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NACA 23015 (naca23015-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 23015 (naca23015-il)
Reynolds number: 100,000
Max Cl/Cd: 33.68 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23015-il-100000.txt
Download as CSV file: xf-naca23015-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5113   0.11291   0.10765  -0.0076   0.9999   0.2035
 -10.750  -0.5422   0.10760   0.10244  -0.0120   0.9999   0.2145
 -10.500  -0.8014   0.06702   0.06100  -0.0354   0.9999   0.1166
 -10.000  -0.8398   0.05529   0.04808  -0.0298   0.9999   0.1041
  -9.750  -0.8348   0.05183   0.04427  -0.0279   0.9999   0.1042
  -9.500  -0.8268   0.04842   0.04053  -0.0262   0.9999   0.1044
  -9.250  -0.8148   0.04487   0.03671  -0.0247   0.9999   0.1048
  -9.000  -0.7957   0.04199   0.03388  -0.0241   0.9999   0.1069
  -8.750  -0.7781   0.03989   0.03166  -0.0230   0.9999   0.1089
  -8.500  -0.7613   0.03774   0.02925  -0.0215   0.9999   0.1102
  -8.250  -0.7436   0.03585   0.02711  -0.0201   0.9999   0.1122
  -8.000  -0.7252   0.03416   0.02512  -0.0186   0.9999   0.1143
  -7.750  -0.7060   0.03261   0.02327  -0.0170   0.9999   0.1160
  -7.500  -0.6865   0.03113   0.02153  -0.0155   0.9999   0.1179
  -7.250  -0.6653   0.02939   0.01985  -0.0146   0.9999   0.1208
  -7.000  -0.6443   0.02820   0.01862  -0.0133   0.9999   0.1235
  -6.750  -0.6233   0.02715   0.01751  -0.0120   0.9999   0.1265
  -6.500  -0.6028   0.02628   0.01653  -0.0106   0.9999   0.1299
  -6.250  -0.5822   0.02526   0.01546  -0.0092   0.9999   0.1329
  -6.000  -0.5620   0.02424   0.01459  -0.0079   0.9999   0.1366
  -5.750  -0.5428   0.02354   0.01394  -0.0064   0.9999   0.1415
  -5.500  -0.5240   0.02301   0.01336  -0.0048   0.9999   0.1464
  -5.250  -0.5064   0.02217   0.01271  -0.0032   0.9999   0.1517
  -5.000  -0.4896   0.02164   0.01227  -0.0015   0.9999   0.1589
  -4.750  -0.4735   0.02107   0.01181   0.0002   0.9999   0.1677
  -4.500  -0.4573   0.02059   0.01142   0.0019   0.9999   0.1805
  -4.250  -0.4413   0.01989   0.01100   0.0034   0.9999   0.2048
  -4.000  -0.4296   0.01808   0.01076   0.0052   0.9999   0.4407
  -3.750  -0.4166   0.01785   0.01119   0.0081   0.9999   0.5861
  -3.500  -0.4010   0.01807   0.01161   0.0103   0.9999   0.6459
  -3.250  -0.3853   0.01838   0.01205   0.0124   0.9999   0.6912
  -3.000  -0.3534   0.01866   0.01246   0.0122   0.9945   0.7376
  -2.750  -0.3095   0.01886   0.01271   0.0103   0.9840   0.7828
  -2.500  -0.2678   0.01910   0.01298   0.0091   0.9725   0.8236
  -2.250  -0.2265   0.01947   0.01335   0.0085   0.9608   0.8600
  -2.000  -0.1732   0.02002   0.01387   0.0062   0.9518   0.8898
  -1.750  -0.1093   0.02042   0.01419   0.0014   0.9420   0.9115
  -1.500  -0.0411   0.02042   0.01408  -0.0050   0.9315   0.9244
  -1.250   0.0306   0.02012   0.01367  -0.0118   0.9200   0.9350
  -1.000   0.0947   0.01985   0.01332  -0.0172   0.9015   0.9431
  -0.750   0.1439   0.01961   0.01301  -0.0202   0.8801   0.9554
  -0.500   0.1916   0.01944   0.01276  -0.0230   0.8551   0.9665
  -0.250   0.2381   0.01922   0.01244  -0.0256   0.8291   0.9770
   0.000   0.2829   0.01902   0.01212  -0.0281   0.8012   0.9877
   0.250   0.3279   0.01882   0.01179  -0.0307   0.7712   0.9978
   0.500   0.3508   0.01854   0.01136  -0.0302   0.7431   1.0001
   0.750   0.3678   0.01823   0.01091  -0.0285   0.7162   1.0001
   1.000   0.3855   0.01799   0.01049  -0.0270   0.6905   1.0001
