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SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD2083 (9.0%) (sd2083-il)
Reynolds number: 100,000
Max Cl/Cd: 58.06 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2083-il-100000.txt
Download as CSV file: xf-sd2083-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2083 (9.0%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3910   0.10660   0.10164  -0.0302   1.0000   0.0853
  -9.250  -0.4009   0.10461   0.09975  -0.0343   1.0000   0.0877
  -9.000  -0.4165   0.10287   0.09814  -0.0391   1.0000   0.0883
  -8.750  -0.3958   0.09692   0.09217  -0.0357   1.0000   0.0904
  -8.500  -0.3839   0.09361   0.08886  -0.0342   1.0000   0.0940
  -8.250  -0.3837   0.09087   0.08619  -0.0347   1.0000   0.0971
  -8.000  -0.3944   0.08860   0.08404  -0.0359   1.0000   0.1001
  -7.750  -0.4206   0.08732   0.08293  -0.0363   1.0000   0.1014
  -7.500  -0.4472   0.08575   0.08144  -0.0382   1.0000   0.1021
  -7.250  -0.4723   0.08419   0.07984  -0.0396   1.0000   0.1025
  -7.000  -0.4469   0.07957   0.07539  -0.0311   1.0000   0.1057
  -6.750  -0.4510   0.07750   0.07337  -0.0287   1.0000   0.1081
  -6.500  -0.4593   0.07511   0.07100  -0.0280   1.0000   0.1118
  -6.250  -0.4814   0.07220   0.06781  -0.0349   1.0000   0.1169
  -6.000  -0.4729   0.06860   0.06443  -0.0299   1.0000   0.1190
  -5.750  -0.4691   0.06633   0.06219  -0.0274   1.0000   0.1227
  -5.500  -0.4695   0.06253   0.05815  -0.0310   1.0000   0.1321
  -5.250  -0.4624   0.06003   0.05576  -0.0279   1.0000   0.1357
  -5.000  -0.4555   0.05674   0.05227  -0.0294   1.0000   0.1471
  -4.750  -0.4462   0.05416   0.04954  -0.0294   1.0000   0.1608
  -4.500  -0.4359   0.05171   0.04703  -0.0286   1.0000   0.1752
  -4.250  -0.4250   0.04933   0.04465  -0.0273   1.0000   0.1905
  -4.000  -0.4123   0.04697   0.04226  -0.0263   1.0000   0.2060
  -3.750  -0.3538   0.03469   0.02791  -0.0331   1.0000   0.0859
  -3.500  -0.3273   0.03091   0.02339  -0.0324   1.0000   0.0720
  -3.250  -0.2999   0.02824   0.02028  -0.0324   0.9989   0.0678
  -3.000  -0.2609   0.02593   0.01732  -0.0340   0.9949   0.0652
  -2.750  -0.2248   0.02444   0.01547  -0.0354   0.9902   0.0660
  -2.500  -0.1867   0.02354   0.01436  -0.0374   0.9852   0.0722
  -2.250  -0.1514   0.02242   0.01308  -0.0387   0.9803   0.0760
  -2.000  -0.1168   0.02147   0.01222  -0.0400   0.9746   0.0851
  -1.750  -0.0798   0.02049   0.01141  -0.0418   0.9700   0.1198
  -1.500  -0.0242   0.01698   0.01113  -0.0463   0.9703   1.0000
  -1.250   0.0077   0.01727   0.01105  -0.0476   0.9621   1.0000
  -1.000   0.0482   0.01772   0.01115  -0.0505   0.9557   1.0000
  -0.750   0.0804   0.01803   0.01123  -0.0519   0.9473   1.0000
  -0.500   0.1168   0.01842   0.01140  -0.0540   0.9400   1.0000
  -0.250   0.1532   0.01876   0.01154  -0.0561   0.9319   1.0000
   0.000   0.1851   0.01910   0.01173  -0.0573   0.9231   1.0000
   0.250   0.2279   0.01942   0.01192  -0.0604   0.9162   1.0000
   0.500   0.2560   0.01971   0.01212  -0.0608   0.9059   1.0000
   0.750   0.2942   0.01998   0.01230  -0.0629   0.8978   1.0000
   1.000   0.3327   0.02016   0.01242  -0.0650   0.8890   1.0000
   1.250   0.3629   0.02039   0.01261  -0.0656   0.8784   1.0000
