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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 200,000
Max Cl/Cd: 53.55 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nl722343-il-200000.txt
Download as CSV file: xf-nl722343-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4961   0.08625   0.08264  -0.0286   1.0000   0.0405
  -8.500  -0.5014   0.08209   0.07854  -0.0308   1.0000   0.0414
  -8.250  -0.5118   0.07766   0.07416  -0.0337   1.0000   0.0417
  -8.000  -0.5273   0.07382   0.07035  -0.0353   1.0000   0.0418
  -7.750  -0.5369   0.06992   0.06642  -0.0364   1.0000   0.0425
  -7.500  -0.5463   0.06617   0.06256  -0.0369   1.0000   0.0439
  -7.250  -0.5595   0.06415   0.06014  -0.0360   1.0000   0.0452
  -7.000  -0.5627   0.06239   0.05809  -0.0337   1.0000   0.0455
  -6.750  -0.5631   0.05540   0.05126  -0.0330   1.0000   0.0466
  -6.500  -0.5569   0.05252   0.04846  -0.0314   1.0000   0.0478
  -6.250  -0.5506   0.05012   0.04601  -0.0297   1.0000   0.0493
  -6.000  -0.5430   0.04767   0.04344  -0.0282   1.0000   0.0518
  -5.500  -0.5244   0.04159   0.03673  -0.0255   1.0000   0.0593
  -5.250  -0.5109   0.03945   0.03462  -0.0244   1.0000   0.0627
  -5.000  -0.4960   0.03740   0.03205  -0.0231   1.0000   0.0717
  -4.750  -0.4802   0.03486   0.02962  -0.0224   1.0000   0.0757
  -4.500  -0.4624   0.03298   0.02734  -0.0214   1.0000   0.0864
  -4.250  -0.4436   0.03082   0.02521  -0.0206   1.0000   0.0914
  -4.000  -0.4241   0.02889   0.02308  -0.0200   1.0000   0.1040
  -3.750  -0.3827   0.02322   0.01612  -0.0168   1.0000   0.0432
  -3.500  -0.3551   0.02111   0.01343  -0.0153   1.0000   0.0364
  -3.250  -0.3306   0.01980   0.01196  -0.0144   1.0000   0.0358
  -3.000  -0.3064   0.01835   0.01038  -0.0135   1.0000   0.0365
  -2.750  -0.2832   0.01711   0.00919  -0.0128   1.0000   0.0389
  -2.500  -0.2599   0.01623   0.00829  -0.0118   1.0000   0.0397
  -2.250  -0.2368   0.01552   0.00758  -0.0109   1.0000   0.0412
  -2.000  -0.2137   0.01494   0.00698  -0.0101   1.0000   0.0437
  -1.750  -0.1905   0.01429   0.00634  -0.0094   1.0000   0.0485
  -1.500  -0.1596   0.01382   0.00591  -0.0103   0.9981   0.0643
  -1.250  -0.1369   0.01202   0.00661  -0.0094   0.9945   0.7306
  -1.000  -0.1104   0.01241   0.00715  -0.0077   0.9881   0.7927
  -0.750  -0.0884   0.01247   0.00741  -0.0048   0.9808   0.8441
  -0.500  -0.0585   0.01248   0.00749  -0.0038   0.9718   0.8825
  -0.250  -0.0050   0.01230   0.00724  -0.0081   0.9569   0.8918
   0.000   0.0555   0.01193   0.00677  -0.0141   0.9413   0.8923
   0.250   0.1048   0.01168   0.00645  -0.0183   0.9335   0.8923
   0.500   0.1434   0.01149   0.00622  -0.0203   0.9250   0.8932
   0.750   0.1929   0.01120   0.00592  -0.0244   0.9189   0.8933
   1.000   0.2322   0.01097   0.00568  -0.0265   0.9103   0.8936
   1.250   0.2784   0.01063   0.00535  -0.0298   0.9025   0.8938
   1.500   0.3127   0.01038   0.00512  -0.0306   0.8898   0.8950
   1.750   0.3474   0.01011   0.00486  -0.0315   0.8750   0.8959
   2.000   0.3815   0.00984   0.00461  -0.0322   0.8564   0.8967
