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

NACA 23015 (naca23015-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 23015 (naca23015-il)
Reynolds number: 200,000
Max Cl/Cd: 48.38 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23015-il-200000.txt
Download as CSV file: xf-naca23015-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23015                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7990   0.07899   0.07467  -0.0453   0.9999   0.0567
 -13.000  -0.8153   0.07362   0.06921  -0.0469   0.9999   0.0565
 -12.750  -0.8369   0.06855   0.06400  -0.0478   0.9999   0.0562
 -12.500  -0.8612   0.06401   0.05930  -0.0474   0.9999   0.0560
 -12.250  -0.8871   0.06013   0.05523  -0.0453   0.9999   0.0558
 -12.000  -0.9120   0.05671   0.05157  -0.0417   0.9999   0.0557
 -11.750  -0.9322   0.05293   0.04747  -0.0383   0.9999   0.0558
 -11.500  -0.9484   0.04925   0.04334  -0.0348   0.9999   0.0563
 -11.250  -0.9593   0.04594   0.03948  -0.0312   0.9999   0.0571
 -11.000  -0.9305   0.04467   0.03854  -0.0319   0.9999   0.0587
 -10.750  -0.9169   0.04314   0.03693  -0.0306   0.9999   0.0601
 -10.500  -0.9086   0.04078   0.03429  -0.0286   0.9999   0.0614
 -10.250  -0.8998   0.03838   0.03150  -0.0264   0.9999   0.0628
 -10.000  -0.8911   0.03674   0.02931  -0.0239   0.9999   0.0643
  -9.750  -0.8710   0.03421   0.02683  -0.0234   0.9999   0.0659
  -9.500  -0.8493   0.03304   0.02568  -0.0227   0.9999   0.0676
  -9.250  -0.8299   0.03173   0.02421  -0.0216   0.9999   0.0694
  -9.000  -0.8110   0.03045   0.02267  -0.0202   0.9999   0.0714
  -8.750  -0.7922   0.02932   0.02123  -0.0186   0.9999   0.0729
  -8.500  -0.7699   0.02750   0.01948  -0.0180   0.9999   0.0748
  -8.250  -0.7482   0.02658   0.01857  -0.0171   0.9999   0.0768
  -8.000  -0.7271   0.02567   0.01759  -0.0159   0.9999   0.0787
  -7.750  -0.7066   0.02485   0.01663  -0.0145   0.9999   0.0806
  -7.500  -0.6866   0.02424   0.01586  -0.0130   0.9999   0.0822
  -7.250  -0.6658   0.02284   0.01457  -0.0120   0.9999   0.0842
  -7.000  -0.6461   0.02211   0.01388  -0.0106   0.9999   0.0860
  -6.750  -0.6272   0.02153   0.01329  -0.0090   0.9999   0.0882
  -6.500  -0.6089   0.02102   0.01275  -0.0074   0.9999   0.0904
  -6.250  -0.5911   0.02062   0.01229  -0.0056   0.9999   0.0922
  -6.000  -0.5741   0.01983   0.01157  -0.0039   0.9999   0.0943
  -5.750  -0.5578   0.01935   0.01117  -0.0022   0.9999   0.0968
  -5.500  -0.5414   0.01903   0.01089  -0.0005   0.9999   0.0996
  -5.250  -0.5248   0.01878   0.01064   0.0012   0.9999   0.1024
  -5.000  -0.4929   0.01814   0.01004   0.0002   0.9969   0.1062
  -4.750  -0.4524   0.01749   0.00947  -0.0024   0.9927   0.1126
  -4.500  -0.4131   0.01681   0.00883  -0.0046   0.9866   0.1203
  -4.250  -0.3713   0.01616   0.00826  -0.0073   0.9821   0.1333
  -4.000  -0.3349   0.01507   0.00753  -0.0092   0.9748   0.1821
  -3.750  -0.3034   0.01310   0.00705  -0.0108   0.9702   0.4880
  -3.500  -0.2657   0.01261   0.00686  -0.0124   0.9626   0.5657
