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NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA M13 AIRFOIL (m13-il)
Reynolds number: 50,000
Max Cl/Cd: 38.81 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m13-il-50000.txt
Download as CSV file: xf-m13-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M13 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4758   0.12173   0.11501   0.0052   1.0000   0.1101
  -8.750  -0.4798   0.12089   0.11427   0.0015   1.0000   0.1121
  -8.500  -0.4735   0.11646   0.10990   0.0004   1.0000   0.1140
  -8.250  -0.4592   0.11113   0.10455   0.0015   1.0000   0.1196
  -8.000  -0.4573   0.10865   0.10213  -0.0007   1.0000   0.1242
  -7.750  -0.4621   0.10787   0.10147  -0.0064   1.0000   0.1264
  -7.500  -0.4489   0.10182   0.09541  -0.0042   1.0000   0.1302
  -7.250  -0.4406   0.09826   0.09188  -0.0054   1.0000   0.1362
  -7.000  -0.4377   0.09720   0.09085  -0.0139   1.0000   0.1407
  -6.750  -0.4253   0.09123   0.08493  -0.0103   1.0000   0.1459
  -6.500  -0.4166   0.08930   0.08300  -0.0169   1.0000   0.1544
  -6.250  -0.4057   0.08422   0.07798  -0.0144   1.0000   0.1623
  -5.750  -0.3810   0.07852   0.07225  -0.0234   1.0000   0.1834
  -5.500  -0.3693   0.07414   0.06792  -0.0219   1.0000   0.1950
  -5.250  -0.3567   0.07035   0.06416  -0.0224   1.0000   0.2069
  -5.000  -0.3407   0.06780   0.06153  -0.0267   1.0000   0.2258
  -4.750  -0.3300   0.06367   0.05745  -0.0251   1.0000   0.2422
  -4.500  -0.3179   0.06072   0.05451  -0.0255   1.0000   0.2692
  -4.250  -0.3114   0.05729   0.05121  -0.0225   1.0000   0.3008
  -4.000  -0.3083   0.05438   0.04843  -0.0187   1.0000   0.3452
  -3.750  -0.3108   0.05165   0.04587  -0.0131   1.0000   0.4006
  -3.500  -0.3151   0.04914   0.04351  -0.0070   1.0000   0.4556
  -3.250  -0.3196   0.04658   0.04112   0.0000   1.0000   0.5018
  -3.000  -0.3231   0.04422   0.03889   0.0061   1.0000   0.5450
  -2.750  -0.3220   0.04203   0.03676   0.0096   1.0000   0.5831
  -2.500  -0.3185   0.03959   0.03436   0.0136   1.0000   0.6136
  -2.250  -0.3064   0.03718   0.03197   0.0145   1.0000   0.6352
  -2.000  -0.2834   0.03470   0.02943   0.0119   1.0000   0.6486
  -1.750  -0.1284   0.03373   0.02656  -0.0307   1.0000   0.3918
  -1.500  -0.0673   0.03335   0.02486  -0.0379   1.0000   0.2336
  -1.250  -0.0349   0.03215   0.02302  -0.0389   1.0000   0.1926
  -1.000  -0.0066   0.03096   0.02135  -0.0394   1.0000   0.1745
  -0.750   0.0201   0.03036   0.02025  -0.0397   1.0000   0.1685
  -0.500   0.0445   0.02965   0.01927  -0.0401   1.0000   0.1687
  -0.250   0.0819   0.02867   0.01805  -0.0427   0.9954   0.1664
   0.000   0.1366   0.02772   0.01673  -0.0479   0.9840   0.1660
   0.250   0.1901   0.02702   0.01567  -0.0526   0.9721   0.1713
   0.500   0.2400   0.02635   0.01491  -0.0569   0.9599   0.1862
   0.750   0.2876   0.02549   0.01429  -0.0610   0.9477   0.2423
   1.000   0.3366   0.02326   0.01347  -0.0644   0.9360   1.0000
