5.000  -0.2689   0.03907   0.02940  -0.0428   0.4304   0.0443
  -4.750  -0.2412   0.03782   0.02799  -0.0435   0.4301   0.0448
  -4.500  -0.2129   0.03673   0.02673  -0.0441   0.4298   0.0452
  -4.250  -0.1842   0.03577   0.02558  -0.0446   0.4295   0.0452
  -4.000  -0.1552   0.03495   0.02457  -0.0450   0.4292   0.0447
  -3.750  -0.1261   0.03428   0.02374  -0.0453   0.4290   0.0444
  -3.500  -0.0971   0.03373   0.02306  -0.0457   0.4287   0.0441
  -3.250  -0.0683   0.03326   0.02251  -0.0460   0.4285   0.0440
  -3.000  -0.0396   0.03285   0.02209  -0.0463   0.4283   0.0440
  -2.750  -0.0112   0.03251   0.02176  -0.0466   0.4280   0.0440
  -2.500   0.0171   0.03224   0.02155  -0.0469   0.4279   0.0441
  -2.250   0.0453   0.03204   0.02142  -0.0473   0.4276   0.0443
  -2.000   0.0733   0.03189   0.02134  -0.0477   0.4270   0.0446
  -1.750   0.1015   0.03181   0.02132  -0.0482   0.4264   0.0450
  -1.500   0.1299   0.03183   0.02137  -0.0488   0.4259   0.0463
  -1.250   0.1587   0.03201   0.02155  -0.0495   0.4256   0.0477
  -1.000   0.1876   0.03229   0.02181  -0.0503   0.4253   0.0489
  -0.750   0.2165   0.03264   0.02213  -0.0512   0.4250   0.0495
  -0.500   0.2455   0.03307   0.02254  -0.0521   0.4248   0.0501
  -0.250   0.2743   0.03350   0.02294  -0.0530   0.4245   0.0510
   0.000   0.3029   0.03406   0.02348  -0.0540   0.4242   0.0523
   0.250   0.3312   0.03466   0.02406  -0.0548   0.4238   0.0539
   0.500   0.3591   0.03518   0.02454  -0.0554   0.4231   0.0561
   0.750   0.3869   0.03566   0.02500  -0.0559   0.4225   0.0611
   1.000   0.4145   0.03593   0.02557  -0.0567   0.4219   0.1306
   1.250   0.4418   0.03603   0.02653  -0.0581   0.4216   0.3591
   1.500   0.4684   0.03675   0.02757  -0.0587   0.4212   0.4529
   1.750   0.4944   0.03759   0.02860  -0.0592   0.4208   0.5134
   2.000   0.5195   0.03842   0.02962  -0.0594   0.4202   0.5770
   2.250   0.5407   0.04197   0.03371  -0.0650   0.4165   0.6361
   2.500   0.5611   0.04396   0.03598  -0.0672   0.4134   0.6896
   2.750   0.5791   0.04517   0.03746  -0.0672   0.4112   0.7653
   3.000   0.5925   0.04570   0.03831  -0.0651   0.4093   0.9296
   3.250   0.6180   0.04676   0.03928  -0.0659   0.4079   1.0000
   3.500   0.6429   0.04775   0.04017  -0.0662   0.4067   1.0000
   3.750   0.6684   0.04845   0.04076  -0.0660   0.4057   1.0000
   4.000   0.6942   0.04899   0.04119  -0.0653   0.4049   1.0000
   4.500   0.7168   0.05672   0.04908  -0.0754   0.3931   1.0000
   4.750   0.7404   0.05752   0.04982  -0.0750   0.3916   1.0000
   5.000   0.7651   0.05809   0.05032  -0.0742   0.3904   1.0000
   5.250   0.7903   0.05858   0.05075  -0.0731   0.3895   1.0000
   5.750   0.7986   0.06565   0.05791  -0.0802   0.3771   1.0000
   6.000   0.8232   0.06627   0.05849  -0.0794   0.3758   1.0000
   6.250   0.8477   0.06692   0.05911  -0.0785   0.3747   1.0000
   6.500   0.8266   0.07201   0.06427  -0.0822   0.3646   1.0000
   6.750   0.8489   0.07285   0.06509  -0.0817   0.3631   1.0000
   7.000   0.8703   0.07375   0.06597  -0.0811   0.3614   1.0000
   7.250   0.8573   0.07781   0.07007  -0.0832   0.3526   1.0000
   7.500   0.8784   0.07871   0.07098  -0.0827   0.3510   1.0000
   7.750   0.9023   0.07930   0.07156  -0.0819   0.3499   1.0000
   8.000   0.8891   0.08337   0.07568  -0.0838   0.3409   1.0000
   8.250   0.9110   0.08408   0.07640  -0.0831   0.3394   1.0000
   8.750   0.9229   0.08856   0.08095  -0.0840   0.3295   1.0000
   9.000   0.9439   0.08926   0.08167  -0.0834   0.3277   1.0000
   9.250   0.9370   0.09283   0.08529  -0.0847   0.3199   1.0000
   9.500   0.9588   0.09337   0.08585  -0.0841   0.3181   1.0000
   9.750   0.9529   0.09694   0.08947  -0.0852   0.3107   1.0000
  10.000   0.9726   0.09764   0.09021  -0.0847   0.3082   1.0000
  10.250   0.9952   0.09792   0.09053  -0.0840   0.3067   1.0000
  10.500   0.9871   0.10185   0.09452  -0.0853   0.2984   1.0000
  10.750   1.0078   0.10226   0.09497  -0.0847   0.2962   1.0000
  11.250   1.0211   0.10660   0.09943  -0.0853   0.2856   1.0000
  11.500   1.0427   0.10675   0.09963  -0.0845   0.2836   1.0000
  12.000   1.0547   0.11135   0.10435  -0.0853   0.2722   1.0000
  12.250   1.0771   0.11124   0.10431  -0.0845   0.2703   1.0000
  12.750   1.0870   0.11622   0.10942  -0.0854   0.2580   1.0000
  13.000   1.1102   0.11583   0.10910  -0.0845   0.2562   1.0000
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