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UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il)
Reynolds number: 50,000
Max Cl/Cd: 17.85 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ui1720-il-50000-n5.txt
Download as CSV file: xf-ui1720-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3507   0.14322   0.13665   0.0053   1.0004   0.1039
 -11.000  -0.3537   0.14127   0.13478   0.0027   1.0004   0.1063
 -10.750  -0.3575   0.13914   0.13274   0.0001   1.0004   0.1069
 -10.500  -0.3320   0.13348   0.12719   0.0022   1.0004   0.1110
 -10.250  -0.3252   0.13045   0.12425   0.0013   1.0004   0.1145
 -10.000  -0.3242   0.12781   0.12172  -0.0006   1.0004   0.1173
  -9.750  -0.3265   0.12534   0.11936  -0.0030   1.0004   0.1185
  -9.250  -0.2889   0.11769   0.11035  -0.0067   0.5267   0.1246
  -9.000  -0.3008   0.11131   0.10401  -0.0133   0.5338   0.0957
  -8.500  -0.2816   0.10442   0.09662  -0.0149   0.4708   0.0936
  -8.250  -0.2766   0.10087   0.09299  -0.0169   0.4568   0.0935
  -8.000  -0.2712   0.09727   0.08929  -0.0188   0.4458   0.0928
  -7.750  -0.2670   0.09361   0.08559  -0.0211   0.4369   0.0930
  -7.500  -0.2650   0.08993   0.08186  -0.0238   0.4305   0.0939
  -7.250  -0.2617   0.08588   0.07778  -0.0275   0.4248   0.0944
  -7.000  -0.2554   0.08122   0.07310  -0.0325   0.4193   0.0948
  -6.750  -0.2491   0.07458   0.06637  -0.0419   0.4161   0.0959
  -6.500  -0.2318   0.07361   0.06529  -0.0398   0.4081   0.0987
  -6.250  -0.2171   0.06935   0.06096  -0.0444   0.4031   0.1005
  -6.000  -0.2008   0.06409   0.05554  -0.0509   0.3990   0.1029
  -5.750  -0.1821   0.05707   0.04817  -0.0599   0.3958   0.1051
  -5.500  -0.1599   0.05188   0.04256  -0.0657   0.3920   0.1081
  -5.250  -0.1362   0.04991   0.04041  -0.0669   0.3876   0.1109
  -5.000  -0.1097   0.04663   0.03679  -0.0702   0.3834   0.1146
  -4.750  -0.0803   0.04250   0.03198  -0.0746   0.3797   0.1181
  -4.500  -0.0527   0.04064   0.02986  -0.0758   0.3758   0.1212
  -4.250  -0.0247   0.03920   0.02818  -0.0766   0.3723   0.1240
  -4.000   0.0051   0.03765   0.02619  -0.0779   0.3692   0.1279
  -3.750   0.0361   0.03592   0.02401  -0.0793   0.3658   0.1317
  -3.500   0.0655   0.03473   0.02259  -0.0800   0.3623   0.1344
  -3.250   0.0938   0.03404   0.02182  -0.0801   0.3589   0.1384
  -3.000   0.1227   0.03329   0.02082  -0.0804   0.3560   0.1426
  -2.750   0.1521   0.03254   0.01970  -0.0806   0.3534   0.1465
  -2.500   0.1803   0.03207   0.01909  -0.0806   0.3513   0.1510
  -2.250   0.2084   0.03179   0.01866  -0.0805   0.3496   0.1567
  -2.000   0.2370   0.03147   0.01820  -0.0804   0.3479   0.1626
  -1.750   0.2644   0.03127   0.01806  -0.0802   0.3462   0.1687
  -1.500   0.2919   0.03121   0.01796  -0.0799   0.3446   0.1777
  -1.250   0.3196   0.03118   0.01794  -0.0797   0.3430   0.1870
  -1.000   0.3474   0.03124   0.01796  -0.0795   0.3416   0.2003
  -0.750   0.3748   0.03134   0.01811  -0.0794   0.3402   0.2172
  -0.500   0.4020   0.03146   0.01836  -0.0793   0.3389   0.2402
  -0.250   0.4289   0.03162   0.01868  -0.0791   0.3377   0.2748
   0.000   0.4554   0.03176   0.01910  -0.0790   0.3365   0.3275
   0.250   0.4809   0.03188   0.01959  -0.0786   0.3352   0.4104
   0.500   0.5040   0.03192   0.02012  -0.0776   0.3340   0.5304
   0.750   0.5211   0.03174   0.02056  -0.0748   0.3328   0.7078
   1.000   0.5489   0.03195   0.02087  -0.0741   0.3315   0.9996
   1.250   0.5758   0.03282   0.02146  -0.0741   0.3304   0.9996
   1.500   0.6004   0.03389   0.02248  -0.0741   0.3292   0.9996
   1.750   0.6246   0.03505   0.02360  -0.0740   0.3283   0.9996
   2.000   0.6482   0.03631   0.02483  -0.0739   0.3275   0.9996
   2.250   0.6710   0.03767   0.02618  -0.0738   0.3268   0.9996
   2.500   0.6930   0.03914   0.02766  -0.0737   0.3260   0.9996
   2.750   0.7140   0.04074   0.02928  -0.0737   0.3254   0.9996
   3.000   0.7340   0.04248   0.03107  -0.0736   0.3248   0.9996
   3.250   0.7527   0.04438   0.03302  -0.0736   0.3240   0.9996
   3.500   0.7700   0.04642   0.03512  -0.0737   0.3228   0.9996
   3.750   0.7860   0.04857   0.03733  -0.0737   0.3215   0.9996
   4.000   0.8007   0.05087   0.03969  -0.0739   0.3202   0.9996
   4.250   0.8131   0.05353   0.04241  -0.0741   0.3193   0.9996
   4.500   0.8214   0.05673   0.04571  -0.0747   0.3187   0.9996
   4.750   0.8254   0.06049   0.04959  -0.0756   0.3183   0.9996
   5.000   0.8277   0.06434   0.05351  -0.0766   0.3174   0.9996
   5.250   0.8325   0.06772   0.05693  -0.0774   0.3161   0.9996
   5.500   0.8399   0.07071   0.05992  -0.0779   0.3148   0.9996
   5.750   0.8440   0.07420   0.06343  -0.0787   0.3138   0.9996
   6.000   0.8461   0.07779   0.06703  -0.0794   0.3131   0.9996
   6.250   0.8625   0.07974   0.06894  -0.0788   0.3120   0.9996
   6.500   0.8185   0.08893   0.07825  -0.0848   0.3097   0.9996
   6.750   0.8043   0.09424   0.08361  -0.0873   0.3083   0.9996
   7.000   0.7962   0.09867   0.08807  -0.0891   0.3062   0.9996
   7.250   0.7939   0.10243   0.09183  -0.0902   0.3041   0.9996
   7.500   0.7950   0.10596   0.09539  -0.0911   0.3028   0.9996
   7.750   0.7972   0.10939   0.09882  -0.0919   0.3017   0.9996
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