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STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: STRAND AIRFOIL (strand-il)
Reynolds number: 500,000
Max Cl/Cd: 101.56 at α=11.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-strand-il-500000-n5.txt
Download as CSV file: xf-strand-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5360   0.08619   0.08170   0.0146   0.3745   0.0237
  -9.000  -0.5568   0.07567   0.07110   0.0033   0.3745   0.0237
  -8.750  -0.5751   0.06736   0.06266  -0.0090   0.3745   0.0237
  -8.500  -0.5773   0.06141   0.05648  -0.0184   0.3745   0.0237
  -8.250  -0.5712   0.05712   0.05197  -0.0228   0.3744   0.0237
  -8.000  -0.5598   0.05341   0.04803  -0.0258   0.3743   0.0237
  -7.750  -0.5445   0.05009   0.04450  -0.0281   0.3742   0.0237
  -7.500  -0.5263   0.04707   0.04126  -0.0299   0.3741   0.0237
  -7.000  -0.4844   0.04150   0.03583  -0.0312   0.3739   0.0232
  -6.750  -0.4628   0.03884   0.03303  -0.0327   0.3737   0.0228
  -6.500  -0.4395   0.03625   0.03021  -0.0341   0.3736   0.0224
  -6.250  -0.4145   0.03396   0.02768  -0.0352   0.3735   0.0223
  -6.000  -0.3884   0.03204   0.02552  -0.0361   0.3733   0.0225
  -5.750  -0.3617   0.03023   0.02348  -0.0368   0.3732   0.0224
  -5.500  -0.3343   0.02846   0.02150  -0.0374   0.3730   0.0221
  -5.250  -0.3064   0.02688   0.01971  -0.0379   0.3729   0.0218
  -5.000  -0.2780   0.02551   0.01814  -0.0383   0.3727   0.0217
  -4.750  -0.2494   0.02432   0.01678  -0.0386   0.3726   0.0217
  -4.500  -0.2206   0.02328   0.01559  -0.0388   0.3724   0.0217
  -4.250  -0.1917   0.02236   0.01454  -0.0390   0.3722   0.0218
  -4.000  -0.1627   0.02154   0.01360  -0.0392   0.3719   0.0219
  -3.750  -0.1336   0.02081   0.01277  -0.0393   0.3716   0.0221
  -3.500  -0.1044   0.02015   0.01202  -0.0394   0.3714   0.0222
  -3.250  -0.0752   0.01956   0.01137  -0.0395   0.3713   0.0224
  -3.000  -0.0460   0.01903   0.01078  -0.0396   0.3711   0.0225
  -2.750  -0.0168   0.01855   0.01026  -0.0397   0.3709   0.0226
  -2.500   0.0125   0.01812   0.00979  -0.0398   0.3708   0.0228
  -2.250   0.0419   0.01779   0.00943  -0.0399   0.3706   0.0231
  -2.000   0.0713   0.01757   0.00916  -0.0399   0.3704   0.0235
  -1.750   0.1008   0.01735   0.00891  -0.0400   0.3703   0.0236
  -1.500   0.1302   0.01706   0.00862  -0.0402   0.3701   0.0237
  -1.250   0.1596   0.01666   0.00825  -0.0404   0.3699   0.0238
  -1.000   0.1891   0.01631   0.00793  -0.0406   0.3698   0.0240
  -0.750   0.2188   0.01607   0.00771  -0.0409   0.3696   0.0243
  -0.500   0.2486   0.01590   0.00756  -0.0412   0.3694   0.0245
  -0.250   0.2784   0.01577   0.00745  -0.0415   0.3693   0.0249
   0.000   0.3082   0.01569   0.00738  -0.0417   0.3691   0.0253
   0.250   0.3380   0.01563   0.00734  -0.0420   0.3690   0.0257
   0.500   0.3678   0.01561   0.00732  -0.0422   0.3688   0.0262
   0.750   0.3976   0.01561   0.00734  -0.0425   0.3687   0.0267
   1.000   0.4273   0.01566   0.00739  -0.0427   0.3685   0.0273
   1.250   0.4570   0.01567   0.00742  -0.0429   0.3684   0.0283
   1.500   0.4866   0.01573   0.00750  -0.0432   0.3682   0.0293
   1.750   0.5161   0.01583   0.00761  -0.0434   0.3681   0.0300
   2.000   0.5456   0.01596   0.00775  -0.0436   0.3680   0.0308
   2.250   0.5749   0.01611   0.00791  -0.0437   0.3678   0.0318
