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UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: UAG 88-143/20 (uag8814320-il)
Reynolds number: 200,000
Max Cl/Cd: 53.18 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-uag8814320-il-200000-n5.txt
Download as CSV file: xf-uag8814320-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0948   0.09707   0.09222  -0.1530   0.8370   0.0098
 -11.000   0.0983   0.09409   0.08925  -0.1539   0.8359   0.0094
 -10.750   0.1006   0.09095   0.08612  -0.1548   0.8349   0.0092
 -10.500   0.0992   0.08753   0.08275  -0.1553   0.8333   0.0087
 -10.250   0.0975   0.08421   0.07949  -0.1557   0.8317   0.0086
 -10.000   0.0931   0.08021   0.07553  -0.1562   0.8300   0.0079
  -9.750   0.0890   0.07672   0.07210  -0.1567   0.8283   0.0080
  -9.500   0.0888   0.07408   0.06950  -0.1571   0.8265   0.0079
  -9.250   0.0858   0.07101   0.06646  -0.1576   0.8247   0.0078
  -9.000   0.0810   0.06775   0.06323  -0.1583   0.8230   0.0077
  -8.750   0.0755   0.06452   0.06004  -0.1591   0.8215   0.0075
  -8.500   0.0614   0.06134   0.05697  -0.1591   0.8185   0.0075
  -8.250   0.0420   0.05837   0.05408  -0.1589   0.8149   0.0073
  -8.000   0.0205   0.05408   0.04982  -0.1591   0.8119   0.0072
  -7.750   0.0025   0.04874   0.04436  -0.1593   0.8096   0.0070
  -7.500  -0.0532   0.03704   0.03213  -0.1546   0.8047   0.0064
  -7.250  -0.0722   0.03138   0.02574  -0.1496   0.8007   0.0062
  -7.000  -0.0660   0.02888   0.02278  -0.1469   0.7986   0.0063
  -6.750  -0.0518   0.02714   0.02065  -0.1451   0.7969   0.0063
  -6.500  -0.0332   0.02577   0.01896  -0.1438   0.7957   0.0064
  -6.250  -0.0121   0.02462   0.01751  -0.1429   0.7947   0.0065
  -6.000  -0.0110   0.02455   0.01736  -0.1384   0.7894   0.0066
  -5.750   0.0056   0.02392   0.01651  -0.1366   0.7868   0.0067
  -5.500   0.0263   0.02324   0.01562  -0.1354   0.7849   0.0070
  -5.250   0.0496   0.02265   0.01485  -0.1347   0.7836   0.0072
  -5.000   0.0741   0.02205   0.01408  -0.1342   0.7825   0.0078
  -4.750   0.0999   0.02153   0.01342  -0.1339   0.7816   0.0083
  -4.500   0.0947   0.02194   0.01383  -0.1281   0.7746   0.0089
  -4.250   0.1148   0.02169   0.01347  -0.1268   0.7724   0.0101
  -4.000   0.1380   0.02125   0.01300  -0.1261   0.7709   0.0166
  -3.750   0.1641   0.02093   0.01266  -0.1259   0.7697   0.0244
  -3.500   0.1922   0.02066   0.01232  -0.1259   0.7688   0.0328
  -3.250   0.2210   0.02044   0.01203  -0.1262   0.7680   0.0406
  -3.000   0.2030   0.02134   0.01297  -0.1182   0.7586   0.0431
  -2.750   0.2295   0.02118   0.01280  -0.1181   0.7573   0.0526
  -2.500   0.2575   0.02099   0.01261  -0.1183   0.7563   0.0634
  -2.250   0.2384   0.02181   0.01343  -0.1100   0.7473   0.0643
  -2.000   0.2618   0.02168   0.01321  -0.1093   0.7453   0.0682
  -1.750   0.2885   0.02141   0.01293  -0.1091   0.7441   0.0738
  -1.500   0.3174   0.02115   0.01260  -0.1094   0.7431   0.0815
   0.000   0.6097   0.01816   0.01200  -0.1365   0.7416   1.0000
   0.500   0.5465   0.02044   0.01425  -0.1156   0.7200   1.0000
   0.750   0.5715   0.02034   0.01405  -0.1150   0.7183   1.0000
   1.000   0.5991   0.02013   0.01375  -0.1149   0.7171   1.0000
   1.250   0.6277   0.01988   0.01342  -0.1150   0.7162   1.0000
   1.500   0.6573   0.01959   0.01305  -0.1152   0.7154   1.0000
   2.000   0.6726   0.02065   0.01402  -0.1089   0.7033   1.0000