  -3.250  -0.2261   0.01225   0.00667  -0.0141   0.9559   0.6180
  -3.000  -0.1924   0.01199   0.00654  -0.0147   0.9447   0.6577
  -2.750  -0.1591   0.01177   0.00641  -0.0150   0.9337   0.6927
  -2.500  -0.1294   0.01160   0.00634  -0.0145   0.9206   0.7272
  -2.250  -0.1047   0.01148   0.00631  -0.0129   0.9028   0.7583
  -2.000  -0.0811   0.01139   0.00622  -0.0110   0.8831   0.7855
  -1.750  -0.0586   0.01133   0.00618  -0.0089   0.8630   0.8091
  -1.500  -0.0362   0.01133   0.00617  -0.0068   0.8434   0.8328
  -1.250  -0.0138   0.01137   0.00618  -0.0048   0.8235   0.8563
  -1.000   0.0087   0.01143   0.00619  -0.0028   0.8031   0.8784
  -0.750   0.0326   0.01151   0.00621  -0.0011   0.7821   0.8970
  -0.500   0.0593   0.01161   0.00622   0.0000   0.7607   0.9122
  -0.250   0.0881   0.01173   0.00623   0.0005   0.7385   0.9262
   0.000   0.1187   0.01187   0.00624   0.0006   0.7157   0.9397
   0.250   0.1547   0.01208   0.00631  -0.0004   0.6923   0.9496
   0.500   0.1929   0.01230   0.00640  -0.0020   0.6664   0.9580
   0.750   0.2336   0.01255   0.00650  -0.0042   0.6393   0.9651
   1.000   0.2749   0.01280   0.00659  -0.0065   0.6119   0.9714
   1.250   0.3166   0.01306   0.00669  -0.0090   0.5837   0.9774
   1.500   0.3571   0.01332   0.00679  -0.0113   0.5555   0.9838
   1.750   0.3985   0.01357   0.00688  -0.0140   0.5258   0.9896
   2.000   0.4395   0.01384   0.00699  -0.0165   0.4966   0.9951
   2.250   0.4802   0.01411   0.00709  -0.0191   0.4683   1.0001
   2.500   0.5005   0.01412   0.00695  -0.0182   0.4462   1.0001
   2.750   0.5209   0.01414   0.00686  -0.0173   0.4244   1.0001
   3.000   0.5410   0.01422   0.00681  -0.0162   0.4042   1.0001
   3.250   0.5608   0.01434   0.00681  -0.0151   0.3863   1.0001
   3.500   0.5807   0.01452   0.00686  -0.0139   0.3709   1.0001
   3.750   0.6006   0.01470   0.00694  -0.0127   0.3570   1.0001
   4.000   0.6209   0.01488   0.00707  -0.0115   0.3443   1.0001
   4.250   0.6411   0.01514   0.00722  -0.0104   0.3336   1.0001
   4.500   0.6619   0.01536   0.00739  -0.0092   0.3236   1.0001
   4.750   0.6831   0.01567   0.00762  -0.0082   0.3153   1.0001
   5.000   0.7047   0.01592   0.00785  -0.0072   0.3072   1.0001
   5.250   0.7266   0.01631   0.00813  -0.0062   0.3001   1.0001
   5.500   0.7490   0.01656   0.00842  -0.0053   0.2928   1.0001
   5.750   0.7716   0.01691   0.00870  -0.0045   0.2866   1.0001
   6.000   0.7948   0.01731   0.00908  -0.0038   0.2805   1.0001
   6.250   0.8182   0.01762   0.00942  -0.0031   0.2741   1.0001
   6.500   0.8420   0.01804   0.00976  -0.0025   0.2685   1.0001
   6.750   0.8658   0.01846   0.01021  -0.0019   0.2628   1.0001
   7.000   0.8898   0.01881   0.01060  -0.0014   0.2570   1.0001
   7.250   0.9140   0.01925   0.01098  -0.0009   0.2518   1.0001
   7.500   0.9379   0.01975   0.01152  -0.0004   0.2465   1.0001
   7.750   0.9616   0.02010   0.01194   0.0001   0.2408   1.0001
   8.000   0.9855   0.02052   0.01231   0.0006   0.2355   1.0001
