Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il)
Reynolds number: 200,000
Max Cl/Cd: 74.32 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l7769-il-200000-n5.txt
Download as CSV file: xf-l7769-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4209   0.10679   0.10169   0.0089   0.5279   0.0463
  -9.000  -0.4245   0.10270   0.09763   0.0053   0.5265   0.0466
  -8.750  -0.4231   0.09882   0.09377   0.0028   0.5246   0.0466
  -8.500  -0.4108   0.09379   0.08869   0.0038   0.5222   0.0392
  -8.250  -0.4017   0.09099   0.08589   0.0034   0.5201   0.0384
  -8.000  -0.3987   0.08752   0.08242   0.0018   0.5185   0.0377
  -7.750  -0.3987   0.08382   0.07873  -0.0001   0.5170   0.0370
  -7.500  -0.4031   0.08002   0.07494  -0.0024   0.5157   0.0365
  -7.250  -0.4023   0.07557   0.07047  -0.0065   0.5145   0.0363
  -7.000  -0.3969   0.07118   0.06602  -0.0106   0.5131   0.0366
  -6.750  -0.3892   0.06629   0.06109  -0.0150   0.5115   0.0369
  -6.500  -0.3800   0.06054   0.05524  -0.0198   0.5099   0.0365
  -6.250  -0.3687   0.05399   0.04850  -0.0245   0.5082   0.0361
  -6.000  -0.3552   0.04666   0.04087  -0.0287   0.5065   0.0359
  -5.750  -0.3445   0.03488   0.02833  -0.0328   0.5054   0.0363
  -5.500  -0.3278   0.02752   0.02001  -0.0340   0.5037   0.0373
  -5.250  -0.3042   0.02480   0.01674  -0.0339   0.5014   0.0377
  -5.000  -0.2789   0.02309   0.01463  -0.0337   0.4993   0.0381
  -4.750  -0.2527   0.02182   0.01304  -0.0335   0.4974   0.0386
  -4.500  -0.2259   0.02082   0.01178  -0.0332   0.4955   0.0391
  -4.250  -0.1987   0.01998   0.01075  -0.0329   0.4931   0.0395
  -4.000  -0.1714   0.01923   0.00987  -0.0327   0.4908   0.0400
  -3.750  -0.1443   0.01860   0.00920  -0.0325   0.4886   0.0409
  -3.500  -0.1168   0.01816   0.00871  -0.0323   0.4863   0.0421
  -3.250  -0.0893   0.01773   0.00821  -0.0320   0.4842   0.0433
  -3.000  -0.0617   0.01729   0.00767  -0.0317   0.4822   0.0444
  -2.750  -0.0342   0.01689   0.00716  -0.0314   0.4804   0.0454
  -2.500  -0.0064   0.01655   0.00675  -0.0312   0.4784   0.0466
  -2.250   0.0214   0.01621   0.00645  -0.0310   0.4763   0.0481
  -2.000   0.0493   0.01596   0.00621  -0.0308   0.4741   0.0503
  -1.750   0.0772   0.01574   0.00596  -0.0306   0.4721   0.0532
  -1.500   0.1051   0.01553   0.00578  -0.0304   0.4702   0.0580
  -1.250   0.1329   0.01535   0.00564  -0.0301   0.4684   0.0664
  -1.000   0.1609   0.01521   0.00553  -0.0299   0.4667   0.0789
  -0.750   0.1889   0.01515   0.00546  -0.0297   0.4651   0.0914
  -0.500   0.2169   0.01514   0.00542  -0.0295   0.4635   0.1019
  -0.250   0.2452   0.01516   0.00545  -0.0294   0.4614   0.1115
   0.000   0.2734   0.01521   0.00557  -0.0293   0.4593   0.1221
   0.250   0.3016   0.01526   0.00566  -0.0293   0.4573   0.1332
   0.500   0.3297   0.01529   0.00571  -0.0291   0.4554   0.1438
   0.750   0.3576   0.01527   0.00571  -0.0290   0.4537   0.1524
   1.000   0.3854   0.01523   0.00568  -0.0289   0.4521   0.1597
   1.250   0.4133   0.01520   0.00566  -0.0287   0.4506   0.1682
   1.500   0.4411   0.01516   0.00564  -0.0285   0.4491   0.1771
   2.000   0.4967   0.01518   0.00573  -0.0283   0.4458   0.2034
   2.250   0.5241   0.01512   0.00591  -0.0282   0.4439   0.2488
   2.750   0.5911   0.01364   0.00628  -0.0302   0.4399   1.0000
   3.000   0.6185   0.01382   0.00642  -0.0300   0.4380   1.0000
   3.250   0.6459   0.01398   0.00653  -0.0298   0.4362   1.0000
   3.500   0.6733   0.01414   0.00664  -0.0295   0.4346   1.0000
   3.750   0.7007   0.01431   0.00678  -0.0293   0.4332   1.0000
