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UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: UAG 88-143/20 (uag8814320-il)
Reynolds number: 100,000
Max Cl/Cd: 30.31 at α=11°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-uag8814320-il-100000-n5.txt
Download as CSV file: xf-uag8814320-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UAG 88-143/20                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.0690   0.11196   0.10598  -0.1488   0.8872   0.0211
 -11.750   0.0735   0.10947   0.10351  -0.1491   0.8855   0.0200
 -11.500   0.0766   0.10690   0.10094  -0.1495   0.8838   0.0196
 -11.250   0.0791   0.10414   0.09822  -0.1500   0.8820   0.0187
 -11.000   0.0809   0.10122   0.09531  -0.1507   0.8801   0.0179
 -10.500   0.0791   0.09408   0.08821  -0.1533   0.8763   0.0161
 -10.250   0.0801   0.09138   0.08555  -0.1537   0.8746   0.0161
 -10.000   0.0811   0.08988   0.08409  -0.1528   0.8722   0.0158
  -9.750   0.0768   0.08730   0.08158  -0.1524   0.8694   0.0159
  -9.500   0.0765   0.08509   0.07940  -0.1522   0.8667   0.0157
  -9.250   0.0751   0.08244   0.07679  -0.1524   0.8644   0.0156
  -9.000   0.0738   0.07971   0.07409  -0.1529   0.8624   0.0154
  -8.750   0.0649   0.07812   0.07257  -0.1512   0.8589   0.0152
  -8.500   0.0529   0.07647   0.07101  -0.1492   0.8545   0.0151
  -8.250   0.0432   0.07419   0.06878  -0.1485   0.8513   0.0150
  -8.000   0.0321   0.07123   0.06586  -0.1487   0.8483   0.0150
  -7.750  -0.0024   0.07211   0.06687  -0.1413   0.8409   0.0148
  -7.500  -0.0176   0.06988   0.06466  -0.1400   0.8370   0.0146
  -7.250  -0.0383   0.06884   0.06365  -0.1360   0.8316   0.0143
  -7.000  -0.0646   0.06765   0.06250  -0.1309   0.8253   0.0144
  -6.750  -0.0689   0.06367   0.05841  -0.1311   0.8224   0.0142
  -6.500  -0.1102   0.06523   0.06008  -0.1202   0.8132   0.0141
  -6.250  -0.1131   0.06066   0.05533  -0.1199   0.8100   0.0141
  -6.000  -0.1379   0.06001   0.05466  -0.1129   0.8027   0.0139
  -5.750  -0.1429   0.05584   0.05025  -0.1107   0.7985   0.0138
  -5.500  -0.1369   0.04942   0.04331  -0.1102   0.7961   0.0137
  -5.250  -0.1431   0.04612   0.03958  -0.1060   0.7912   0.0136
  -5.000  -0.1414   0.04279   0.03568  -0.1026   0.7868   0.0140
  -4.750  -0.1235   0.03968   0.03191  -0.1013   0.7845   0.0144
  -4.500  -0.0995   0.03729   0.02887  -0.1006   0.7830   0.0161
  -4.250  -0.0722   0.03628   0.02763  -0.1007   0.7817   0.0176
  -4.000  -0.0739   0.03671   0.02801  -0.0963   0.7753   0.0205
  -3.750  -0.0527   0.03631   0.02745  -0.0954   0.7723   0.0256
  -3.250   0.0019   0.03527   0.02588  -0.0951   0.7689   0.0426
  -3.000   0.0081   0.03568   0.02627  -0.0921   0.7633   0.0482
  -2.750   0.0276   0.03562   0.02596  -0.0909   0.7597   0.0553
  -2.500   0.0526   0.03535   0.02566  -0.0907   0.7575   0.0628
  -2.250   0.0813   0.03500   0.02509  -0.0907   0.7559   0.0689
  -2.000   0.0902   0.03514   0.02525  -0.0882   0.7506   0.0744
  -1.750   0.1085   0.03523   0.02522  -0.0868   0.7467   0.0833
  -1.500   0.1337   0.03497   0.02494  -0.0866   0.7443   0.0928
  -1.250   0.1619   0.03464   0.02455  -0.0866   0.7427   0.1021
  -1.000   0.1690   0.03499   0.02486  -0.0837   0.7366   0.1084
  -0.750   0.1898   0.03494   0.02480  -0.0828   0.7329   0.1228
  -0.500   0.2175   0.03468   0.02459  -0.0829   0.7308   0.1464
  -0.250   0.2479   0.03429   0.02439  -0.0835   0.7292   0.2105
   0.000   0.3328   0.03286   0.02515  -0.0958   0.7294   1.0000
   0.500   0.3600   0.03379   0.02571  -0.0919   0.7188   1.0000
   0.750   0.3885   0.03385   0.02558  -0.0921   0.7167   1.0000
   1.000   0.4185   0.03387   0.02542  -0.0924   0.7150   1.0000
