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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 500,000
Max Cl/Cd: 70.16 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nl722343-il-500000.txt
Download as CSV file: xf-nl722343-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5041   0.08351   0.08118  -0.0296   1.0000   0.0172
  -8.750  -0.5128   0.07713   0.07484  -0.0349   1.0000   0.0175
  -8.500  -0.5276   0.07192   0.06964  -0.0385   1.0000   0.0175
  -8.250  -0.5439   0.06855   0.06626  -0.0385   1.0000   0.0174
  -8.000  -0.5568   0.06373   0.06132  -0.0390   1.0000   0.0176
  -7.750  -0.5671   0.05994   0.05740  -0.0375   1.0000   0.0177
  -7.500  -0.5759   0.05682   0.05414  -0.0348   1.0000   0.0178
  -7.250  -0.5828   0.05398   0.05114  -0.0318   1.0000   0.0178
  -7.000  -0.5892   0.04892   0.04601  -0.0305   0.9996   0.0181
  -6.750  -0.5678   0.04560   0.04260  -0.0331   0.9973   0.0184
  -6.500  -0.5438   0.04258   0.03946  -0.0355   0.9952   0.0189
  -6.250  -0.5198   0.03947   0.03617  -0.0372   0.9925   0.0197
  -6.000  -0.4876   0.03657   0.03260  -0.0380   0.9892   0.0225
  -5.750  -0.4660   0.03081   0.02661  -0.0400   0.9869   0.0233
  -5.500  -0.4372   0.02889   0.02465  -0.0417   0.9855   0.0244
  -5.250  -0.4109   0.02711   0.02262  -0.0418   0.9822   0.0271
  -5.000  -0.3842   0.02418   0.01927  -0.0422   0.9791   0.0299
  -4.750  -0.3545   0.02266   0.01768  -0.0433   0.9771   0.0316
  -4.500  -0.3227   0.02121   0.01585  -0.0442   0.9753   0.0375
  -4.250  -0.2908   0.01610   0.01020  -0.0428   0.9746   0.0202
  -4.000  -0.2590   0.01418   0.00798  -0.0430   0.9738   0.0184
  -3.750  -0.2338   0.01324   0.00700  -0.0425   0.9705   0.0186
  -3.500  -0.2066   0.01250   0.00625  -0.0424   0.9675   0.0191
  -3.250  -0.1766   0.01191   0.00565  -0.0430   0.9653   0.0201
  -3.000  -0.1442   0.01139   0.00511  -0.0440   0.9634   0.0213
  -2.750  -0.1066   0.01079   0.00449  -0.0461   0.9616   0.0234
  -2.500  -0.0660   0.01020   0.00391  -0.0488   0.9602   0.0266
  -2.250  -0.0346   0.00967   0.00337  -0.0493   0.9531   0.0331
  -2.000   0.0013   0.00756   0.00259  -0.0520   0.9481   0.3979
  -1.750   0.0296   0.00678   0.00263  -0.0517   0.9374   0.6786
  -1.500   0.0625   0.00680   0.00261  -0.0520   0.9265   0.7051
  -1.250   0.0912   0.00700   0.00283  -0.0514   0.9186   0.7328
  -1.000   0.1164   0.00712   0.00304  -0.0501   0.9115   0.7550
  -0.750   0.1429   0.00716   0.00311  -0.0493   0.9044   0.7699
  -0.500   0.1710   0.00716   0.00306  -0.0491   0.8966   0.7748
  -0.250   0.1991   0.00713   0.00297  -0.0489   0.8880   0.7782
   0.000   0.2259   0.00706   0.00288  -0.0485   0.8780   0.7804
   0.250   0.2539   0.00701   0.00279  -0.0483   0.8676   0.7816
   0.500   0.2817   0.00697   0.00270  -0.0481   0.8551   0.7820
   0.750   0.3087   0.00693   0.00262  -0.0478   0.8395   0.7824
   1.000   0.3354   0.00691   0.00255  -0.0474   0.8199   0.7831
   1.250   0.3620   0.00692   0.00247  -0.0469   0.7933   0.7835
   1.500   0.3870   0.00700   0.00239  -0.0460   0.7447   0.7839
   1.750   0.4040   0.00755   0.00234  -0.0435   0.6100   0.7843
   2.000   0.4223   0.00820   0.00249  -0.0417   0.4934   0.7848
   2.250   0.4430   0.00878   0.00263  -0.0405   0.3944   0.7853
   2.500   0.4654   0.00930   0.00279  -0.0396   0.3130   0.7861
