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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 50,000
Max Cl/Cd: 29.23 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nl722343-il-50000-n5.txt
Download as CSV file: xf-nl722343-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-43 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4984   0.11200   0.10461  -0.0178   1.0000   0.1211
  -9.500  -0.5261   0.11017   0.10299  -0.0236   1.0000   0.1283
  -9.250  -0.5184   0.10565   0.09853  -0.0234   1.0000   0.1294
  -9.000  -0.5018   0.09616   0.08889  -0.0271   1.0000   0.0656
  -8.750  -0.5152   0.08960   0.08240  -0.0333   1.0000   0.0557
  -8.500  -0.5145   0.08586   0.07871  -0.0333   1.0000   0.0540
  -8.250  -0.5217   0.08200   0.07492  -0.0344   1.0000   0.0528
  -8.000  -0.5294   0.07803   0.07098  -0.0354   1.0000   0.0514
  -7.500  -0.5565   0.06866   0.06114  -0.0381   1.0000   0.0454
  -7.250  -0.5537   0.06511   0.05751  -0.0374   1.0000   0.0451
  -7.000  -0.5504   0.06162   0.05388  -0.0365   1.0000   0.0450
  -6.750  -0.5455   0.05825   0.05033  -0.0356   1.0000   0.0448
  -6.500  -0.5398   0.05485   0.04662  -0.0345   1.0000   0.0450
  -6.250  -0.5309   0.05162   0.04310  -0.0334   1.0000   0.0449
  -6.000  -0.5200   0.04846   0.03965  -0.0322   1.0000   0.0448
  -5.750  -0.5071   0.04544   0.03635  -0.0310   1.0000   0.0444
  -5.500  -0.4924   0.04254   0.03312  -0.0298   1.0000   0.0441
  -5.250  -0.4758   0.03978   0.02999  -0.0285   1.0000   0.0439
  -5.000  -0.4574   0.03724   0.02707  -0.0273   1.0000   0.0439
  -4.750  -0.4374   0.03491   0.02435  -0.0260   1.0000   0.0441
  -4.500  -0.4160   0.03289   0.02189  -0.0247   1.0000   0.0449
  -4.250  -0.3948   0.03091   0.01970  -0.0237   1.0000   0.0469
  -4.000  -0.3732   0.02935   0.01803  -0.0226   1.0000   0.0496
  -3.750  -0.3504   0.02788   0.01638  -0.0212   1.0000   0.0517
  -3.500  -0.3273   0.02659   0.01492  -0.0196   1.0000   0.0536
  -3.250  -0.3049   0.02558   0.01365  -0.0179   1.0000   0.0568
  -3.000  -0.2847   0.02447   0.01261  -0.0164   1.0000   0.0623
  -2.750  -0.2638   0.02361   0.01160  -0.0148   1.0000   0.0683
  -2.500  -0.2428   0.02266   0.01063  -0.0138   1.0000   0.0784
  -2.250  -0.2214   0.02175   0.00968  -0.0128   1.0000   0.0963
  -2.000  -0.1996   0.01977   0.00862  -0.0128   1.0000   0.2151
  -1.750  -0.2097   0.01866   0.00974  -0.0028   1.0000   0.7686
  -1.500  -0.1286   0.01917   0.01018  -0.0036   1.0000   0.9716
  -1.250  -0.0939   0.01903   0.00975  -0.0057   1.0000   0.9802
  -1.000  -0.0636   0.01891   0.00940  -0.0071   1.0000   0.9893
  -0.750  -0.0367   0.01883   0.00914  -0.0081   1.0000   1.0000
  -0.500  -0.0326   0.01865   0.00889  -0.0048   1.0000   1.0000
  -0.250  -0.0278   0.01847   0.00866  -0.0018   1.0000   1.0000
   0.000  -0.0198   0.01835   0.00846   0.0007   1.0000   1.0000
   0.250  -0.0067   0.01831   0.00834   0.0023   1.0000   1.0000
   0.500   0.0103   0.01836   0.00829   0.0032   1.0000   1.0000