   2.250   0.4101   0.00962   0.00441  -0.0318   0.8298   0.8979
   2.500   0.4400   0.00942   0.00416  -0.0315   0.7899   0.8992
   2.750   0.4680   0.00938   0.00379  -0.0305   0.6770   0.9010
   3.000   0.4822   0.01029   0.00375  -0.0274   0.4986   0.9039
   3.250   0.4967   0.01127   0.00403  -0.0251   0.3649   0.9070
   3.500   0.5175   0.01197   0.00435  -0.0242   0.3010   0.9102
   3.750   0.5413   0.01249   0.00466  -0.0237   0.2719   0.9135
   4.000   0.5666   0.01290   0.00498  -0.0234   0.2543   0.9172
   4.250   0.5926   0.01331   0.00534  -0.0232   0.2411   0.9218
   4.500   0.6195   0.01369   0.00569  -0.0233   0.2305   0.9275
   4.750   0.6483   0.01407   0.00610  -0.0237   0.2213   0.9345
   5.000   0.6782   0.01460   0.00658  -0.0244   0.2127   0.9442
   5.250   0.7118   0.01493   0.00703  -0.0259   0.2040   0.9585
   5.500   0.7464   0.01548   0.00758  -0.0277   0.1953   0.9972
   5.750   0.7732   0.01587   0.00803  -0.0279   0.1871   1.0000
   6.000   0.7996   0.01636   0.00855  -0.0280   0.1780   1.0000
   6.250   0.8249   0.01675   0.00890  -0.0280   0.1664   1.0000
   6.500   0.8498   0.01698   0.00917  -0.0279   0.1541   1.0000
   6.750   0.8751   0.01718   0.00950  -0.0277   0.1426   1.0000
   7.000   0.9001   0.01742   0.00982  -0.0275   0.1299   1.0000
   7.250   0.9250   0.01753   0.01001  -0.0273   0.1139   1.0000
   7.500   0.9500   0.01774   0.01017  -0.0270   0.0859   1.0000
   7.750   0.9696   0.01900   0.01127  -0.0259   0.0598   1.0000
   8.000   0.9889   0.02029   0.01255  -0.0247   0.0500   1.0000
   8.250   1.0064   0.02181   0.01402  -0.0233   0.0447   1.0000
   8.500   1.0278   0.02282   0.01519  -0.0224   0.0408   1.0000
   8.750   1.0467   0.02411   0.01647  -0.0213   0.0377   1.0000
   9.000   1.0654   0.02599   0.01844  -0.0202   0.0358   1.0000
   9.250   1.0856   0.02752   0.02016  -0.0191   0.0344   1.0000
   9.500   1.1048   0.02924   0.02208  -0.0180   0.0332   1.0000
   9.750   1.1227   0.03112   0.02417  -0.0168   0.0323   1.0000
  10.000   1.1391   0.03301   0.02622  -0.0155   0.0313   1.0000
  10.250   1.1541   0.03515   0.02850  -0.0143   0.0304   1.0000
  10.500   1.1633   0.03895   0.03254  -0.0128   0.0295   1.0000
  10.750   1.1682   0.04154   0.03549  -0.0104   0.0291   1.0000
  11.000   1.1691   0.04429   0.03862  -0.0077   0.0290   1.0000
  11.250   1.1650   0.04740   0.04207  -0.0048   0.0289   1.0000
  11.500   1.1536   0.05032   0.04529  -0.0012   0.0289   1.0000
  11.750   1.1388   0.05359   0.04881   0.0019   0.0290   1.0000
  12.000   1.1215   0.05721   0.05265   0.0042   0.0290   1.0000
  12.250   1.1019   0.06129   0.05695   0.0053   0.0291   1.0000
  12.500   1.0820   0.06621   0.06205   0.0050   0.0293   1.0000
  12.750   1.0629   0.07137   0.06740   0.0035   0.0294   1.0000
  13.000   1.0414   0.07719   0.07341  -0.0001   0.0296   1.0000
  13.250   1.0149   0.08547   0.08191  -0.0072   0.0299   1.0000
  13.500   0.6957   0.13563   0.13262  -0.0368   0.0457   1.0000
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