   1.250   0.3815   0.02384   0.01367  -0.0682   0.9211   1.0000
   1.500   0.4252   0.02441   0.01403  -0.0718   0.9065   1.0000
   1.750   0.4663   0.02498   0.01449  -0.0748   0.8919   1.0000
   2.000   0.5030   0.02558   0.01502  -0.0769   0.8773   1.0000
   2.250   0.5370   0.02622   0.01561  -0.0784   0.8629   1.0000
   2.500   0.5687   0.02688   0.01627  -0.0795   0.8486   1.0000
   2.750   0.5985   0.02759   0.01703  -0.0801   0.8345   1.0000
   3.000   0.6267   0.02832   0.01780  -0.0804   0.8205   1.0000
   3.250   0.6537   0.02909   0.01862  -0.0805   0.8068   1.0000
   3.500   0.6799   0.02988   0.01949  -0.0803   0.7931   1.0000
   3.750   0.7054   0.03070   0.02045  -0.0801   0.7795   1.0000
   4.000   0.7304   0.03152   0.02139  -0.0796   0.7660   1.0000
   4.250   0.7550   0.03236   0.02236  -0.0791   0.7525   1.0000
   4.500   0.7794   0.03321   0.02335  -0.0784   0.7390   1.0000
   4.750   0.8033   0.03406   0.02439  -0.0776   0.7254   1.0000
   5.000   0.8268   0.03495   0.02552  -0.0767   0.7116   1.0000
   5.250   0.8495   0.03589   0.02668  -0.0758   0.6976   1.0000
   5.500   0.8707   0.03697   0.02799  -0.0747   0.6830   1.0000
   5.750   0.8903   0.03819   0.02948  -0.0736   0.6678   1.0000
   6.000   0.9091   0.03949   0.03107  -0.0725   0.6519   1.0000
   6.250   0.9540   0.03146   0.02328  -0.0593   0.5943   1.0000
   6.500   0.9733   0.02508   0.01667  -0.0469   0.5016   1.0000
   6.750   0.9679   0.02521   0.01530  -0.0385   0.2284   1.0000
   7.000   0.9689   0.02909   0.01800  -0.0359   0.1429   1.0000
   7.250   0.9787   0.03166   0.02032  -0.0337   0.1200   1.0000
   7.500   0.9944   0.03388   0.02247  -0.0314   0.1089   1.0000
   7.750   1.0197   0.03600   0.02463  -0.0297   0.1006   1.0000
   8.000   1.0497   0.03847   0.02718  -0.0286   0.0931   1.0000
   8.250   1.0793   0.04134   0.03007  -0.0280   0.0872   1.0000
   8.500   1.1092   0.04519   0.03409  -0.0275   0.0858   1.0000
   8.750   1.1327   0.04887   0.03820  -0.0264   0.0860   1.0000
   9.000   1.1491   0.05231   0.04235  -0.0246   0.0874   1.0000
   9.250   1.1580   0.05640   0.04716  -0.0227   0.0890   1.0000
   9.500   1.1621   0.06084   0.05225  -0.0210   0.0904   1.0000
   9.750   1.1614   0.06549   0.05741  -0.0195   0.0918   1.0000
  10.000   1.1549   0.07029   0.06263  -0.0181   0.0935   1.0000
  10.250   1.1462   0.07520   0.06784  -0.0170   0.0951   1.0000
  10.500   1.1387   0.08030   0.07315  -0.0164   0.0967   1.0000
  10.750   1.1357   0.08555   0.07857  -0.0160   0.0991   1.0000
  11.000   1.0623   0.09137   0.08470  -0.0190   0.1033   1.0000
  11.250   1.0264   0.10015   0.09354  -0.0250   0.1071   1.0000
  11.500   1.0207   0.10682   0.10022  -0.0270   0.1104   1.0000
  11.750   0.9637   0.12361   0.11692  -0.0425   0.1186   1.0000
  12.000   0.8292   0.11504   0.10864  -0.0227   0.1104   1.0000
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