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UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: UAG 88-143/20 (uag8814320-il)
Reynolds number: 500,000
Max Cl/Cd: 123.92 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-uag8814320-il-500000-n5.txt
Download as CSV file: xf-uag8814320-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1002   0.08709   0.08342  -0.1572   0.8025   0.0052
 -10.750   0.1016   0.08374   0.08010  -0.1582   0.8015   0.0051
 -10.500   0.1027   0.08042   0.07680  -0.1591   0.8004   0.0049
 -10.250   0.0992   0.07635   0.07275  -0.1601   0.7992   0.0047
 -10.000   0.0970   0.07265   0.06908  -0.1612   0.7982   0.0045
  -9.750   0.0419   0.06107   0.05759  -0.1634   0.7965   0.0040
  -9.500   0.0213   0.05575   0.05229  -0.1653   0.7951   0.0040
  -9.250  -0.0132   0.05010   0.04673  -0.1673   0.7929   0.0039
  -8.750  -0.1163   0.02975   0.02578  -0.1644   0.7874   0.0038
  -8.500  -0.1187   0.02616   0.02177  -0.1619   0.7858   0.0038
  -8.250  -0.1111   0.02386   0.01914  -0.1598   0.7845   0.0038
  -8.000  -0.0996   0.02195   0.01690  -0.1579   0.7834   0.0037
  -7.750  -0.0835   0.02057   0.01526  -0.1566   0.7825   0.0037
  -7.500  -0.0654   0.01938   0.01382  -0.1554   0.7816   0.0037
  -7.250  -0.0460   0.01846   0.01272  -0.1542   0.7805   0.0037
  -7.000  -0.0275   0.01755   0.01164  -0.1528   0.7788   0.0037
  -6.750  -0.0069   0.01683   0.01078  -0.1518   0.7772   0.0037
  -6.500   0.0146   0.01618   0.01000  -0.1508   0.7758   0.0037
  -6.250   0.0371   0.01558   0.00929  -0.1500   0.7744   0.0036
  -6.000   0.0605   0.01507   0.00865  -0.1494   0.7731   0.0036
  -5.750   0.0847   0.01458   0.00805  -0.1489   0.7718   0.0037
  -5.500   0.1095   0.01414   0.00751  -0.1484   0.7708   0.0037
  -5.250   0.1349   0.01376   0.00703  -0.1481   0.7698   0.0037
  -5.000   0.1607   0.01339   0.00655  -0.1479   0.7688   0.0037
  -4.750   0.1869   0.01307   0.00615  -0.1477   0.7679   0.0037
  -4.500   0.2099   0.01284   0.00586  -0.1469   0.7661   0.0037
  -4.250   0.2335   0.01264   0.00562  -0.1462   0.7643   0.0037
  -4.000   0.2577   0.01242   0.00535  -0.1456   0.7625   0.0038
  -3.750   0.2827   0.01221   0.00509  -0.1452   0.7609   0.0039
  -3.500   0.3083   0.01201   0.00484  -0.1448   0.7594   0.0039
  -3.250   0.3344   0.01182   0.00460  -0.1446   0.7581   0.0041
  -3.000   0.3611   0.01164   0.00438  -0.1445   0.7569   0.0044
  -2.750   0.3881   0.01147   0.00418  -0.1445   0.7557   0.0051
  -2.250   0.4361   0.01112   0.00396  -0.1434   0.7522   0.0312
  -2.000   0.4597   0.01103   0.00393  -0.1427   0.7499   0.0426
  -1.750   0.4842   0.01088   0.00387  -0.1423   0.7479   0.0597
  -1.500   0.5098   0.01075   0.00378  -0.1420   0.7460   0.0727
  -1.250   0.5362   0.01061   0.00366  -0.1419   0.7444   0.0861
  -1.000   0.5628   0.01043   0.00354  -0.1418   0.7429   0.1132
  -0.750   0.5882   0.01013   0.00345  -0.1417   0.7414   0.1873
  -0.500   0.6049   0.00981   0.00355  -0.1398   0.7381   0.3134
  -0.250   0.6242   0.00948   0.00356  -0.1384   0.7353   0.4380
   0.000   0.6430   0.00909   0.00355  -0.1368   0.7328   0.5743
   0.250   0.6592   0.00862   0.00353  -0.1345   0.7306   0.7265
   0.500   0.6976   0.00825   0.00362  -0.1366   0.7291   0.9019
   0.750   0.7903   0.00838   0.00376  -0.1509   0.7282   0.9716
   1.000   0.8317   0.00852   0.00390  -0.1542   0.7249   0.9840
   1.250   0.8775   0.00857   0.00393  -0.1585   0.7219   0.9909
   1.500   0.9175   0.00858   0.00391  -0.1615   0.7190   0.9957
   1.750   0.9547   0.00854   0.00383  -0.1639   0.7163   0.9985
   2.000   0.9828   0.00858   0.00387  -0.1643   0.7124   1.0000
   2.250   1.0001   0.00863   0.00392  -0.1624   0.7077   1.0000
   2.500   1.0207   0.00863   0.00389  -0.1611   0.7038   1.0000
   2.750   1.0394   0.00868   0.00394  -0.1595   0.6994   1.0000
   3.000   1.0557   0.00875   0.00402  -0.1573   0.6940   1.0000
