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

NACA 23024 (naca23024-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 23024 (naca23024-il)
Reynolds number: 500,000
Max Cl/Cd: 44.53 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23024-il-500000.txt
Download as CSV file: xf-naca23024-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23024                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0645   0.07953   0.07408  -0.0660   1.0000   0.0831
 -19.500  -1.0667   0.07672   0.07124  -0.0662   1.0000   0.0846
 -19.250  -1.0701   0.07379   0.06831  -0.0664   1.0000   0.0861
 -19.000  -1.0729   0.07091   0.06540  -0.0666   1.0000   0.0878
 -18.750  -1.0728   0.06837   0.06281  -0.0666   1.0000   0.0896
 -18.500  -1.0731   0.06586   0.06023  -0.0666   1.0000   0.0913
 -18.250  -1.0798   0.06276   0.05713  -0.0665   1.0000   0.0932
 -18.000  -1.0826   0.06009   0.05444  -0.0663   1.0000   0.0951
 -17.750  -1.0838   0.05760   0.05191  -0.0659   1.0000   0.0973
 -17.500  -1.0833   0.05537   0.04962  -0.0655   1.0000   0.0994
 -17.250  -1.0902   0.05250   0.04675  -0.0649   1.0000   0.1017
 -17.000  -1.0930   0.05006   0.04428  -0.0642   1.0000   0.1042
 -16.750  -1.0910   0.04813   0.04229  -0.0634   1.0000   0.1068
 -16.500  -1.0957   0.04567   0.03982  -0.0624   1.0000   0.1095
 -16.250  -1.0992   0.04340   0.03754  -0.0613   1.0000   0.1125
 -16.000  -1.0979   0.04163   0.03573  -0.0601   1.0000   0.1157
 -15.750  -1.1014   0.03956   0.03364  -0.0586   1.0000   0.1185
 -15.500  -1.1042   0.03763   0.03171  -0.0569   1.0000   0.1221
 -15.250  -1.1027   0.03613   0.03018  -0.0551   1.0000   0.1259
 -15.000  -1.1075   0.03430   0.02836  -0.0529   1.0000   0.1297
 -14.750  -1.1092   0.03282   0.02687  -0.0506   1.0000   0.1337
 -14.500  -1.1111   0.03146   0.02549  -0.0480   1.0000   0.1381
 -14.250  -1.1162   0.03007   0.02411  -0.0450   1.0000   0.1422
 -14.000  -1.1180   0.02902   0.02305  -0.0420   1.0000   0.1468
 -13.750  -1.1252   0.02781   0.02184  -0.0383   1.0000   0.1513
 -13.500  -1.0994   0.02674   0.02077  -0.0400   0.9977   0.1589
 -13.250  -1.0776   0.02547   0.01954  -0.0413   0.9947   0.1666
 -13.000  -1.0521   0.02452   0.01861  -0.0428   0.9921   0.1748
 -12.750  -1.0289   0.02354   0.01764  -0.0436   0.9887   0.1831
 -12.500  -1.0063   0.02254   0.01668  -0.0443   0.9849   0.1907
 -12.250  -0.9776   0.02183   0.01596  -0.0456   0.9820   0.1988
 -12.000  -0.9503   0.02097   0.01515  -0.0470   0.9796   0.2078
 -11.750  -0.9223   0.02028   0.01447  -0.0481   0.9768   0.2156
 -11.500  -0.9026   0.01950   0.01372  -0.0476   0.9706   0.2235
 -11.250  -0.8729   0.01889   0.01310  -0.0488   0.9673   0.2308
 -11.000  -0.8428   0.01822   0.01248  -0.0501   0.9649   0.2396
 -10.750  -0.8214   0.01767   0.01191  -0.0494   0.9581   0.2461
 -10.500  -0.7955   0.01702   0.01131  -0.0497   0.9533   0.2542
 -10.250  -0.7623   0.01653   0.01080  -0.0511   0.9505   0.2616
 -10.000  -0.7395   0.01590   0.01022  -0.0507   0.9445   0.2688
  -9.750  -0.7140   0.01544   0.00975  -0.0505   0.9382   0.2761
  -9.500  -0.6830   0.01486   0.00920  -0.0515   0.9341   0.2836
  -9.250  -0.6474   0.01437   0.00871  -0.0534   0.9305   0.2916
  -9.000  -0.6204   0.01400   0.00832  -0.0534   0.9210   0.2983
  -8.750  -0.5809   0.01350   0.00787  -0.0560   0.9157   0.3070
  -8.500  -0.5403   0.01320   0.00752  -0.0587   0.9083   0.3146
  -8.250  -0.5026   0.01278   0.00714  -0.0611   0.8980   0.3232
  -8.000  -0.4486   0.01249   0.00681  -0.0666   0.8905   0.3323
