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UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il)
Reynolds number: 100,000
Max Cl/Cd: 29.08 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ui1720-il-100000-n5.txt
Download as CSV file: xf-ui1720-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3179   0.11311   0.10638  -0.0120   0.3948   0.0446
  -9.750  -0.3160   0.10885   0.10208  -0.0142   0.3873   0.0450
  -9.500  -0.3139   0.10479   0.09801  -0.0165   0.3805   0.0461
  -9.250  -0.3026   0.10257   0.09572  -0.0172   0.3706   0.0478
  -9.000  -0.2995   0.09868   0.09182  -0.0194   0.3659   0.0491
  -8.750  -0.3001   0.09388   0.08703  -0.0224   0.3627   0.0500
  -8.500  -0.3022   0.08869   0.08187  -0.0259   0.3602   0.0512
  -8.250  -0.2887   0.08706   0.08019  -0.0262   0.3535   0.0528
  -8.000  -0.2859   0.08298   0.07609  -0.0291   0.3506   0.0545
  -7.000  -0.2752   0.05036   0.04313  -0.0678   0.3463   0.0637
  -6.500  -0.2371   0.03850   0.03022  -0.0798   0.3390   0.0709
  -6.250  -0.2125   0.03759   0.02916  -0.0801   0.3342   0.0731
  -6.000  -0.1881   0.03319   0.02379  -0.0834   0.3310   0.0776
  -5.750  -0.1624   0.03262   0.02322  -0.0832   0.3271   0.0794
  -5.500  -0.1362   0.03168   0.02211  -0.0833   0.3234   0.0819
  -5.250  -0.1092   0.02986   0.01975  -0.0841   0.3203   0.0853
  -5.000  -0.0825   0.02883   0.01846  -0.0842   0.3176   0.0876
  -4.750  -0.0557   0.02821   0.01769  -0.0841   0.3152   0.0899
  -4.500  -0.0284   0.02743   0.01662  -0.0841   0.3131   0.0924
  -4.250  -0.0005   0.02661   0.01538  -0.0841   0.3113   0.0953
  -4.000   0.0271   0.02591   0.01456  -0.0840   0.3095   0.0973
  -3.750   0.0547   0.02544   0.01402  -0.0838   0.3077   0.0994
  -3.500   0.0825   0.02501   0.01348  -0.0836   0.3060   0.1021
  -3.250   0.1106   0.02457   0.01284  -0.0834   0.3044   0.1049
  -3.000   0.1388   0.02416   0.01225  -0.0831   0.3029   0.1071
  -2.750   0.1662   0.02384   0.01195  -0.0828   0.3014   0.1097
  -2.500   0.1939   0.02363   0.01169  -0.0826   0.3001   0.1131
  -2.250   0.2218   0.02344   0.01139  -0.0823   0.2989   0.1167
  -2.000   0.2496   0.02325   0.01111  -0.0819   0.2978   0.1200
  -1.750   0.2771   0.02312   0.01099  -0.0817   0.2967   0.1242
  -1.500   0.3049   0.02309   0.01090  -0.0814   0.2957   0.1300
  -1.250   0.3325   0.02306   0.01084  -0.0811   0.2949   0.1361
  -1.000   0.3602   0.02312   0.01086  -0.0808   0.2939   0.1438
  -0.750   0.3877   0.02317   0.01094  -0.0806   0.2930   0.1540
  -0.500   0.4152   0.02320   0.01106  -0.0803   0.2920   0.1687
  -0.250   0.4427   0.02325   0.01123  -0.0800   0.2910   0.1896
   0.000   0.4700   0.02333   0.01145  -0.0798   0.2899   0.2216
   0.250   0.4970   0.02342   0.01175  -0.0795   0.2890   0.2684
   0.500   0.5241   0.02355   0.01211  -0.0793   0.2882   0.3320
   0.750   0.5510   0.02369   0.01252  -0.0790   0.2874   0.4135
   1.000   0.5769   0.02379   0.01299  -0.0785   0.2867   0.5194
   1.250   0.5997   0.02375   0.01345  -0.0771   0.2860   0.6658
   1.500   0.6252   0.02356   0.01376  -0.0757   0.2853   0.9996
   1.750   0.6523   0.02413   0.01423  -0.0755   0.2846   0.9996
   2.000   0.6791   0.02472   0.01475  -0.0753   0.2840   0.9996
   2.250   0.7057   0.02535   0.01531  -0.0750   0.2834   0.9996
   2.500   0.7320   0.02600   0.01592  -0.0747   0.2828   0.9996
   2.750   0.7580   0.02668   0.01657  -0.0744   0.2822   0.9996
   3.000   0.7837   0.02740   0.01726  -0.0741   0.2817   0.9996
   3.250   0.8091   0.02815   0.01800  -0.0738   0.2812   0.9996
   3.500   0.8343   0.02894   0.01879  -0.0734   0.2807   0.9996
   3.750   0.8592   0.02973   0.01957  -0.0730   0.2800   0.9996
   4.000   0.8841   0.03049   0.02033  -0.0726   0.2793   0.9996
   4.250   0.9088   0.03127   0.02108  -0.0723   0.2786   0.9996
   4.500   0.9333   0.03209   0.02188  -0.0719   0.2779   0.9996
   4.750   0.9574   0.03299   0.02280  -0.0715   0.2773   0.9996
   5.000   0.9808   0.03400   0.02383  -0.0710   0.2769   0.9996
   5.250   1.0039   0.03508   0.02494  -0.0706   0.2764   0.9996
   5.500   1.0264   0.03627   0.02616  -0.0702   0.2760   0.9996
   5.750   1.0465   0.03769   0.02769  -0.0696   0.2755   0.9996
   6.000   1.0635   0.03942   0.02962  -0.0690   0.2750   0.9996
   6.250   1.0780   0.04145   0.03187  -0.0683   0.2743   0.9996
   6.500   1.0873   0.04406   0.03477  -0.0675   0.2730   0.9996
   6.750   1.0913   0.04729   0.03830  -0.0669   0.2714   0.9996
   7.000   1.0878   0.05148   0.04278  -0.0665   0.2699   0.9996
   7.250   1.0732   0.05674   0.04833  -0.0665   0.2672   0.9996
   7.500   1.0547   0.06233   0.05412  -0.0672   0.2646   0.9996
   7.750   1.0480   0.06609   0.05795  -0.0673   0.2626   0.9996
   8.000   1.0537   0.06846   0.06035  -0.0671   0.2614   0.9996
   8.250   1.0634   0.07046   0.06235  -0.0668   0.2604   0.9996
   8.500   1.0757   0.07222   0.06412  -0.0663   0.2597   0.9996
   8.750   1.0880   0.07404   0.06594  -0.0658   0.2590   0.9996
  11.750   0.7458   0.13759   0.13067  -0.0735   0.2107   0.9996
  12.000   0.7425   0.14014   0.13327  -0.0740   0.2080   0.9996
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