   3.250   1.0757   0.00878   0.00401  -0.1559   0.6892   1.0000
   3.500   1.0909   0.00888   0.00414  -0.1535   0.6834   1.0000
   3.750   1.1074   0.00896   0.00420  -0.1513   0.6772   1.0000
   4.000   1.1224   0.00906   0.00430  -0.1489   0.6707   1.0000
   4.250   1.1363   0.00917   0.00441  -0.1462   0.6637   1.0000
   4.500   1.1472   0.00930   0.00453  -0.1429   0.6563   1.0000
   4.750   1.1557   0.00943   0.00464  -0.1390   0.6486   1.0000
   5.000   1.1637   0.00961   0.00482  -0.1351   0.6403   1.0000
   5.250   1.1739   0.00981   0.00500  -0.1318   0.6316   1.0000
   5.500   1.1831   0.01007   0.00527  -0.1283   0.6219   1.0000
   5.750   1.1925   0.01039   0.00558  -0.1250   0.6116   1.0000
   6.000   1.2017   0.01078   0.00594  -0.1218   0.6005   1.0000
   6.250   1.2101   0.01125   0.00639  -0.1186   0.5882   1.0000
   6.500   1.2176   0.01184   0.00694  -0.1154   0.5739   1.0000
   6.750   1.2264   0.01245   0.00755  -0.1126   0.5605   1.0000
   7.000   1.2342   0.01317   0.00822  -0.1097   0.5449   1.0000
   7.250   1.2410   0.01396   0.00897  -0.1067   0.5277   1.0000
   7.500   1.2485   0.01477   0.00973  -0.1039   0.5114   1.0000
   7.750   1.2494   0.01588   0.01073  -0.1001   0.4875   1.0000
   8.000   1.2518   0.01698   0.01174  -0.0967   0.4652   1.0000
   8.250   1.2493   0.01835   0.01297  -0.0927   0.4361   1.0000
   8.500   1.2507   0.01960   0.01412  -0.0894   0.4097   1.0000
   8.750   1.2437   0.02134   0.01565  -0.0851   0.3714   1.0000
   9.000   1.2386   0.02309   0.01719  -0.0812   0.3341   1.0000
   9.250   1.2299   0.02516   0.01896  -0.0770   0.2844   1.0000
   9.500   1.2264   0.02701   0.02056  -0.0737   0.2425   1.0000
   9.750   1.2263   0.02873   0.02208  -0.0708   0.2064   1.0000
  10.000   1.2261   0.03049   0.02362  -0.0681   0.1691   1.0000
  10.250   1.2206   0.03267   0.02552  -0.0649   0.1213   1.0000
  10.500   1.2194   0.03465   0.02728  -0.0623   0.0845   1.0000
  10.750   1.2142   0.03697   0.02936  -0.0593   0.0461   1.0000
  11.250   1.2133   0.04118   0.03337  -0.0547   0.0048   1.0000
  11.500   1.2221   0.04263   0.03488  -0.0534   0.0037   1.0000
  11.750   1.2303   0.04414   0.03647  -0.0521   0.0031   1.0000
  12.000   1.2399   0.04557   0.03798  -0.0510   0.0029   1.0000
  12.250   1.2485   0.04711   0.03961  -0.0498   0.0027   1.0000
  12.500   1.2561   0.04875   0.04133  -0.0486   0.0024   1.0000
  12.750   1.2591   0.05084   0.04352  -0.0472   0.0020   1.0000
  13.000   1.2655   0.05264   0.04540  -0.0460   0.0020   1.0000
  13.250   1.2726   0.05441   0.04725  -0.0450   0.0020   1.0000
  13.500   1.2717   0.05701   0.04997  -0.0435   0.0018   1.0000
  13.750   1.2745   0.05929   0.05235  -0.0424   0.0018   1.0000
  14.000   1.2763   0.06173   0.05490  -0.0413   0.0017   1.0000
  14.250   1.2781   0.06419   0.05745  -0.0404   0.0017   1.0000
  14.500   1.2776   0.06694   0.06030  -0.0394   0.0017   1.0000
  14.750   1.2784   0.06963   0.06308  -0.0386   0.0016   1.0000
  15.000   1.2777   0.07253   0.06608  -0.0378   0.0016   1.0000
  15.250   1.2829   0.07476   0.06839  -0.0374   0.0015   1.0000
  15.500   1.2788   0.07813   0.07187  -0.0367   0.0014   1.0000
  15.750   1.2756   0.08143   0.07528  -0.0361   0.0015   1.0000
  16.000   1.2765   0.08430   0.07824  -0.0359   0.0014   1.0000
  16.250   1.2762   0.08735   0.08139  -0.0356   0.0013   1.0000
  16.500   1.2805   0.08986   0.08398  -0.0357   0.0011   1.0000
  16.750   1.2791   0.09314   0.08737  -0.0357   0.0011   1.0000
  17.000   1.2785   0.09633   0.09065  -0.0358   0.0011   1.0000
  17.250   1.2756   0.09983   0.09426  -0.0359   0.0010   1.0000
  17.500   1.2728   0.10338   0.09790  -0.0363   0.0009   1.0000
  17.750   1.2693   0.10708   0.10170  -0.0366   0.0010   1.0000
  18.000   1.2645   0.11100   0.10572  -0.0372   0.0009   1.0000
  18.250   1.2581   0.11513   0.10996  -0.0378   0.0008   1.0000
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