   8.250   1.0092   0.02109   0.01290   0.0011   0.2302   1.0001
   8.500   1.0320   0.02144   0.01336   0.0017   0.2246   1.0001
   8.750   1.0553   0.02184   0.01374   0.0022   0.2192   1.0001
   9.000   1.0782   0.02245   0.01436   0.0027   0.2140   1.0001
   9.250   1.0997   0.02280   0.01484   0.0036   0.2082   1.0001
   9.500   1.1219   0.02319   0.01521   0.0042   0.2029   1.0001
   9.750   1.1434   0.02379   0.01584   0.0049   0.1975   1.0001
  10.000   1.1632   0.02415   0.01633   0.0059   0.1916   1.0001
  10.250   1.1839   0.02456   0.01671   0.0067   0.1864   1.0001
  10.500   1.2026   0.02514   0.01740   0.0078   0.1807   1.0001
  10.750   1.2205   0.02553   0.01787   0.0090   0.1748   1.0001
  11.000   1.2397   0.02614   0.01837   0.0099   0.1694   1.0001
  11.250   1.2532   0.02661   0.01909   0.0117   0.1634   1.0001
  11.500   1.2678   0.02708   0.01956   0.0133   0.1579   1.0001
  11.750   1.2804   0.02781   0.02036   0.0150   0.1523   1.0001
  12.000   1.2906   0.02843   0.02107   0.0171   0.1466   1.0001
  12.250   1.3004   0.02923   0.02180   0.0192   0.1418   1.0001
  12.500   1.3030   0.03013   0.02290   0.0222   0.1367   1.0001
  12.750   1.3083   0.03105   0.02384   0.0245   0.1322   1.0001
  13.000   1.3137   0.03227   0.02510   0.0264   0.1276   1.0001
  13.250   1.3177   0.03354   0.02650   0.0283   0.1230   1.0001
  13.500   1.3230   0.03487   0.02780   0.0298   0.1192   1.0001
  13.750   1.3268   0.03653   0.02957   0.0312   0.1153   1.0001
  14.000   1.3298   0.03824   0.03139   0.0324   0.1117   1.0001
  14.250   1.3340   0.03994   0.03309   0.0334   0.1086   1.0001
  14.500   1.3381   0.04187   0.03505   0.0343   0.1056   1.0001
  14.750   1.3376   0.04418   0.03754   0.0349   0.1028   1.0001
  15.000   1.3394   0.04635   0.03978   0.0353   0.1002   1.0001
  15.250   1.3438   0.04834   0.04175   0.0357   0.0979   1.0001
  15.500   1.3470   0.05061   0.04407   0.0362   0.0957   1.0001
  15.750   1.3422   0.05370   0.04737   0.0360   0.0939   1.0001
  16.000   1.3394   0.05668   0.05049   0.0358   0.0921   1.0001
  16.250   1.3388   0.05945   0.05334   0.0355   0.0903   1.0001
  16.500   1.3433   0.06162   0.05550   0.0355   0.0885   1.0001
  16.750   1.3513   0.06350   0.05735   0.0360   0.0867   1.0001
  17.000   1.3371   0.06810   0.06220   0.0345   0.0857   1.0001
  17.250   1.3232   0.07293   0.06725   0.0328   0.0846   1.0001
  17.500   1.3097   0.07788   0.07239   0.0309   0.0836   1.0001
  17.750   1.2971   0.08287   0.07755   0.0289   0.0825   1.0001
  18.000   1.2878   0.08750   0.08230   0.0269   0.0814   1.0001
  18.250   1.2877   0.09068   0.08552   0.0258   0.0801   1.0001
  18.500   1.3084   0.09047   0.08519   0.0273   0.0784   1.0001
  18.750   1.2814   0.09805   0.09300   0.0233   0.0778   1.0001
  19.000   1.2403   0.10857   0.10382   0.0170   0.0775   1.0001
<< Back to NACA 23015 (naca23015-il)

Polar data table (+)

Polar graphs


<< Back to NACA 23015 (naca23015-il)