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UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: UAG 88-143/20 (uag8814320-il)
Reynolds number: 500,000
Max Cl/Cd: 126.97 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-uag8814320-il-500000.txt
Download as CSV file: xf-uag8814320-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1301   0.08739   0.08401  -0.1646   0.8347   0.0166
 -10.500   0.1339   0.08494   0.08159  -0.1650   0.8335   0.0172
 -10.250   0.1359   0.08223   0.07892  -0.1654   0.8321   0.0171
 -10.000   0.1377   0.07958   0.07630  -0.1659   0.8307   0.0174
  -9.750   0.0984   0.06904   0.06586  -0.1668   0.8286   0.0102
  -9.500   0.0969   0.06639   0.06323  -0.1671   0.8270   0.0099
  -9.250   0.0882   0.06294   0.05982  -0.1676   0.8252   0.0096
  -9.000   0.0676   0.05816   0.05509  -0.1685   0.8231   0.0094
  -8.750  -0.1519   0.02920   0.02534  -0.1623   0.8148   0.0072
  -8.500  -0.1542   0.02608   0.02176  -0.1591   0.8128   0.0071
  -8.250  -0.1469   0.02393   0.01923  -0.1566   0.8113   0.0071
  -8.000  -0.1353   0.02217   0.01714  -0.1544   0.8101   0.0073
  -7.750  -0.1186   0.02103   0.01575  -0.1529   0.8089   0.0074
  -7.500  -0.1034   0.02020   0.01477  -0.1510   0.8068   0.0076
  -7.250  -0.0861   0.01958   0.01404  -0.1494   0.8044   0.0081
  -7.000  -0.0668   0.01892   0.01325  -0.1481   0.8025   0.0084
  -6.750  -0.0455   0.01832   0.01251  -0.1470   0.8009   0.0090
  -6.500  -0.0226   0.01775   0.01179  -0.1463   0.7996   0.0096
  -6.250   0.0000   0.01703   0.01094  -0.1454   0.7983   0.0111
  -6.000   0.0249   0.01662   0.01046  -0.1450   0.7972   0.0127
  -5.750   0.0501   0.01623   0.00995  -0.1446   0.7962   0.0150
  -5.500   0.0758   0.01598   0.00968  -0.1443   0.7953   0.0208
  -5.250   0.0917   0.01599   0.00976  -0.1423   0.7919   0.0249
  -5.000   0.1147   0.01600   0.00974  -0.1415   0.7895   0.0279
  -4.750   0.1404   0.01602   0.00968  -0.1413   0.7879   0.0298
  -4.500   0.1649   0.01564   0.00927  -0.1408   0.7865   0.0332
  -4.250   0.1924   0.01551   0.00913  -0.1409   0.7853   0.0368
  -4.000   0.2210   0.01547   0.00903  -0.1412   0.7842   0.0403
  -3.750   0.2468   0.01507   0.00861  -0.1409   0.7833   0.0455
  -3.500   0.2753   0.01497   0.00846  -0.1412   0.7825   0.0507
  -3.250   0.2938   0.01518   0.00866  -0.1396   0.7794   0.0536
  -3.000   0.3114   0.01503   0.00856  -0.1379   0.7761   0.0606
  -2.750   0.3368   0.01489   0.00838  -0.1375   0.7744   0.0651
  -2.500   0.3629   0.01462   0.00808  -0.1373   0.7729   0.0702
  -2.250   0.3905   0.01436   0.00781  -0.1373   0.7718   0.0770
  -2.000   0.4187   0.01410   0.00754  -0.1375   0.7708   0.0856
  -1.750   0.4473   0.01382   0.00729  -0.1378   0.7699   0.1015
  -1.500   0.4752   0.01345   0.00707  -0.1381   0.7691   0.1499
  -1.250   0.4830   0.01350   0.00741  -0.1345   0.7641   0.2267
  -1.000   0.5011   0.01297   0.00736  -0.1330   0.7616   0.3832
  -0.750   0.5136   0.01207   0.00727  -0.1300   0.7597   0.6498
  -0.500   0.5518   0.01139   0.00733  -0.1319   0.7589   0.9068
  -0.250   0.6326   0.01142   0.00731  -0.1433   0.7589   0.9576
   0.000   0.6850   0.01140   0.00721  -0.1486   0.7583   0.9742
   0.250   0.7344   0.01131   0.00705  -0.1533   0.7575   0.9835
   0.500   0.8164   0.01121   0.00688  -0.1651   0.7573   0.9956
   0.750   0.8696   0.01102   0.00663  -0.1708   0.7566   1.0000
   1.000   0.8952   0.01089   0.00645  -0.1707   0.7551   1.0000
   1.250   0.8996   0.01113   0.00674  -0.1663   0.7497   1.0000
   1.500   0.9227   0.01100   0.00659  -0.1655   0.7473   1.0000
   1.750   0.9491   0.01080   0.00636  -0.1654   0.7455   1.0000
   2.000   0.9774   0.01058   0.00610  -0.1657   0.7439   1.0000
   2.250   1.0079   0.01038   0.00585  -0.1664   0.7425   1.0000
   2.500   1.0125   0.01060   0.00615  -0.1619   0.7370   1.0000
   2.750   1.0350   0.01049   0.00603  -0.1610   0.7340   1.0000