   1.500   0.4176   0.02031   0.01252  -0.0703   0.8726   1.0000
   1.750   0.4466   0.02042   0.01262  -0.0705   0.8608   1.0000
   2.000   0.4791   0.02046   0.01267  -0.0711   0.8496   1.0000
   2.250   0.5189   0.02028   0.01253  -0.0726   0.8404   1.0000
   2.500   0.5593   0.01993   0.01222  -0.0740   0.8312   1.0000
   2.750   0.5886   0.01978   0.01212  -0.0736   0.8189   1.0000
   3.000   0.6190   0.01955   0.01196  -0.0732   0.8068   1.0000
   3.250   0.6502   0.01922   0.01170  -0.0728   0.7950   1.0000
   3.500   0.6823   0.01879   0.01135  -0.0723   0.7835   1.0000
   3.750   0.7146   0.01828   0.01094  -0.0718   0.7719   1.0000
   4.000   0.7424   0.01789   0.01064  -0.0706   0.7573   1.0000
   4.250   0.7683   0.01755   0.01038  -0.0692   0.7403   1.0000
   4.500   0.7956   0.01710   0.01002  -0.0678   0.7223   1.0000
   4.750   0.8248   0.01656   0.00957  -0.0665   0.7033   1.0000
   5.000   0.8488   0.01628   0.00936  -0.0647   0.6779   1.0000
   5.250   0.8736   0.01600   0.00911  -0.0630   0.6490   1.0000
   5.500   0.8968   0.01587   0.00898  -0.0611   0.6139   1.0000
   5.750   0.9188   0.01591   0.00898  -0.0592   0.5717   1.0000
   6.000   0.9389   0.01617   0.00911  -0.0571   0.5228   1.0000
   6.250   0.9572   0.01668   0.00941  -0.0549   0.4707   1.0000
   6.500   0.9740   0.01742   0.00987  -0.0527   0.4199   1.0000
   6.750   0.9899   0.01827   0.01052  -0.0506   0.3720   1.0000
   7.000   1.0052   0.01921   0.01130  -0.0485   0.3280   1.0000
   7.250   1.0200   0.02023   0.01214  -0.0464   0.2875   1.0000
   7.500   1.0338   0.02135   0.01305  -0.0443   0.2493   1.0000
   7.750   1.0462   0.02245   0.01404  -0.0421   0.2104   1.0000
   8.000   1.0558   0.02349   0.01494  -0.0397   0.1698   1.0000
   8.250   1.0644   0.02469   0.01595  -0.0373   0.1285   1.0000
   8.500   1.0681   0.02671   0.01766  -0.0342   0.0883   1.0000
   8.750   1.0725   0.02897   0.01976  -0.0310   0.0637   1.0000
   9.000   1.0833   0.03110   0.02188  -0.0286   0.0532   1.0000
   9.250   1.1044   0.03382   0.02463  -0.0276   0.0477   1.0000
   9.500   1.1272   0.03618   0.02718  -0.0267   0.0438   1.0000
   9.750   1.1485   0.03891   0.02991  -0.0263   0.0403   1.0000
  10.000   1.1656   0.04206   0.03340  -0.0251   0.0381   1.0000
  10.250   1.1787   0.04513   0.03688  -0.0233   0.0373   1.0000
  10.500   1.1859   0.04852   0.04070  -0.0211   0.0371   1.0000
  10.750   1.1866   0.05202   0.04464  -0.0185   0.0370   1.0000
  11.000   1.1812   0.05542   0.04840  -0.0154   0.0372   1.0000
  11.250   1.1714   0.05883   0.05212  -0.0124   0.0374   1.0000
  11.500   1.1580   0.06245   0.05602  -0.0097   0.0376   1.0000
  11.750   1.1422   0.06635   0.06019  -0.0077   0.0379   1.0000
  12.000   1.1257   0.07050   0.06456  -0.0065   0.0382   1.0000
  12.250   1.1074   0.07510   0.06938  -0.0061   0.0385   1.0000
  12.500   1.0890   0.08018   0.07463  -0.0065   0.0388   1.0000
  12.750   1.0705   0.08590   0.08051  -0.0078   0.0391   1.0000
  13.000   1.0548   0.09150   0.08628  -0.0095   0.0395   1.0000
  13.250   1.0313   0.09745   0.09242  -0.0131   0.0399   1.0000
  13.500   0.9924   0.10742   0.10261  -0.0211   0.0408   1.0000
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