   4.000   0.7282   0.01449   0.00691  -0.0291   0.4319   1.0000
   4.250   0.7554   0.01472   0.00717  -0.0290   0.4295   1.0000
   4.500   0.7825   0.01492   0.00746  -0.0288   0.4258   1.0000
   4.750   0.8098   0.01500   0.00754  -0.0286   0.4221   1.0000
   5.000   0.8373   0.01500   0.00751  -0.0284   0.4190   1.0000
   5.250   0.8649   0.01505   0.00752  -0.0281   0.4166   1.0000
   5.500   0.8920   0.01525   0.00777  -0.0280   0.4140   1.0000
   5.750   0.9188   0.01552   0.00815  -0.0279   0.4105   1.0000
   6.000   0.9458   0.01570   0.00839  -0.0277   0.4073   1.0000
   6.250   0.9731   0.01579   0.00851  -0.0275   0.4043   1.0000
   6.500   1.0006   0.01572   0.00840  -0.0272   0.4009   1.0000
   6.750   1.0272   0.01590   0.00872  -0.0271   0.3949   1.0000
   7.000   1.0542   0.01593   0.00880  -0.0269   0.3897   1.0000
   7.250   1.0815   0.01594   0.00881  -0.0267   0.3860   1.0000
   7.500   1.1078   0.01620   0.00921  -0.0266   0.3812   1.0000
   7.750   1.1343   0.01637   0.00948  -0.0264   0.3757   1.0000
   8.000   1.1613   0.01637   0.00949  -0.0261   0.3709   1.0000
   8.250   1.1871   0.01666   0.00996  -0.0260   0.3638   1.0000
   8.500   1.2135   0.01677   0.01012  -0.0258   0.3576   1.0000
   8.750   1.2393   0.01702   0.01051  -0.0257   0.3498   1.0000
   9.000   1.2652   0.01714   0.01068  -0.0254   0.3410   1.0000
   9.250   1.2903   0.01740   0.01103  -0.0252   0.3283   1.0000
   9.500   1.3148   0.01769   0.01136  -0.0250   0.3109   1.0000
   9.750   1.3372   0.01814   0.01173  -0.0246   0.2853   1.0000
  10.000   1.3559   0.01903   0.01247  -0.0242   0.2563   1.0000
  10.250   1.3714   0.02029   0.01361  -0.0237   0.2311   1.0000
  10.500   1.3844   0.02175   0.01499  -0.0233   0.2117   1.0000
  10.750   1.3942   0.02343   0.01663  -0.0228   0.1936   1.0000
  11.000   1.4002   0.02539   0.01859  -0.0225   0.1771   1.0000
  11.250   1.3974   0.02835   0.02159  -0.0232   0.1646   1.0000
  11.500   1.3872   0.03191   0.02520  -0.0239   0.1561   1.0000
  11.750   1.3785   0.03526   0.02855  -0.0242   0.1487   1.0000
  12.000   1.3723   0.03832   0.03164  -0.0243   0.1416   1.0000
  12.250   1.3661   0.04140   0.03473  -0.0244   0.1350   1.0000
  12.500   1.3605   0.04445   0.03778  -0.0245   0.1278   1.0000
  12.750   1.3552   0.04751   0.04086  -0.0247   0.1209   1.0000
  13.000   1.3503   0.05060   0.04396  -0.0250   0.1139   1.0000
  13.250   1.3463   0.05364   0.04702  -0.0253   0.1070   1.0000
  13.500   1.3415   0.05684   0.05023  -0.0257   0.0998   1.0000
  13.750   1.3388   0.06001   0.05342  -0.0262   0.0905   1.0000
  14.000   1.3353   0.06339   0.05682  -0.0269   0.0809   1.0000
  14.250   1.3296   0.06717   0.06056  -0.0278   0.0695   1.0000
  14.500   1.3221   0.07129   0.06462  -0.0289   0.0580   1.0000
  14.750   1.3142   0.07555   0.06882  -0.0301   0.0483   1.0000
  15.000   1.3071   0.07985   0.07310  -0.0314   0.0411   1.0000
  15.250   1.3008   0.08412   0.07739  -0.0326   0.0357   1.0000
  15.500   1.2959   0.08831   0.08162  -0.0340   0.0326   1.0000
  15.750   1.2917   0.09248   0.08586  -0.0353   0.0302   1.0000
  16.250   1.2821   0.10131   0.09484  -0.0385   0.0270   1.0000
  16.500   1.2780   0.10575   0.09939  -0.0401   0.0258   1.0000
  16.750   1.2728   0.11042   0.10415  -0.0420   0.0249   1.0000
  17.000   1.2661   0.11546   0.10927  -0.0441   0.0241   1.0000
<< Back to LISSAMAN 7769 AIRFOIL (l7769-il)

Polar data table (+)

Polar graphs


<< Back to LISSAMAN 7769 AIRFOIL (l7769-il)