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UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il)
Reynolds number: 200,000
Max Cl/Cd: 44.88 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ui1720-il-200000-n5.txt
Download as CSV file: xf-ui1720-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5616   0.03194   0.02632  -0.0877   0.5612   0.0365
  -9.500  -0.5377   0.03242   0.02648  -0.0870   0.4595   0.0374
  -9.250  -0.5147   0.03173   0.02546  -0.0874   0.4067   0.0387
  -8.750  -0.3962   0.06733   0.06163  -0.0413   0.3173   0.0369
  -8.500  -0.4456   0.02706   0.01961  -0.0900   0.3399   0.0452
  -8.250  -0.4198   0.02672   0.01911  -0.0899   0.3281   0.0467
  -8.000  -0.3937   0.02642   0.01866  -0.0897   0.3190   0.0485
  -7.500  -0.3420   0.02503   0.01680  -0.0898   0.3070   0.0527
  -7.250  -0.3156   0.02442   0.01598  -0.0897   0.3024   0.0550
  -7.000  -0.2895   0.02361   0.01487  -0.0897   0.2985   0.0572
  -6.750  -0.2628   0.02347   0.01466  -0.0893   0.2949   0.0588
  -6.500  -0.2361   0.02294   0.01391  -0.0891   0.2922   0.0610
  -6.250  -0.2092   0.02222   0.01291  -0.0890   0.2898   0.0633
  -6.000  -0.1822   0.02194   0.01262  -0.0887   0.2874   0.0648
  -5.750  -0.1550   0.02159   0.01215  -0.0884   0.2851   0.0667
  -5.500  -0.1277   0.02108   0.01138  -0.0882   0.2831   0.0689
  -5.250  -0.1005   0.02061   0.01077  -0.0879   0.2813   0.0706
  -5.000  -0.0733   0.02032   0.01043  -0.0876   0.2795   0.0721
  -4.750  -0.0460   0.02004   0.01003  -0.0872   0.2780   0.0740
  -4.500  -0.0186   0.01975   0.00956  -0.0869   0.2765   0.0759
  -4.250   0.0091   0.01945   0.00906  -0.0865   0.2752   0.0775
  -4.000   0.0365   0.01909   0.00872  -0.0862   0.2742   0.0790
  -3.750   0.0642   0.01886   0.00845  -0.0859   0.2732   0.0807
  -3.500   0.0920   0.01862   0.00817  -0.0856   0.2722   0.0823
  -3.250   0.1198   0.01841   0.00788  -0.0852   0.2712   0.0842
  -3.000   0.1477   0.01826   0.00762  -0.0849   0.2703   0.0861
  -2.750   0.1754   0.01803   0.00741  -0.0846   0.2693   0.0879
  -2.500   0.2032   0.01790   0.00726  -0.0842   0.2684   0.0898
  -2.250   0.2310   0.01780   0.00712  -0.0839   0.2676   0.0920
  -2.000   0.2590   0.01773   0.00699  -0.0836   0.2668   0.0948
  -1.750   0.2869   0.01764   0.00689  -0.0833   0.2659   0.0977
  -1.500   0.3148   0.01759   0.00683  -0.0830   0.2650   0.1012
  -1.250   0.3427   0.01758   0.00677  -0.0827   0.2641   0.1052
  -1.000   0.3706   0.01755   0.00674  -0.0824   0.2632   0.1098
  -0.750   0.3986   0.01757   0.00674  -0.0822   0.2625   0.1166
  -0.500   0.4265   0.01760   0.00678  -0.0819   0.2618   0.1255
  -0.250   0.4544   0.01766   0.00686  -0.0817   0.2612   0.1378
   0.000   0.4823   0.01774   0.00697  -0.0814   0.2606   0.1557
   0.500   0.5378   0.01798   0.00736  -0.0810   0.2595   0.2186
   0.750   0.5655   0.01813   0.00763  -0.0808   0.2589   0.2631
