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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 100,000
Max Cl/Cd: 56.3 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2030-il-100000.txt
Download as CSV file: xf-sd2030-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2030-086-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4436   0.09455   0.08968  -0.0330   1.0000   0.1002
  -8.250  -0.4693   0.09274   0.08802  -0.0351   1.0000   0.1012
  -8.000  -0.4945   0.09030   0.08568  -0.0383   1.0000   0.1016
  -7.750  -0.4720   0.08568   0.08109  -0.0321   1.0000   0.1044
  -7.500  -0.4678   0.08305   0.07849  -0.0296   1.0000   0.1080
  -7.250  -0.4765   0.08019   0.07569  -0.0299   1.0000   0.1111
  -7.000  -0.5008   0.07728   0.07274  -0.0345   1.0000   0.1152
  -6.750  -0.5063   0.07320   0.06866  -0.0342   1.0000   0.1173
  -6.500  -0.4965   0.07055   0.06612  -0.0301   1.0000   0.1206
  -6.250  -0.4967   0.06777   0.06331  -0.0296   1.0000   0.1261
  -6.000  -0.5015   0.06387   0.05927  -0.0312   1.0000   0.1324
  -5.750  -0.4939   0.06137   0.05682  -0.0286   1.0000   0.1371
  -5.500  -0.4912   0.05786   0.05315  -0.0295   1.0000   0.1473
  -5.250  -0.4843   0.05523   0.05029  -0.0298   1.0000   0.1601
  -5.000  -0.4737   0.05257   0.04778  -0.0270   1.0000   0.1669
  -4.750  -0.4646   0.05003   0.04501  -0.0274   1.0000   0.1893
  -4.500  -0.4534   0.04745   0.04245  -0.0258   1.0000   0.2051
  -4.250  -0.4039   0.03493   0.02797  -0.0315   1.0000   0.0902
  -4.000  -0.3761   0.03106   0.02324  -0.0304   1.0000   0.0729
  -3.750  -0.3523   0.02820   0.02004  -0.0300   1.0000   0.0703
  -3.500  -0.3274   0.02601   0.01743  -0.0292   1.0000   0.0686
  -3.250  -0.3025   0.02427   0.01531  -0.0284   1.0000   0.0683
  -3.000  -0.2784   0.02313   0.01387  -0.0275   1.0000   0.0719
  -2.750  -0.2543   0.02189   0.01242  -0.0267   1.0000   0.0753
  -2.500  -0.2310   0.02070   0.01124  -0.0259   1.0000   0.0793
  -2.250  -0.2078   0.01986   0.01034  -0.0249   1.0000   0.0860
  -2.000  -0.1850   0.01896   0.00951  -0.0240   1.0000   0.1016
  -1.750  -0.1617   0.01762   0.00866  -0.0234   1.0000   0.1648
  -1.500  -0.1327   0.01458   0.00876  -0.0216   1.0000   1.0000
  -1.250  -0.1122   0.01475   0.00859  -0.0208   1.0000   1.0000
  -1.000  -0.0916   0.01496   0.00854  -0.0201   1.0000   1.0000
  -0.750  -0.0709   0.01521   0.00855  -0.0195   1.0000   1.0000
  -0.500  -0.0503   0.01548   0.00864  -0.0189   1.0000   1.0000
  -0.250  -0.0297   0.01579   0.00876  -0.0184   1.0000   1.0000
   0.000   0.0081   0.01642   0.00921  -0.0212   0.9946   1.0000
   0.250   0.0520   0.01706   0.00969  -0.0251   0.9856   1.0000
   0.500   0.0937   0.01762   0.01012  -0.0285   0.9759   1.0000
   0.750   0.1357   0.01816   0.01056  -0.0319   0.9662   1.0000
   1.000   0.1829   0.01873   0.01106  -0.0362   0.9572   1.0000
   1.250   0.2213   0.01903   0.01131  -0.0387   0.9453   1.0000
   1.500   0.2611   0.01931   0.01157  -0.0413   0.9333   1.0000
   1.750   0.3023   0.01953   0.01179  -0.0441   0.9213   1.0000