   3.000   1.0629   0.01029   0.00581  -0.1612   0.7317   1.0000
   3.250   1.0942   0.01007   0.00557  -0.1620   0.7297   1.0000
   3.500   1.1020   0.01021   0.00576  -0.1581   0.7242   1.0000
   3.750   1.1244   0.01010   0.00565  -0.1571   0.7203   1.0000
   4.000   1.1536   0.00991   0.00545  -0.1575   0.7173   1.0000
   4.250   1.1675   0.00998   0.00556  -0.1548   0.7123   1.0000
   4.500   1.1858   0.00996   0.00556  -0.1530   0.7073   1.0000
   4.750   1.2142   0.00982   0.00541  -0.1533   0.7035   1.0000
   5.000   1.2230   0.00996   0.00559  -0.1496   0.6970   1.0000
   5.250   1.2438   0.00992   0.00556  -0.1483   0.6915   1.0000
   5.500   1.2587   0.01000   0.00567  -0.1458   0.6852   1.0000
   5.750   1.2733   0.01005   0.00574  -0.1432   0.6783   1.0000
   6.000   1.2810   0.01016   0.00587  -0.1392   0.6706   1.0000
   6.250   1.2964   0.01021   0.00591  -0.1367   0.6632   1.0000
   6.500   1.2970   0.01045   0.00618  -0.1314   0.6538   1.0000
   6.750   1.3089   0.01063   0.00636  -0.1284   0.6447   1.0000
   7.000   1.3202   0.01085   0.00656  -0.1254   0.6340   1.0000
   7.250   1.3226   0.01128   0.00700  -0.1209   0.6194   1.0000
   7.500   1.3159   0.01207   0.00770  -0.1150   0.5949   1.0000
   7.750   1.3174   0.01287   0.00845  -0.1109   0.5743   1.0000
   8.000   1.3148   0.01394   0.00940  -0.1063   0.5476   1.0000
   8.250   1.3106   0.01518   0.01050  -0.1016   0.5180   1.0000
   8.500   1.3085   0.01642   0.01161  -0.0975   0.4911   1.0000
   8.750   1.2991   0.01806   0.01306  -0.0924   0.4547   1.0000
   9.000   1.2915   0.01971   0.01452  -0.0878   0.4188   1.0000
   9.250   1.2786   0.02176   0.01631  -0.0827   0.3736   1.0000
   9.500   1.2699   0.02375   0.01805  -0.0784   0.3310   1.0000
   9.750   1.2646   0.02565   0.01973  -0.0747   0.2906   1.0000
  10.000   1.2507   0.02817   0.02186  -0.0702   0.2310   1.0000
  10.250   1.2339   0.03101   0.02424  -0.0656   0.1605   1.0000
  10.500   1.2185   0.03390   0.02667  -0.0614   0.0927   1.0000
  10.750   1.1969   0.03742   0.02970  -0.0568   0.0214   1.0000
  11.000   1.1982   0.03939   0.03162  -0.0546   0.0082   1.0000
  11.250   1.2079   0.04074   0.03304  -0.0532   0.0073   1.0000
  11.500   1.2141   0.04242   0.03482  -0.0516   0.0062   1.0000
  11.750   1.2185   0.04427   0.03680  -0.0498   0.0057   1.0000
  12.000   1.2256   0.04592   0.03855  -0.0484   0.0056   1.0000
  12.250   1.2317   0.04770   0.04041  -0.0470   0.0054   1.0000
  12.500   1.2359   0.04968   0.04249  -0.0456   0.0053   1.0000
  12.750   1.2403   0.05169   0.04460  -0.0443   0.0053   1.0000
  13.000   1.2426   0.05393   0.04693  -0.0428   0.0052   1.0000
  13.250   1.2430   0.05641   0.04953  -0.0414   0.0052   1.0000
  13.500   1.2454   0.05873   0.05194  -0.0402   0.0052   1.0000
  13.750   1.2442   0.06146   0.05478  -0.0389   0.0051   1.0000
  14.000   1.2435   0.06420   0.05761  -0.0377   0.0051   1.0000
  14.250   1.2433   0.06688   0.06039  -0.0366   0.0051   1.0000
  14.500   1.2416   0.06974   0.06334  -0.0354   0.0052   1.0000
  14.750   1.2422   0.07237   0.06607  -0.0344   0.0052   1.0000
  15.000   1.2420   0.07506   0.06885  -0.0333   0.0052   1.0000
  15.250   1.2433   0.07752   0.07139  -0.0322   0.0053   1.0000
  15.500   1.2463   0.07975   0.07370  -0.0311   0.0054   1.0000
  15.750   1.2508   0.08174   0.07577  -0.0299   0.0054   1.0000
  16.000   1.2559   0.08380   0.07794  -0.0290   0.0054   1.0000
  16.250   1.2625   0.08550   0.07972  -0.0277   0.0054   1.0000
  16.500   1.2644   0.08836   0.08270  -0.0277   0.0052   1.0000
  16.750   1.2649   0.09157   0.08605  -0.0283   0.0048   1.0000
  17.000   1.2692   0.09358   0.08819  -0.0269   0.0050   1.0000
  17.250   1.2711   0.09614   0.09091  -0.0261   0.0051   1.0000
  17.500   1.2715   0.09898   0.09390  -0.0254   0.0052   1.0000
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