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LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il)
Reynolds number: 50,000
Max Cl/Cd: 15.4 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l7769-il-50000-n5.txt
Download as CSV file: xf-l7769-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LISSAMAN 7769 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3749   0.11056   0.10331   0.0053   0.6451   0.1247
  -8.250  -0.3787   0.10846   0.10127   0.0015   0.6421   0.1260
  -8.000  -0.3832   0.10615   0.09904  -0.0023   0.6388   0.1264
  -7.750  -0.3610   0.10107   0.09394  -0.0013   0.6342   0.1283
  -7.500  -0.3449   0.09758   0.09041  -0.0010   0.6304   0.1315
  -7.250  -0.3386   0.09470   0.08752  -0.0023   0.6275   0.1336
  -7.000  -0.3341   0.09180   0.08468  -0.0046   0.6242   0.1344
  -6.500  -0.3306   0.07902   0.07165  -0.0222   0.6200   0.0851
  -6.250  -0.3152   0.07593   0.06856  -0.0223   0.6164   0.0837
  -6.000  -0.3015   0.07249   0.06504  -0.0241   0.6134   0.0821
  -5.750  -0.2870   0.06884   0.06127  -0.0267   0.6105   0.0808
  -5.500  -0.2701   0.06517   0.05749  -0.0299   0.6069   0.0807
  -5.250  -0.2520   0.06165   0.05381  -0.0326   0.6035   0.0812
  -5.000  -0.2327   0.05824   0.05017  -0.0349   0.6005   0.0814
  -4.750  -0.2122   0.05493   0.04661  -0.0368   0.5978   0.0810
  -4.500  -0.1907   0.05176   0.04312  -0.0383   0.5954   0.0805
  -4.250  -0.1665   0.04876   0.03984  -0.0401   0.5918   0.0804
  -4.000  -0.1419   0.04601   0.03676  -0.0414   0.5883   0.0806
  -3.750  -0.1168   0.04351   0.03388  -0.0422   0.5851   0.0817
  -3.500  -0.0907   0.04109   0.03091  -0.0429   0.5821   0.0843
  -3.250  -0.0651   0.03937   0.02882  -0.0430   0.5796   0.0866
  -3.000  -0.0382   0.03824   0.02758  -0.0437   0.5762   0.0887
  -2.750  -0.0108   0.03698   0.02609  -0.0442   0.5730   0.0910
  -2.500   0.0169   0.03570   0.02450  -0.0444   0.5699   0.0941
  -2.250   0.0447   0.03457   0.02298  -0.0443   0.5670   0.0994
  -2.000   0.0708   0.03413   0.02246  -0.0441   0.5644   0.1056
  -1.750   0.0992   0.03337   0.02141  -0.0442   0.5614   0.1133
  -1.500   0.1271   0.03311   0.02113  -0.0448   0.5578   0.1232
  -1.250   0.1550   0.03288   0.02083  -0.0451   0.5549   0.1366
  -1.000   0.1822   0.03272   0.02055  -0.0452   0.5522   0.1537
  -0.750   0.2097   0.03255   0.02027  -0.0451   0.5496   0.1729
  -0.500   0.2369   0.03230   0.01995  -0.0449   0.5474   0.1898
  -0.250   0.2642   0.03238   0.02003  -0.0454   0.5440   0.2046
   0.000   0.2906   0.03257   0.02027  -0.0460   0.5404   0.2200
   0.250   0.3163   0.03274   0.02051  -0.0463   0.5376   0.2350
   0.500   0.3416   0.03291   0.02074  -0.0463   0.5350   0.2539
   0.750   0.3665   0.03294   0.02092  -0.0461   0.5326   0.2813
   1.000   0.3898   0.03248   0.02109  -0.0456   0.5306   0.3813
   1.500   0.4549   0.03326   0.02296  -0.0492   0.5229   1.0000
   1.750   0.4785   0.03420   0.02374  -0.0494   0.5198   1.0000
