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UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il)
Reynolds number: 50,000
Max Cl/Cd: 10.11 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ui1720-il-50000.txt
Download as CSV file: xf-ui1720-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3195   0.13346   0.12742   0.0050   1.0004   0.1727
 -10.000  -0.3206   0.13202   0.12609   0.0034   1.0004   0.1790
  -9.750  -0.3433   0.13439   0.12860  -0.0004   1.0004   0.1812
  -9.500  -0.3004   0.12424   0.11863   0.0024   1.0004   0.1883
  -9.250  -0.2983   0.12242   0.11701   0.0011   1.0004   0.1965
  -9.000  -0.3240   0.12490   0.11968  -0.0028   1.0004   0.1994
  -8.750  -0.2562   0.11472   0.10863  -0.0054   0.6407   0.2116
  -8.500  -0.2755   0.11646   0.11031  -0.0096   0.6260   0.2179
  -8.250  -0.2378   0.10932   0.10264  -0.0071   0.5789   0.2269
  -8.000  -0.2472   0.10953   0.10282  -0.0101   0.5709   0.2366
  -7.750  -0.2219   0.10400   0.09711  -0.0094   0.5527   0.2435
  -7.500  -0.2224   0.10311   0.09621  -0.0115   0.5453   0.2557
  -7.250  -0.2001   0.09840   0.09142  -0.0111   0.5338   0.2647
  -7.000  -0.2136   0.09907   0.09216  -0.0145   0.5311   0.2767
  -6.750  -0.1771   0.09297   0.08597  -0.0127   0.5201   0.2881
  -6.500  -0.1776   0.09122   0.08428  -0.0146   0.5160   0.3002
  -6.250  -0.1757   0.09039   0.08345  -0.0161   0.5119   0.3165
  -6.000  -0.1441   0.08541   0.07842  -0.0146   0.5046   0.3299
  -5.750  -0.1340   0.08296   0.07604  -0.0148   0.4999   0.3453
  -5.500  -0.1255   0.08083   0.07393  -0.0153   0.4958   0.3627
  -5.250  -0.1157   0.07875   0.07184  -0.0156   0.4920   0.3813
  -5.000  -0.1011   0.07643   0.06947  -0.0149   0.4883   0.4022
  -4.750  -0.0845   0.07403   0.06716  -0.0140   0.4845   0.4246
  -4.500  -0.0691   0.07190   0.06507  -0.0133   0.4812   0.4485
  -4.250  -0.0610   0.07042   0.06365  -0.0128   0.4790   0.4796
  -4.000  -0.0383   0.06783   0.06106  -0.0106   0.4763   0.5075
  -3.750  -0.0244   0.06596   0.05922  -0.0088   0.4743   0.5419
  -3.500   0.0577   0.05101   0.04298  -0.0717   0.4736   0.2591
  -3.250   0.0878   0.04848   0.04022  -0.0745   0.4715   0.2520
  -3.000   0.1198   0.04604   0.03743  -0.0780   0.4697   0.2473
  -2.750   0.1533   0.04385   0.03484  -0.0816   0.4683   0.2437
  -2.500   0.1829   0.04275   0.03357  -0.0833   0.4673   0.2464
  -2.250   0.2130   0.04184   0.03244  -0.0850   0.4664   0.2487
  -2.000   0.2429   0.04122   0.03157  -0.0864   0.4658   0.2523
  -1.750   0.2722   0.04089   0.03099  -0.0876   0.4652   0.2586
  -1.500   0.2979   0.04090   0.03109  -0.0880   0.4646   0.2656
  -1.250   0.3255   0.04109   0.03113  -0.0888   0.4639   0.2745
  -1.000   0.3506   0.04147   0.03157  -0.0893   0.4635   0.2860
  -0.750   0.3764   0.04205   0.03211  -0.0900   0.4637   0.3002
  -0.500   0.4010   0.04285   0.03295  -0.0905   0.4648   0.3194
  -0.250   0.4255   0.04376   0.03398  -0.0909   0.4664   0.3451
   0.000   0.4505   0.04470   0.03504  -0.0913   0.4680   0.3855
   0.250   0.4655   0.04781   0.03874  -0.0956   0.4786   0.4258
   0.500   0.4841   0.04940   0.04091  -0.0966   0.4850   0.5229
   0.750   0.4940   0.04886   0.04174  -0.0921   0.4882   0.9996
   1.000   0.2637   0.07308   0.06462  -0.1240   0.8133   0.2944
   1.250   0.2932   0.07452   0.06595  -0.1249   0.7940   0.3143
   1.500   0.3193   0.07587   0.06731  -0.1252   0.7752   0.3422
   1.750   0.3433   0.07714   0.06871  -0.1252   0.7570   0.3860
   2.000   0.3900   0.07875   0.07173  -0.1279   0.7507   0.6305
   2.250   0.4033   0.07912   0.07215  -0.1248   0.7317   0.9996
   2.500   0.4207   0.08080   0.07346  -0.1239   0.7125   0.9996
   2.750   0.4336   0.08235   0.07474  -0.1225   0.6939   0.9996
   3.000   0.4434   0.08398   0.07615  -0.1211   0.6768   0.9996
   3.250   0.4571   0.08613   0.07809  -0.1204   0.6633   0.9996
   3.500   0.4907   0.08919   0.08090  -0.1216   0.6529   0.9996
   3.750   0.4934   0.09053   0.08211  -0.1197   0.6365   0.9996
   4.000   0.5312   0.09470   0.08606  -0.1214   0.6298   0.9996
   4.250   0.5340   0.09557   0.08683  -0.1194   0.6132   0.9996
   4.500   0.5337   0.09712   0.08827  -0.1177   0.5996   0.9996
   4.750   0.5672   0.10058   0.09158  -0.1187   0.5921   0.9996
   5.000   0.5613   0.10173   0.09266  -0.1168   0.5781   0.9996
   5.250   0.5980   0.10563   0.09642  -0.1179   0.5714   0.9996
   5.500   0.5871   0.10643   0.09715  -0.1158   0.5574   0.9996
   5.750   0.6224   0.11039   0.10100  -0.1167   0.5513   0.9996
   6.000   0.6088   0.11119   0.10176  -0.1148   0.5389   0.9996
   6.250   0.6369   0.11459   0.10507  -0.1153   0.5322   0.9996
   6.500   0.6315   0.11631   0.10674  -0.1142   0.5227   0.9996
   6.750   0.6506   0.11896   0.10932  -0.1140   0.5137   0.9996
   7.000   0.6923   0.12444   0.11472  -0.1152   0.5098   0.9996
   7.250   0.6641   0.12356   0.11382  -0.1131   0.4964   0.9996
   7.500   0.6928   0.12746   0.11766  -0.1135   0.4913   0.9996
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