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UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il)
Reynolds number: 100,000
Max Cl/Cd: 17.54 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ui1720-il-100000.txt
Download as CSV file: xf-ui1720-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2829   0.11968   0.11359  -0.0083   0.4648   0.1010
  -9.500  -0.2799   0.11713   0.11098  -0.0107   0.4542   0.1051
  -9.250  -0.3055   0.11662   0.11063  -0.0190   0.4595   0.1069
  -9.000  -0.2662   0.11030   0.10406  -0.0137   0.4363   0.1095
  -8.750  -0.2538   0.10758   0.10120  -0.0139   0.4283   0.1142
  -8.500  -0.2720   0.10649   0.10022  -0.0212   0.4292   0.1189
  -8.250  -0.2509   0.10148   0.09515  -0.0188   0.4197   0.1212
  -8.000  -0.2339   0.09855   0.09211  -0.0178   0.4129   0.1251
  -7.750  -0.2388   0.09660   0.09018  -0.0227   0.4113   0.1317
  -7.500  -0.2339   0.09271   0.08625  -0.0246   0.4082   0.1345
  -7.250  -0.2117   0.08988   0.08339  -0.0221   0.4027   0.1394
  -7.000  -0.2290   0.08746   0.08106  -0.0411   0.4046   0.1480
  -6.750  -0.2086   0.08387   0.07744  -0.0297   0.3986   0.1501
  -6.500  -0.1896   0.08163   0.07512  -0.0268   0.3945   0.1560
  -6.250  -0.1860   0.07745   0.07094  -0.0393   0.3937   0.1655
  -6.000  -0.1684   0.07543   0.06882  -0.0335   0.3903   0.1693
  -5.750  -0.1542   0.07137   0.06465  -0.0456   0.3889   0.1829
  -5.500  -0.1305   0.06881   0.06192  -0.0562   0.3871   0.1996
  -5.250  -0.1181   0.06559   0.05886  -0.0495   0.3846   0.2015
  -5.000  -0.1021   0.06398   0.05730  -0.0446   0.3822   0.2064
  -4.750  -0.0799   0.06058   0.05380  -0.0512   0.3804   0.2217
  -4.500  -0.0609   0.05899   0.05221  -0.0494   0.3784   0.2306
  -4.250  -0.0044   0.04263   0.03465  -0.0777   0.3776   0.1664
  -4.000   0.0249   0.03910   0.03079  -0.0800   0.3758   0.1577
  -3.750   0.0554   0.03584   0.02703  -0.0825   0.3741   0.1550
  -3.500   0.0851   0.03377   0.02453  -0.0837   0.3726   0.1548
  -3.250   0.1142   0.03246   0.02287  -0.0844   0.3711   0.1565
  -3.000   0.1433   0.03144   0.02150  -0.0848   0.3697   0.1578
  -2.750   0.1723   0.03069   0.02048  -0.0851   0.3684   0.1608
  -2.500   0.2014   0.03005   0.01959  -0.0851   0.3671   0.1631
  -2.250   0.2295   0.02936   0.01881  -0.0851   0.3658   0.1657
  -2.000   0.2569   0.02907   0.01857  -0.0849   0.3645   0.1702
  -1.750   0.2847   0.02895   0.01842  -0.0847   0.3636   0.1753
  -1.500   0.3128   0.02892   0.01827  -0.0845   0.3629   0.1803
  -1.250   0.3397   0.02880   0.01828  -0.0843   0.3624   0.1865
  -1.000   0.3668   0.02901   0.01853  -0.0840   0.3619   0.1958
  -0.750   0.3933   0.02916   0.01881  -0.0837   0.3617   0.2060
  -0.500   0.4197   0.02947   0.01922  -0.0834   0.3615   0.2206
  -0.250   0.4454   0.02983   0.01981  -0.0831   0.3616   0.2426
   0.000   0.4708   0.03024   0.02051  -0.0828   0.3618   0.2800
   0.250   0.4953   0.03062   0.02137  -0.0825   0.3622   0.3579
   0.500   0.5185   0.03095   0.02246  -0.0819   0.3628   0.5143
   0.750   0.5336   0.03108   0.02352  -0.0790   0.3633   0.7527
   1.000   0.5610   0.03198   0.02460  -0.0790   0.3635   0.9996
   1.250   0.5852   0.03344   0.02599  -0.0791   0.3638   0.9996
   1.500   0.6088   0.03508   0.02757  -0.0792   0.3649   0.9996
   1.750   0.6320   0.03681   0.02925  -0.0793   0.3662   0.9996
   2.000   0.6554   0.03858   0.03094  -0.0794   0.3675   0.9996
   2.250   0.6795   0.04039   0.03262  -0.0794   0.3687   0.9996
   2.500   0.5680   0.06787   0.06203  -0.1091   0.4753   0.9996
   2.750   0.5980   0.06953   0.06352  -0.1083   0.4722   0.9996
   3.000   0.6330   0.07147   0.06531  -0.1074   0.4705   0.9996
   3.250   0.6658   0.07391   0.06760  -0.1059   0.4694   0.9996
   3.500   0.6342   0.07601   0.06969  -0.1068   0.4516   0.9996
   3.750   0.6693   0.07820   0.07175  -0.1058   0.4501   0.9996
   4.000   0.7023   0.08120   0.07463  -0.1049   0.4487   0.9996
   4.250   0.6640   0.08277   0.07619  -0.1054   0.4314   0.9996
   4.500   0.6984   0.08519   0.07851  -0.1045   0.4300   0.9996
   4.750   0.7359   0.08808   0.08133  -0.1035   0.4291   0.9996
   5.000   0.6825   0.08994   0.08318  -0.1046   0.4120   0.9996
   5.250   0.7136   0.09242   0.08559  -0.1038   0.4104   0.9996
   5.500   0.7506   0.09544   0.08853  -0.1028   0.4093   0.9996
   5.750   0.6979   0.09735   0.09045  -0.1041   0.3933   0.9996
   6.000   0.7264   0.09973   0.09277  -0.1032   0.3912   0.9996
   6.250   0.7593   0.10268   0.09566  -0.1024   0.3899   0.9996
   6.500   0.7962   0.10638   0.09932  -0.1014   0.3891   0.9996
   6.750   0.7302   0.10753   0.10049  -0.1035   0.3732   0.9996
   7.000   0.7577   0.11016   0.10307  -0.1026   0.3713   0.9996
   7.250   0.7912   0.11340   0.10627  -0.1017   0.3701   0.9996
   7.500   0.8297   0.11760   0.11044  -0.1007   0.3693   0.9996
   7.750   0.7584   0.11803   0.11090  -0.1033   0.3537   0.9996
   8.000   0.7834   0.12080   0.11364  -0.1026   0.3518   0.9996
   8.250   0.8133   0.12419   0.11700  -0.1018   0.3507   0.9996
   8.500   0.8484   0.12846   0.12126  -0.1008   0.3499   0.9996
   8.750   0.7794   0.12890   0.12173  -0.1039   0.3355   0.9996
   9.000   0.8016   0.13158   0.12439  -0.1033   0.3333   0.9996
   9.250   0.8284   0.13486   0.12766  -0.1026   0.3319   0.9996
   9.500   0.8596   0.13895   0.13175  -0.1018   0.3310   0.9996
   9.750   0.7987   0.14006   0.13289  -0.1054   0.3196   0.9996
  10.000   0.8145   0.14253   0.13536  -0.1051   0.3163   0.9996
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