   1.250   0.4188   0.03478   0.02625  -0.0888   0.7060   1.0000
   1.500   0.4470   0.03483   0.02615  -0.0889   0.7037   1.0000
   1.750   0.4777   0.03481   0.02600  -0.0894   0.7021   1.0000
   2.000   0.4794   0.03576   0.02689  -0.0861   0.6928   1.0000
   2.250   0.5077   0.03579   0.02681  -0.0862   0.6904   1.0000
   2.500   0.5382   0.03573   0.02665  -0.0867   0.6887   1.0000
   2.750   0.5411   0.03672   0.02761  -0.0836   0.6793   1.0000
   3.000   0.5697   0.03670   0.02751  -0.0838   0.6768   1.0000
   3.250   0.6005   0.03657   0.02732  -0.0842   0.6750   1.0000
   3.500   0.6044   0.03759   0.02832  -0.0814   0.6653   1.0000
   3.750   0.6331   0.03753   0.02821  -0.0816   0.6627   1.0000
   4.000   0.6646   0.03730   0.02795  -0.0821   0.6610   1.0000
   4.250   0.6680   0.03843   0.02910  -0.0793   0.6508   1.0000
   4.500   0.6981   0.03821   0.02885  -0.0796   0.6485   1.0000
   5.000   0.7332   0.03909   0.02974  -0.0774   0.6361   1.0000
   5.250   0.7643   0.03874   0.02941  -0.0777   0.6340   1.0000
   5.500   0.7705   0.03984   0.03054  -0.0755   0.6238   1.0000
   5.750   0.8001   0.03952   0.03025  -0.0756   0.6212   1.0000
   6.000   0.8318   0.03905   0.02983  -0.0759   0.6194   1.0000
   6.250   0.8372   0.04021   0.03103  -0.0736   0.6084   1.0000
   6.500   0.8682   0.03969   0.03057  -0.0738   0.6062   1.0000
   6.750   0.8757   0.04076   0.03170  -0.0718   0.5956   1.0000
   7.000   0.9055   0.04024   0.03124  -0.0718   0.5929   1.0000
   7.500   0.9444   0.04065   0.03182  -0.0699   0.5795   1.0000
   7.750   0.9766   0.03991   0.03116  -0.0701   0.5772   1.0000
   8.000   0.9843   0.04099   0.03233  -0.0682   0.5660   1.0000
   8.250   1.0180   0.04010   0.03155  -0.0684   0.5634   1.0000
   9.250   1.0863   0.04160   0.03350  -0.0639   0.5274   1.0000
   9.500   1.1193   0.04066   0.03269  -0.0640   0.5219   1.0000
  10.000   1.1540   0.04143   0.03373  -0.0618   0.5006   1.0000
  10.250   1.1883   0.04038   0.03281  -0.0620   0.4924   1.0000
  10.500   1.2048   0.04082   0.03337  -0.0608   0.4795   1.0000
  10.750   1.2236   0.04107   0.03374  -0.0598   0.4660   1.0000
  11.000   1.2449   0.04107   0.03384  -0.0589   0.4506   1.0000
  11.250   1.2578   0.04173   0.03460  -0.0573   0.4319   1.0000
  11.500   1.2655   0.04260   0.03541  -0.0551   0.4036   1.0000
  11.750   1.2652   0.04411   0.03672  -0.0524   0.3657   1.0000
  12.000   1.2614   0.04616   0.03858  -0.0497   0.3272   1.0000
  12.250   1.2569   0.04844   0.04065  -0.0472   0.2896   1.0000
  12.500   1.2505   0.05107   0.04306  -0.0448   0.2522   1.0000
  12.750   1.2430   0.05397   0.04576  -0.0427   0.2139   1.0000
  13.000   1.2349   0.05707   0.04864  -0.0408   0.1766   1.0000
  13.250   1.2160   0.06140   0.05249  -0.0386   0.1205   1.0000
  13.500   1.2037   0.06523   0.05598  -0.0370   0.0790   1.0000
  13.750   1.1902   0.06935   0.05976  -0.0355   0.0405   1.0000
  14.000   1.1801   0.07327   0.06351  -0.0343   0.0209   1.0000
  14.250   1.1764   0.07662   0.06690  -0.0335   0.0163   1.0000
  14.500   1.1739   0.07992   0.07034  -0.0329   0.0142   1.0000
  14.750   1.1712   0.08332   0.07392  -0.0324   0.0130   1.0000
  15.000   1.1663   0.08708   0.07784  -0.0321   0.0121   1.0000
  15.250   1.1642   0.09055   0.08147  -0.0320   0.0119   1.0000
  15.500   1.1598   0.09441   0.08555  -0.0320   0.0112   1.0000
  15.750   1.1568   0.09813   0.08945  -0.0322   0.0109   1.0000
  16.000   1.1530   0.10203   0.09354  -0.0325   0.0106   1.0000
  16.250   1.1491   0.10598   0.09766  -0.0330   0.0101   1.0000
  16.500   1.1462   0.10981   0.10165  -0.0336   0.0098   1.0000
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