   2.250   0.6929   0.02074   0.01407  -0.1077   0.7002   1.0000
   2.750   0.7250   0.02128   0.01455  -0.1042   0.6906   1.0000
   3.000   0.7548   0.02096   0.01419  -0.1044   0.6895   1.0000
   3.250   0.7861   0.02057   0.01378  -0.1049   0.6885   1.0000
   3.750   0.8131   0.02141   0.01460  -0.1008   0.6764   1.0000
   4.000   0.8448   0.02099   0.01417  -0.1013   0.6752   1.0000
   4.500   0.8757   0.02172   0.01492  -0.0979   0.6631   1.0000
   4.750   0.9082   0.02126   0.01446  -0.0985   0.6615   1.0000
   5.250   0.9431   0.02181   0.01507  -0.0957   0.6490   1.0000
   5.500   0.9757   0.02134   0.01461  -0.0964   0.6467   1.0000
   5.750   0.9821   0.02219   0.01551  -0.0936   0.6365   1.0000
   6.000   1.0166   0.02161   0.01495  -0.0945   0.6339   1.0000
   6.250   1.0251   0.02239   0.01577  -0.0920   0.6237   1.0000
   6.500   1.0595   0.02182   0.01524  -0.0928   0.6202   1.0000
   6.750   1.0715   0.02242   0.01589  -0.0908   0.6101   1.0000
   7.000   1.1062   0.02184   0.01534  -0.0918   0.6057   1.0000
   7.250   1.1194   0.02240   0.01595  -0.0899   0.5952   1.0000
   7.500   1.1413   0.02250   0.01611  -0.0892   0.5863   1.0000
   7.750   1.1696   0.02225   0.01589  -0.0893   0.5780   1.0000
   8.000   1.1861   0.02264   0.01632  -0.0879   0.5664   1.0000
   8.250   1.2055   0.02288   0.01659  -0.0868   0.5545   1.0000
   8.500   1.2251   0.02310   0.01684  -0.0858   0.5418   1.0000
   8.750   1.2438   0.02339   0.01717  -0.0846   0.5286   1.0000
   9.000   1.2607   0.02377   0.01756  -0.0833   0.5138   1.0000
   9.250   1.2752   0.02425   0.01801  -0.0816   0.4953   1.0000
   9.500   1.2855   0.02497   0.01868  -0.0794   0.4743   1.0000
   9.750   1.2842   0.02622   0.01970  -0.0757   0.4367   1.0000
  10.000   1.2821   0.02769   0.02099  -0.0722   0.4033   1.0000
  10.250   1.2775   0.02941   0.02252  -0.0686   0.3680   1.0000
  10.500   1.2727   0.03129   0.02421  -0.0652   0.3343   1.0000
  10.750   1.2642   0.03354   0.02623  -0.0616   0.2947   1.0000
  11.000   1.2578   0.03580   0.02831  -0.0584   0.2576   1.0000
  11.250   1.2523   0.03811   0.03043  -0.0556   0.2222   1.0000
  11.500   1.2389   0.04115   0.03310  -0.0523   0.1703   1.0000
  11.750   1.2256   0.04432   0.03589  -0.0492   0.1173   1.0000
  12.250   1.2093   0.05018   0.04125  -0.0444   0.0420   1.0000
  12.500   1.1967   0.05371   0.04452  -0.0420   0.0114   1.0000
  12.750   1.1977   0.05611   0.04699  -0.0405   0.0085   1.0000
  13.000   1.2027   0.05816   0.04913  -0.0394   0.0077   1.0000
  13.250   1.2068   0.06033   0.05146  -0.0383   0.0071   1.0000
  13.500   1.2090   0.06270   0.05394  -0.0373   0.0057   1.0000
  13.750   1.2114   0.06514   0.05652  -0.0364   0.0055   1.0000
  14.000   1.2105   0.06799   0.05952  -0.0353   0.0047   1.0000
  14.250   1.2124   0.07060   0.06229  -0.0346   0.0046   1.0000
  14.500   1.2128   0.07343   0.06528  -0.0339   0.0045   1.0000
  14.750   1.2126   0.07635   0.06834  -0.0333   0.0042   1.0000
  15.000   1.2111   0.07951   0.07164  -0.0328   0.0040   1.0000
  15.250   1.2112   0.08254   0.07480  -0.0325   0.0041   1.0000
  15.500   1.2070   0.08615   0.07855  -0.0322   0.0038   1.0000
  15.750   1.2055   0.08948   0.08200  -0.0321   0.0038   1.0000
  16.000   1.2027   0.09301   0.08565  -0.0321   0.0037   1.0000
  16.250   1.1991   0.09667   0.08943  -0.0322   0.0036   1.0000
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