   2.000   0.5022   0.03498   0.02435  -0.0491   0.5169   1.0000
   2.250   0.5262   0.03564   0.02484  -0.0485   0.5146   1.0000
   2.500   0.5478   0.03691   0.02605  -0.0490   0.5111   1.0000
   2.750   0.5669   0.03858   0.02773  -0.0500   0.5063   1.0000
   3.000   0.5880   0.03970   0.02879  -0.0501   0.5024   1.0000
   3.250   0.6107   0.04054   0.02955  -0.0496   0.4995   1.0000
   3.500   0.6346   0.04120   0.03011  -0.0488   0.4971   1.0000
   3.750   0.6461   0.04367   0.03266  -0.0505   0.4904   1.0000
   4.000   0.6644   0.04499   0.03397  -0.0505   0.4855   1.0000
   4.250   0.6871   0.04576   0.03471  -0.0498   0.4823   1.0000
   4.500   0.7116   0.04629   0.03517  -0.0487   0.4795   1.0000
   4.750   0.7143   0.04932   0.03831  -0.0504   0.4699   1.0000
   5.000   0.7373   0.04995   0.03891  -0.0495   0.4659   1.0000
   5.500   0.7612   0.05348   0.04251  -0.0496   0.4521   1.0000
   5.750   0.7868   0.05381   0.04284  -0.0485   0.4486   1.0000
   6.250   0.8068   0.05749   0.04660  -0.0484   0.4339   1.0000
   6.500   0.8363   0.05745   0.04658  -0.0470   0.4312   1.0000
   6.750   0.8243   0.06109   0.05027  -0.0480   0.4191   1.0000
   7.000   0.8550   0.06100   0.05022  -0.0467   0.4160   1.0000
   7.250   0.8398   0.06451   0.05376  -0.0468   0.4042   1.0000
   7.500   0.8705   0.06436   0.05367  -0.0456   0.4007   1.0000
   7.750   0.8586   0.06773   0.05706  -0.0457   0.3890   1.0000
   8.000   0.8797   0.06830   0.05770  -0.0448   0.3837   1.0000
   8.250   0.8800   0.07069   0.06013  -0.0447   0.3736   1.0000
   8.750   0.9025   0.07353   0.06311  -0.0436   0.3580   1.0000
   9.000   0.9007   0.07632   0.06594  -0.0438   0.3474   1.0000
   9.250   0.9265   0.07616   0.06586  -0.0426   0.3425   1.0000
   9.500   0.9213   0.07941   0.06916  -0.0431   0.3311   1.0000
   9.750   0.9483   0.07901   0.06888  -0.0417   0.3267   1.0000
  10.000   0.9429   0.08246   0.07238  -0.0423   0.3154   1.0000
  10.250   0.9414   0.08559   0.07557  -0.0428   0.3052   1.0000
  10.500   0.9643   0.08556   0.07564  -0.0417   0.3000   1.0000
  10.750   0.9583   0.08950   0.07964  -0.0426   0.2894   1.0000
  11.000   0.9836   0.08905   0.07931  -0.0413   0.2850   1.0000
  11.250   0.9735   0.09389   0.08422  -0.0427   0.2743   1.0000
  11.500   0.9997   0.09318   0.08363  -0.0412   0.2703   1.0000
  11.750   0.9870   0.09861   0.08912  -0.0430   0.2594   1.0000
  12.000   1.0128   0.09791   0.08854  -0.0415   0.2557   1.0000
  12.250   0.9951   0.10457   0.09525  -0.0440   0.2452   1.0000
  12.500   1.0187   0.10412   0.09493  -0.0427   0.2413   1.0000
  13.000   1.0207   0.11127   0.10227  -0.0444   0.2269   1.0000
  13.500   1.0165   0.12007   0.11123  -0.0471   0.2131   1.0000
  13.750   1.0423   0.11888   0.11017  -0.0454   0.2098   1.0000
  14.000   1.0106   0.12949   0.12079  -0.0505   0.1997   1.0000
  14.250   1.0348   0.12855   0.12002  -0.0489   0.1960   1.0000
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