   1.000   0.5930   0.01819   0.00785  -0.0806   0.2586   0.3171
   1.250   0.6203   0.01824   0.00812  -0.0803   0.2582   0.3808
   1.500   0.6473   0.01828   0.00841  -0.0800   0.2579   0.4586
   1.750   0.6735   0.01826   0.00873  -0.0794   0.2575   0.5623
   2.000   0.6963   0.01809   0.00904  -0.0780   0.2572   0.7190
   2.500   0.7527   0.01828   0.00955  -0.0772   0.2564   0.9996
   2.750   0.7801   0.01866   0.00989  -0.0769   0.2561   0.9996
   3.000   0.8074   0.01905   0.01026  -0.0767   0.2557   0.9996
   3.250   0.8345   0.01945   0.01064  -0.0764   0.2553   0.9996
   3.500   0.8615   0.01988   0.01106  -0.0761   0.2550   0.9996
   3.750   0.8883   0.02033   0.01150  -0.0757   0.2546   0.9996
   4.000   0.9149   0.02079   0.01197  -0.0754   0.2542   0.9996
   4.250   0.9414   0.02127   0.01246  -0.0751   0.2538   0.9996
   4.500   0.9676   0.02178   0.01299  -0.0747   0.2535   0.9996
   4.750   0.9937   0.02229   0.01352  -0.0743   0.2530   0.9996
   5.000   1.0196   0.02278   0.01404  -0.0739   0.2524   0.9996
   5.250   1.0453   0.02329   0.01458  -0.0735   0.2518   0.9996
   5.500   1.0707   0.02386   0.01519  -0.0731   0.2513   0.9996
   5.750   1.0959   0.02446   0.01583  -0.0727   0.2509   0.9996
   6.000   1.1208   0.02509   0.01651  -0.0723   0.2505   0.9996
   6.250   1.1454   0.02574   0.01722  -0.0718   0.2501   0.9996
   6.500   1.1698   0.02642   0.01796  -0.0713   0.2497   0.9996
   6.750   1.1938   0.02713   0.01874  -0.0708   0.2493   0.9996
   7.000   1.2175   0.02786   0.01954  -0.0703   0.2489   0.9996
   7.250   1.2408   0.02862   0.02037  -0.0698   0.2485   0.9996
   7.500   1.2638   0.02942   0.02125  -0.0692   0.2481   0.9996
   7.750   1.2865   0.03024   0.02215  -0.0686   0.2476   0.9996
   8.000   1.3088   0.03108   0.02307  -0.0680   0.2472   0.9996
   8.250   1.3314   0.03182   0.02387  -0.0675   0.2467   0.9996
   8.500   1.3541   0.03252   0.02463  -0.0669   0.2460   0.9996
   8.750   1.3769   0.03320   0.02535  -0.0663   0.2454   0.9996
   9.000   1.3998   0.03388   0.02606  -0.0658   0.2448   0.9996
   9.250   1.4229   0.03457   0.02678  -0.0653   0.2441   0.9996
   9.500   1.4450   0.03552   0.02775  -0.0648   0.2433   0.9996
   9.750   1.4601   0.03688   0.02930  -0.0637   0.2426   0.9996
  10.000   1.4709   0.03857   0.03126  -0.0623   0.2419   0.9996
  10.250   1.4764   0.04070   0.03367  -0.0606   0.2406   0.9996
  10.500   1.4757   0.04329   0.03655  -0.0587   0.2389   0.9996
  10.750   1.4689   0.04629   0.03982  -0.0567   0.2371   0.9996
  11.000   1.4498   0.05006   0.04385  -0.0543   0.2354   0.9996
  11.250   1.3902   0.05704   0.05110  -0.0523   0.2330   0.9996
  11.500   1.3267   0.06815   0.06240  -0.0582   0.2298   0.9996
  11.750   1.3395   0.06940   0.06367  -0.0579   0.2292   0.9996
  12.000   1.3558   0.07011   0.06440  -0.0572   0.2287   0.9996
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