   1.250   0.4039   0.01781   0.01018  -0.0256   0.6625   1.0001
   1.500   0.4228   0.01768   0.00986  -0.0241   0.6367   1.0001
   1.750   0.4420   0.01762   0.00965  -0.0228   0.6094   1.0001
   2.000   0.4611   0.01762   0.00948  -0.0214   0.5832   1.0001
   2.250   0.4803   0.01769   0.00933  -0.0199   0.5590   1.0001
   2.500   0.4996   0.01782   0.00934  -0.0186   0.5331   1.0001
   2.750   0.5189   0.01799   0.00935  -0.0172   0.5095   1.0001
   3.000   0.5384   0.01822   0.00940  -0.0158   0.4879   1.0001
   3.250   0.5583   0.01849   0.00952  -0.0145   0.4682   1.0001
   3.500   0.5784   0.01881   0.00971  -0.0133   0.4502   1.0001
   3.750   0.5988   0.01916   0.00996  -0.0121   0.4336   1.0001
   4.000   0.6195   0.01955   0.01026  -0.0109   0.4187   1.0001
   4.250   0.6407   0.01998   0.01057  -0.0099   0.4062   1.0001
   4.500   0.6624   0.02041   0.01091  -0.0088   0.3945   1.0001
   4.750   0.6840   0.02091   0.01142  -0.0079   0.3834   1.0001
   5.000   0.7066   0.02142   0.01175  -0.0070   0.3742   1.0001
   5.250   0.7283   0.02195   0.01238  -0.0061   0.3642   1.0001
   5.500   0.7518   0.02251   0.01281  -0.0054   0.3564   1.0001
   5.750   0.7740   0.02314   0.01355  -0.0046   0.3479   1.0001
   6.000   0.7976   0.02371   0.01406  -0.0040   0.3402   1.0001
   6.250   0.8208   0.02444   0.01482  -0.0033   0.3331   1.0001
   6.500   0.8436   0.02508   0.01554  -0.0027   0.3255   1.0001
   6.750   0.8689   0.02580   0.01609  -0.0023   0.3192   1.0001
   7.000   0.8899   0.02656   0.01711  -0.0015   0.3118   1.0001
   7.250   0.9136   0.02719   0.01772  -0.0010   0.3050   1.0001
   7.500   0.9368   0.02805   0.01861  -0.0004   0.2987   1.0001
   7.750   0.9579   0.02884   0.01957   0.0003   0.2914   1.0001
   8.000   0.9830   0.02949   0.02011   0.0007   0.2852   1.0001
   8.250   1.0022   0.03052   0.02137   0.0016   0.2783   1.0001
   8.500   1.0242   0.03121   0.02213   0.0023   0.2713   1.0001
   8.750   1.0478   0.03208   0.02294   0.0027   0.2651   1.0001
   9.000   1.0647   0.03305   0.02417   0.0039   0.2575   1.0001
   9.250   1.0899   0.03359   0.02459   0.0042   0.2510   1.0001
   9.500   1.1044   0.03486   0.02613   0.0056   0.2438   1.0001
   9.750   1.1253   0.03550   0.02680   0.0064   0.2366   1.0001
  10.000   1.1448   0.03656   0.02790   0.0072   0.2301   1.0001
  10.250   1.1584   0.03761   0.02916   0.0087   0.2225   1.0001
  10.500   1.1872   0.03814   0.02943   0.0085   0.2160   1.0001
  10.750   1.1893   0.03975   0.03151   0.0112   0.2088   1.0001
  11.000   1.2122   0.04015   0.03182   0.0117   0.2021   1.0001
  11.250   1.2190   0.04182   0.03372   0.0137   0.1958   1.0001
  11.500   1.2302   0.04282   0.03484   0.0154   0.1891   1.0001
  11.750   1.2534   0.04353   0.03543   0.0158   0.1832   1.0001
  12.000   1.2434   0.04576   0.03807   0.0193   0.1778   1.0001
  12.250   1.2617   0.04624   0.03850   0.0203   0.1721   1.0001
  12.500   1.2672   0.04789   0.04024   0.0222   0.1675   1.0001
  12.750   1.2440   0.05066   0.04336   0.0265   0.1642   1.0001
  13.000   1.2353   0.05256   0.04539   0.0295   0.1605   1.0001
  13.250   1.2769   0.05224   0.04482   0.0285   0.1549   1.0001
  13.500   1.2350   0.05627   0.04921   0.0329   0.1536   1.0001
  13.750   1.1848   0.06222   0.05553   0.0347   0.1528   1.0001
  14.000   1.1013   0.07375   0.06743   0.0322   0.1534   1.0001
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