  -7.750  -0.4175   0.01222   0.00655  -0.0675   0.8763   0.3403
  -7.500  -0.3765   0.01198   0.00629  -0.0703   0.8646   0.3490
  -7.250  -0.3479   0.01182   0.00607  -0.0706   0.8487   0.3564
  -7.000  -0.3253   0.01162   0.00587  -0.0696   0.8321   0.3640
  -6.750  -0.2988   0.01151   0.00567  -0.0694   0.8162   0.3715
  -6.500  -0.2796   0.01138   0.00549  -0.0676   0.7994   0.3783
  -6.250  -0.2637   0.01124   0.00534  -0.0652   0.7831   0.3856
  -6.000  -0.2444   0.01119   0.00519  -0.0633   0.7672   0.3928
  -5.750  -0.2279   0.01109   0.00505  -0.0610   0.7515   0.3996
  -5.500  -0.2140   0.01099   0.00494  -0.0580   0.7371   0.4070
  -5.250  -0.1969   0.01096   0.00482  -0.0557   0.7227   0.4141
  -5.000  -0.1831   0.01088   0.00472  -0.0527   0.7086   0.4214
  -4.750  -0.1691   0.01081   0.00464  -0.0498   0.6954   0.4292
  -4.500  -0.1542   0.01079   0.00455  -0.0470   0.6821   0.4365
  -4.250  -0.1405   0.01072   0.00447  -0.0440   0.6700   0.4439
  -4.000  -0.1279   0.01067   0.00441  -0.0407   0.6569   0.4520
  -3.750  -0.1131   0.01067   0.00435  -0.0378   0.6451   0.4596
  -3.500  -0.1006   0.01060   0.00429  -0.0345   0.6331   0.4674
  -3.250  -0.0885   0.01058   0.00424  -0.0311   0.6215   0.4758
  -3.000  -0.0759   0.01059   0.00420  -0.0277   0.6095   0.4836
  -2.750  -0.0649   0.01054   0.00416  -0.0241   0.5984   0.4921
  -2.500  -0.0535   0.01053   0.00414  -0.0205   0.5869   0.5008
  -2.250  -0.0421   0.01056   0.00411  -0.0169   0.5763   0.5090
  -2.000  -0.0324   0.01051   0.00411  -0.0129   0.5657   0.5179
  -1.750  -0.0234   0.01056   0.00409  -0.0088   0.5554   0.5265
  -1.500  -0.0142   0.01053   0.00409  -0.0047   0.5467   0.5350
  -1.250  -0.0115   0.01052   0.00409   0.0007   0.5367   0.5443
  -1.000  -0.0032   0.01057   0.00408   0.0050   0.5281   0.5530
  -0.750   0.0061   0.01051   0.00408   0.0090   0.5193   0.5628
  -0.500   0.0158   0.01054   0.00408   0.0130   0.5102   0.5727
  -0.250   0.0279   0.01053   0.00410   0.0164   0.5020   0.5826
   0.000   0.0389   0.01053   0.00411   0.0201   0.4925   0.5934
   0.250   0.0506   0.01059   0.00413   0.0236   0.4839   0.6035
   0.500   0.0637   0.01056   0.00417   0.0268   0.4759   0.6146
   1.000   0.0879   0.01064   0.00426   0.0336   0.4589   0.6374
   1.250   0.1022   0.01067   0.00430   0.0365   0.4509   0.6486
   1.500   0.1149   0.01071   0.00436   0.0397   0.4426   0.6609
   1.750   0.1287   0.01077   0.00443   0.0427   0.4352   0.6733
   2.000   0.1427   0.01079   0.00451   0.0456   0.4266   0.6864
   2.500   0.1716   0.01091   0.00468   0.0513   0.4114   0.7135
   2.750   0.1853   0.01098   0.00477   0.0542   0.4030   0.7271
   3.000   0.1990   0.01109   0.00490   0.0571   0.3953   0.7422
   3.250   0.2170   0.01113   0.00501   0.0591   0.3879   0.7568
   3.500   0.2310   0.01124   0.00514   0.0619   0.3801   0.7729
   3.750   0.2491   0.01135   0.00531   0.0638   0.3727   0.7893
   4.000   0.2693   0.01146   0.00547   0.0653   0.3642   0.8058
   4.250   0.2859   0.01165   0.00565   0.0674   0.3561   0.8223
   4.500   0.3112   0.01176   0.00584   0.0678   0.3488   0.8388
   4.750   0.3412   0.01197   0.00607   0.0670   0.3399   0.8535
   5.000   0.3666   0.01218   0.00630   0.0672   0.3317   0.8694
   5.250   0.4132   0.01246   0.00659   0.0629   0.3219   0.8807
   5.500   0.4490   0.01276   0.00688   0.0608   0.3132   0.8932
   5.750   0.4976   0.01311   0.00724   0.0561   0.3035   0.9012
   6.000   0.5292   0.01350   0.00760   0.0549   0.2957   0.9127