   0.750   0.0295   0.01848   0.00833   0.0037   1.0000   1.0000
   1.000   0.0501   0.01865   0.00844   0.0040   1.0000   1.0000
   1.250   0.1004   0.01921   0.00897  -0.0013   0.9863   1.0000
   1.500   0.1572   0.01964   0.00939  -0.0075   0.9661   1.0000
   1.750   0.2245   0.01975   0.00955  -0.0148   0.9362   1.0000
   2.000   0.2841   0.01954   0.00944  -0.0201   0.9063   1.0000
   2.250   0.3322   0.01926   0.00926  -0.0232   0.8797   1.0000
   2.500   0.3738   0.01894   0.00908  -0.0250   0.8514   1.0000
   2.750   0.4053   0.01865   0.00890  -0.0249   0.8166   1.0000
   3.000   0.4346   0.01839   0.00873  -0.0243   0.7719   1.0000
   3.250   0.4636   0.01814   0.00853  -0.0235   0.6996   1.0000
   3.500   0.5178   0.01802   0.00775  -0.0256   0.5510   1.0000
   3.750   0.5386   0.01888   0.00795  -0.0239   0.4499   1.0000
   4.000   0.5586   0.01978   0.00844  -0.0226   0.3892   1.0000
   4.250   0.5808   0.02065   0.00906  -0.0219   0.3504   1.0000
   4.500   0.6051   0.02146   0.00971  -0.0216   0.3223   1.0000
   4.750   0.6310   0.02225   0.01040  -0.0215   0.3011   1.0000
   5.000   0.6583   0.02304   0.01117  -0.0216   0.2844   1.0000
   5.250   0.6865   0.02383   0.01201  -0.0218   0.2696   1.0000
   5.500   0.7150   0.02465   0.01285  -0.0221   0.2560   1.0000
   5.750   0.7429   0.02550   0.01373  -0.0223   0.2435   1.0000
   6.000   0.7701   0.02635   0.01475  -0.0223   0.2307   1.0000
   6.250   0.7964   0.02726   0.01582  -0.0223   0.2182   1.0000
   6.500   0.8220   0.02825   0.01695  -0.0221   0.2062   1.0000
   6.750   0.8464   0.02926   0.01811  -0.0217   0.1936   1.0000
   7.000   0.8695   0.03029   0.01926  -0.0212   0.1802   1.0000
   7.250   0.8913   0.03134   0.02046  -0.0205   0.1661   1.0000
   7.500   0.9111   0.03237   0.02170  -0.0196   0.1504   1.0000
   7.750   0.9285   0.03330   0.02289  -0.0183   0.1330   1.0000
   8.000   0.9452   0.03424   0.02401  -0.0170   0.1161   1.0000
   8.250   0.9616   0.03524   0.02517  -0.0157   0.1011   1.0000
   8.500   0.9775   0.03637   0.02640  -0.0144   0.0887   1.0000
   8.750   0.9932   0.03797   0.02818  -0.0131   0.0784   1.0000
   9.000   1.0079   0.04020   0.03069  -0.0117   0.0710   1.0000
   9.250   1.0215   0.04199   0.03251  -0.0104   0.0660   1.0000
   9.500   1.0315   0.04497   0.03593  -0.0089   0.0613   1.0000
   9.750   1.0396   0.04753   0.03876  -0.0073   0.0576   1.0000
  10.000   1.0480   0.04988   0.04121  -0.0059   0.0552   1.0000
  10.250   1.0490   0.05338   0.04504  -0.0041   0.0539   1.0000
  10.500   1.0396   0.05758   0.04972  -0.0020   0.0529   1.0000
  10.750   1.0232   0.06169   0.05419   0.0002   0.0523   1.0000
  11.000   1.0022   0.06629   0.05904   0.0013   0.0521   1.0000
  11.250   0.9775   0.07176   0.06473   0.0007   0.0522   1.0000
  11.500   0.9504   0.07848   0.07162  -0.0022   0.0527   1.0000
  11.750   0.9216   0.08713   0.08037  -0.0078   0.0534   1.0000
  12.000   0.8953   0.09740   0.09067  -0.0149   0.0541   1.0000
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