   2.750   0.4892   0.00973   0.00294  -0.0390   0.2556   0.7867
   3.000   0.5143   0.01005   0.00311  -0.0386   0.2241   0.7871
   3.250   0.5400   0.01030   0.00326  -0.0383   0.2067   0.7876
   3.500   0.5660   0.01053   0.00343  -0.0380   0.1952   0.7881
   3.750   0.5921   0.01073   0.00360  -0.0378   0.1873   0.7886
   4.000   0.6181   0.01096   0.00381  -0.0375   0.1807   0.7892
   4.250   0.6446   0.01112   0.00399  -0.0373   0.1752   0.7898
   4.500   0.6702   0.01139   0.00422  -0.0369   0.1695   0.7905
   4.750   0.6965   0.01158   0.00445  -0.0367   0.1652   0.7911
   5.000   0.7230   0.01174   0.00463  -0.0365   0.1597   0.7918
   5.250   0.7482   0.01201   0.00488  -0.0361   0.1525   0.7926
   5.500   0.7752   0.01206   0.00499  -0.0360   0.1458   0.7935
   5.750   0.8003   0.01232   0.00524  -0.0356   0.1381   0.7947
   6.000   0.8271   0.01239   0.00540  -0.0355   0.1320   0.7959
   6.250   0.8524   0.01264   0.00563  -0.0351   0.1239   0.7971
   6.500   0.8791   0.01273   0.00578  -0.0350   0.1145   0.7983
   6.750   0.9051   0.01290   0.00596  -0.0347   0.1010   0.7997
   7.000   0.9295   0.01327   0.00621  -0.0343   0.0785   0.8011
   7.250   0.9515   0.01398   0.00678  -0.0335   0.0509   0.8027
   7.500   0.9728   0.01484   0.00753  -0.0326   0.0332   0.8044
   7.750   0.9951   0.01554   0.00826  -0.0317   0.0277   0.8062
   8.000   1.0174   0.01619   0.00896  -0.0309   0.0249   0.8083
   8.250   1.0379   0.01703   0.00991  -0.0297   0.0229   0.8107
   8.500   1.0597   0.01767   0.01067  -0.0288   0.0215   0.8136
   8.750   1.0806   0.01837   0.01146  -0.0278   0.0203   0.8170
   9.000   1.0987   0.01938   0.01255  -0.0264   0.0191   0.8209
   9.250   1.1150   0.02055   0.01387  -0.0248   0.0182   0.8262
   9.500   1.1340   0.02135   0.01482  -0.0235   0.0177   0.8336
   9.750   1.1513   0.02224   0.01590  -0.0219   0.0173   0.8456
  10.000   1.1659   0.02302   0.01696  -0.0198   0.0167   0.8876
  10.250   1.1896   0.02424   0.01838  -0.0199   0.0163   1.0000
  10.500   1.2054   0.02543   0.01968  -0.0184   0.0158   1.0000
  10.750   1.2196   0.02676   0.02112  -0.0168   0.0155   1.0000
  11.000   1.2323   0.02819   0.02264  -0.0150   0.0152   1.0000
  11.250   1.2426   0.02992   0.02448  -0.0130   0.0150   1.0000
  11.500   1.2484   0.03218   0.02689  -0.0106   0.0147   1.0000
  11.750   1.2505   0.03466   0.02955  -0.0078   0.0145   1.0000
  12.000   1.2475   0.03753   0.03265  -0.0046   0.0144   1.0000
  12.250   1.2433   0.03964   0.03498  -0.0014   0.0143   1.0000
  12.500   1.2390   0.04163   0.03716   0.0014   0.0143   1.0000
  12.750   1.2333   0.04368   0.03940   0.0037   0.0142   1.0000
  13.000   1.2255   0.04612   0.04204   0.0054   0.0140   1.0000
  13.250   1.2126   0.04968   0.04580   0.0065   0.0140   1.0000
  13.500   1.2002   0.05332   0.04964   0.0066   0.0139   1.0000
  13.750   1.1835   0.05809   0.05461   0.0055   0.0139   1.0000
  14.000   1.1653   0.06386   0.06055   0.0029   0.0140   1.0000
  14.250   1.1470   0.07048   0.06737  -0.0014   0.0140   1.0000
  14.500   1.1237   0.07903   0.07610  -0.0072   0.0141   1.0000
  14.750   1.1016   0.08806   0.08528  -0.0135   0.0141   1.0000
  15.000   1.0746   0.09853   0.09589  -0.0204   0.0143   1.0000
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