   2.500   0.6042   0.01628   0.00809  -0.0439   0.3677   0.0331
   2.750   0.6335   0.01646   0.00830  -0.0441   0.3675   0.0354
   3.250   0.6940   0.01602   0.00878  -0.0456   0.3672   0.3755
   3.500   0.7234   0.01601   0.00908  -0.0461   0.3669   0.4720
   3.750   0.7525   0.01613   0.00939  -0.0463   0.3666   0.5283
   4.000   0.7814   0.01625   0.00975  -0.0466   0.3664   0.5980
   4.250   0.8100   0.01642   0.01012  -0.0468   0.3663   0.6494
   4.500   0.8375   0.01647   0.01053  -0.0467   0.3661   0.7526
   4.750   0.8627   0.01654   0.01089  -0.0461   0.3659   0.8372
   5.000   0.8859   0.01659   0.01116  -0.0448   0.3657   1.0000
   5.250   0.9147   0.01692   0.01151  -0.0451   0.3655   1.0000
   5.500   0.9437   0.01711   0.01169  -0.0453   0.3650   1.0000
   5.750   0.9727   0.01724   0.01182  -0.0454   0.3645   1.0000
   6.000   1.0017   0.01740   0.01196  -0.0455   0.3640   1.0000
   6.250   1.0303   0.01767   0.01224  -0.0457   0.3637   1.0000
   6.500   1.0588   0.01797   0.01256  -0.0459   0.3634   1.0000
   6.750   1.0873   0.01823   0.01284  -0.0461   0.3631   1.0000
   7.000   1.1158   0.01851   0.01313  -0.0462   0.3627   1.0000
   7.250   1.1440   0.01884   0.01348  -0.0464   0.3623   1.0000
   7.500   1.1720   0.01923   0.01389  -0.0466   0.3619   1.0000
   7.750   1.1995   0.01965   0.01443  -0.0469   0.3610   1.0000
   8.000   1.2265   0.02021   0.01513  -0.0473   0.3599   1.0000
   8.250   1.2533   0.02078   0.01582  -0.0476   0.3587   1.0000
   8.500   1.2802   0.02131   0.01644  -0.0479   0.3576   1.0000
   8.750   1.3081   0.02147   0.01667  -0.0481   0.3562   1.0000
   9.000   1.3375   0.02111   0.01633  -0.0480   0.3547   1.0000
   9.250   1.3681   0.02041   0.01559  -0.0479   0.3532   1.0000
   9.500   1.3985   0.01978   0.01493  -0.0477   0.3521   1.0000
   9.750   1.4293   0.01907   0.01416  -0.0476   0.3510   1.0000
  10.000   1.4582   0.01876   0.01395  -0.0477   0.3479   1.0000
  10.250   1.4881   0.01818   0.01346  -0.0478   0.3425   1.0000
  10.500   1.5205   0.01701   0.01224  -0.0477   0.3392   1.0000
  10.750   1.5458   0.01788   0.01336  -0.0482   0.3325   1.0000
  11.000   1.5722   0.01841   0.01405  -0.0485   0.3255   1.0000
  11.250   1.6017   0.01814   0.01383  -0.0487   0.3081   1.0000
  11.500   1.6362   0.01611   0.01110  -0.0487   0.2607   1.0000
  11.750   1.6543   0.01822   0.01313  -0.0497   0.2323   1.0000
  12.000   1.6673   0.02132   0.01620  -0.0514   0.2026   1.0000
  12.250   1.6559   0.03140   0.02653  -0.0602   0.1807   1.0000
  12.500   1.5874   0.04617   0.04162  -0.0722   0.1857   1.0000
  12.750   1.5470   0.05335   0.04884  -0.0743   0.1818   1.0000
  13.000   1.5199   0.05897   0.05445  -0.0756   0.1736   1.0000
  13.250   1.5012   0.06397   0.05941  -0.0766   0.1647   1.0000
  13.500   1.4874   0.06846   0.06385  -0.0775   0.1550   1.0000
  13.750   1.4792   0.07238   0.06772  -0.0782   0.1446   1.0000
  14.000   1.4713   0.07630   0.07160  -0.0789   0.1349   1.0000
  14.250   1.4642   0.08018   0.07544  -0.0796   0.1256   1.0000
  14.750   1.4552   0.08734   0.08251  -0.0807   0.1066   1.0000
  15.000   1.4512   0.09094   0.08608  -0.0814   0.0981   1.0000
  15.250   1.4466   0.09464   0.08974  -0.0820   0.0900   1.0000
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