   6.250   0.5752   0.01392   0.00802   0.0507   0.2872   0.9175
   6.500   0.6103   0.01450   0.00854   0.0486   0.2790   0.9240
   6.750   0.6384   0.01486   0.00893   0.0482   0.2730   0.9323
   7.000   0.6730   0.01544   0.00947   0.0462   0.2659   0.9356
   7.250   0.7020   0.01602   0.01003   0.0454   0.2601   0.9404
   7.500   0.7218   0.01648   0.01050   0.0465   0.2549   0.9489
   7.750   0.7533   0.01712   0.01109   0.0450   0.2491   0.9515
   8.000   0.7832   0.01773   0.01168   0.0437   0.2436   0.9550
   8.250   0.8015   0.01824   0.01221   0.0449   0.2396   0.9637
   8.500   0.8342   0.01886   0.01281   0.0430   0.2344   0.9657
   8.750   0.8629   0.01960   0.01349   0.0416   0.2293   0.9684
   9.000   0.8937   0.02007   0.01401   0.0402   0.2249   0.9721
   9.250   0.9149   0.02076   0.01470   0.0404   0.2210   0.9784
   9.500   0.9450   0.02147   0.01537   0.0385   0.2166   0.9802
   9.750   0.9758   0.02211   0.01601   0.0366   0.2127   0.9824
  10.000   1.0064   0.02267   0.01661   0.0349   0.2090   0.9853
  10.250   1.0326   0.02342   0.01736   0.0337   0.2050   0.9890
  10.500   1.0558   0.02436   0.01825   0.0327   0.2008   0.9922
  10.750   1.0864   0.02496   0.01889   0.0306   0.1975   0.9946
  11.000   1.1161   0.02562   0.01959   0.0287   0.1941   0.9973
  11.250   1.1440   0.02644   0.02041   0.0268   0.1904   0.9996
  11.500   1.1475   0.02735   0.02130   0.0290   0.1878   1.0000
  11.750   1.1482   0.02815   0.02210   0.0320   0.1853   1.0000
  12.000   1.1518   0.02890   0.02291   0.0345   0.1831   1.0000
  12.250   1.1564   0.02971   0.02376   0.0368   0.1808   1.0000
  12.500   1.1591   0.03073   0.02478   0.0390   0.1781   1.0000
  12.750   1.1617   0.03184   0.02589   0.0412   0.1757   1.0000
  13.000   1.1638   0.03307   0.02710   0.0432   0.1730   1.0000
  13.250   1.1709   0.03407   0.02817   0.0447   0.1710   1.0000
  13.500   1.1769   0.03521   0.02936   0.0461   0.1687   1.0000
  13.750   1.1819   0.03647   0.03063   0.0475   0.1662   1.0000
  14.000   1.1846   0.03794   0.03210   0.0489   0.1637   1.0000
  14.250   1.1875   0.03942   0.03356   0.0503   0.1611   1.0000
  14.500   1.1936   0.04081   0.03503   0.0512   0.1591   1.0000
  14.750   1.1990   0.04226   0.03654   0.0521   0.1567   1.0000
  15.000   1.2025   0.04392   0.03822   0.0529   0.1542   1.0000
  15.250   1.2048   0.04568   0.03997   0.0538   0.1520   1.0000
  15.500   1.2070   0.04746   0.04175   0.0546   0.1496   1.0000
  15.750   1.2118   0.04918   0.04356   0.0551   0.1476   1.0000
  16.000   1.2148   0.05108   0.04551   0.0555   0.1452   1.0000
  16.250   1.2170   0.05307   0.04753   0.0559   0.1430   1.0000
  16.500   1.2176   0.05521   0.04966   0.0563   0.1408   1.0000
  16.750   1.2193   0.05728   0.05175   0.0566   0.1385   1.0000
  17.000   1.2212   0.05949   0.05405   0.0567   0.1364   1.0000
  17.250   1.2225   0.06175   0.05637   0.0567   0.1342   1.0000
  17.500   1.2220   0.06420   0.05884   0.0567   0.1320   1.0000
  17.750   1.2228   0.06644   0.06105   0.0567   0.1299   1.0000
  18.000   1.2222   0.06902   0.06370   0.0565   0.1279   1.0000
  18.250   1.2226   0.07153   0.06629   0.0563   0.1260   1.0000
  18.500   1.2204   0.07436   0.06918   0.0558   0.1238   1.0000
  18.750   1.2201   0.07691   0.07173   0.0555   0.1219   1.0000
  19.000   1.2203   0.07935   0.07414   0.0553   0.1198   1.0000
  19.250   1.2174   0.08239   0.07729   0.0546   0.1180   1.0000
<< Back to NACA 23024 (naca23024-il)

Polar data table (+)

Polar graphs


<< Back to NACA 23024 (naca23024-il)