   2.000   0.3449   0.01965   0.01193  -0.0469   0.9093   1.0000
   2.250   0.3898   0.01965   0.01196  -0.0499   0.8974   1.0000
   2.500   0.4429   0.01942   0.01183  -0.0541   0.8869   1.0000
   2.750   0.4867   0.01909   0.01159  -0.0565   0.8735   1.0000
   3.000   0.5323   0.01860   0.01122  -0.0589   0.8600   1.0000
   3.250   0.5782   0.01796   0.01073  -0.0611   0.8464   1.0000
   3.500   0.6223   0.01719   0.01010  -0.0627   0.8318   1.0000
   3.750   0.6621   0.01643   0.00947  -0.0633   0.8144   1.0000
   4.000   0.6956   0.01577   0.00898  -0.0628   0.7917   1.0000
   4.250   0.7281   0.01515   0.00845  -0.0620   0.7642   1.0000
   4.500   0.7584   0.01463   0.00798  -0.0608   0.7286   1.0000
   4.750   0.7841   0.01437   0.00774  -0.0590   0.6799   1.0000
   5.000   0.8084   0.01436   0.00754  -0.0570   0.6149   1.0000
   5.250   0.8280   0.01478   0.00759  -0.0545   0.5337   1.0000
   5.500   0.8434   0.01559   0.00793  -0.0518   0.4516   1.0000
   5.750   0.8575   0.01658   0.00848  -0.0492   0.3781   1.0000
   6.000   0.8717   0.01768   0.00920  -0.0468   0.3163   1.0000
   6.250   0.8868   0.01882   0.01002  -0.0447   0.2630   1.0000
   6.500   0.9030   0.02004   0.01096  -0.0428   0.2207   1.0000
   6.750   0.9204   0.02131   0.01196  -0.0412   0.1882   1.0000
   7.000   0.9398   0.02255   0.01310  -0.0399   0.1624   1.0000
   7.250   0.9614   0.02400   0.01448  -0.0389   0.1434   1.0000
   7.500   0.9830   0.02533   0.01583  -0.0379   0.1273   1.0000
   7.750   1.0073   0.02700   0.01750  -0.0374   0.1152   1.0000
   8.000   1.0304   0.02868   0.01917  -0.0368   0.1036   1.0000
   8.250   1.0525   0.03026   0.02089  -0.0358   0.0936   1.0000
   8.500   1.0713   0.03196   0.02285  -0.0344   0.0833   1.0000
   8.750   1.0894   0.03401   0.02512  -0.0331   0.0737   1.0000
   9.000   1.1064   0.03633   0.02751  -0.0319   0.0650   1.0000
   9.250   1.1202   0.03846   0.03006  -0.0297   0.0585   1.0000
   9.500   1.1340   0.04214   0.03386  -0.0284   0.0537   1.0000
   9.750   1.1380   0.04482   0.03719  -0.0251   0.0508   1.0000
  10.000   1.1425   0.04758   0.04034  -0.0224   0.0476   1.0000
  10.250   1.1456   0.05087   0.04396  -0.0199   0.0461   1.0000
  10.500   1.1447   0.05442   0.04782  -0.0172   0.0454   1.0000
  10.750   1.1360   0.05826   0.05201  -0.0141   0.0451   1.0000
  11.000   1.1094   0.06230   0.05649  -0.0095   0.0459   1.0000
  11.250   1.0806   0.06669   0.06122  -0.0064   0.0466   1.0000
  11.500   1.0498   0.07179   0.06661  -0.0051   0.0476   1.0000
  11.750   1.0190   0.07767   0.07271  -0.0059   0.0484   1.0000
  12.000   0.9894   0.08453   0.07973  -0.0089   0.0496   1.0000
  12.250   0.9606   0.09279   0.08810  -0.0140   0.0508   1.0000
  12.500   0.9369   0.10192   0.09728  -0.0200   0.0521   1.0000
  12.750   0.9201   0.11089   0.10625  -0.0252   0.0532   1.0000
  13.000   0.9100   0.11883   0.11417  -0.0288   0.0540   1.0000
  13.250   0.7067   0.14902   0.14463  -0.0424   0.1315   1.0000
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