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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 100,000
Max Cl/Cd: 48.77 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg149-il-100000.txt
Download as CSV file: xf-rg149-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9% AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4955   0.09559   0.09056  -0.0190   1.0000   0.1182
  -8.750  -0.5055   0.09218   0.08723  -0.0220   1.0000   0.1234
  -8.500  -0.5440   0.08853   0.08375  -0.0295   1.0000   0.1251
  -8.250  -0.5119   0.08438   0.07958  -0.0239   1.0000   0.1293
  -8.000  -0.5121   0.08128   0.07652  -0.0239   1.0000   0.1336
  -7.750  -0.5527   0.07719   0.07244  -0.0316   1.0000   0.1392
  -7.500  -0.5404   0.07288   0.06822  -0.0292   1.0000   0.1423
  -7.250  -0.5317   0.07003   0.06539  -0.0275   1.0000   0.1476
  -7.000  -0.5467   0.06566   0.06094  -0.0301   1.0000   0.1560
  -6.750  -0.5344   0.06285   0.05818  -0.0278   1.0000   0.1615
  -6.500  -0.5347   0.05946   0.05474  -0.0275   1.0000   0.1730
  -6.250  -0.5434   0.04264   0.03641  -0.0322   1.0000   0.0809
  -6.000  -0.5326   0.03871   0.03214  -0.0306   1.0000   0.0786
  -5.750  -0.5201   0.03445   0.02732  -0.0288   1.0000   0.0752
  -5.500  -0.5033   0.03107   0.02293  -0.0263   1.0000   0.0707
  -5.250  -0.4842   0.02842   0.01989  -0.0247   1.0000   0.0707
  -5.000  -0.4650   0.02592   0.01726  -0.0236   1.0000   0.0736
  -4.750  -0.4441   0.02448   0.01565  -0.0223   1.0000   0.0778
  -4.500  -0.4217   0.02282   0.01369  -0.0209   1.0000   0.0805
  -4.250  -0.3987   0.02152   0.01207  -0.0195   1.0000   0.0836
  -4.000  -0.3772   0.02003   0.01072  -0.0185   1.0000   0.0911
  -3.750  -0.3553   0.01891   0.00956  -0.0172   1.0000   0.1006
  -3.500  -0.3340   0.01779   0.00851  -0.0159   1.0000   0.1146
  -3.250  -0.3136   0.01672   0.00767  -0.0146   1.0000   0.1469
  -3.000  -0.2943   0.01536   0.00690  -0.0133   1.0000   0.2310
  -2.750  -0.2786   0.01378   0.00657  -0.0116   1.0000   0.4461
  -2.500  -0.2721   0.01280   0.00702  -0.0057   1.0000   0.7534
  -2.250  -0.2565   0.01296   0.00732  -0.0011   1.0000   0.8969
  -2.000  -0.0980   0.01352   0.00722  -0.0237   1.0000   1.0000
  -1.750  -0.1012   0.01342   0.00704  -0.0193   1.0000   1.0000
  -1.500  -0.1027   0.01338   0.00691  -0.0151   1.0000   1.0000
  -1.250  -0.1005   0.01340   0.00682  -0.0116   1.0000   1.0000
  -1.000  -0.0936   0.01349   0.00680  -0.0089   1.0000   1.0000
  -0.750  -0.0826   0.01367   0.00686  -0.0070   1.0000   1.0000
  -0.500  -0.0561   0.01400   0.00705  -0.0080   0.9966   1.0000
  -0.250  -0.0029   0.01447   0.00740  -0.0138   0.9856   1.0000
   0.000   0.0489   0.01483   0.00766  -0.0191   0.9737   1.0000
   0.250   0.0992   0.01507   0.00783  -0.0240   0.9612   1.0000
   0.500   0.1488   0.01523   0.00794  -0.0286   0.9484   1.0000
   0.750   0.1987   0.01530   0.00800  -0.0331   0.9356   1.0000
   1.000   0.2503   0.01527   0.00798  -0.0377   0.9232   1.0000
   1.250   0.3128   0.01506   0.00783  -0.0441   0.9140   1.0000
   1.500   0.3626   0.01480   0.00762  -0.0479   0.9001   1.0000
   1.750   0.4097   0.01450   0.00738  -0.0510   0.8853   1.0000
   2.000   0.4456   0.01426   0.00721  -0.0519   0.8651   1.0000
   2.250   0.4835   0.01392   0.00690  -0.0527   0.8442   1.0000
   2.500   0.5127   0.01368   0.00667  -0.0518   0.8185   1.0000
   2.750   0.5392   0.01352   0.00652  -0.0504   0.7916   1.0000
   3.000   0.5638   0.01348   0.00645  -0.0489   0.7651   1.0000
   3.250   0.5878   0.01352   0.00645  -0.0473   0.7388   1.0000
   3.500   0.6103   0.01361   0.00650  -0.0455   0.7106   1.0000
   3.750   0.6316   0.01375   0.00661  -0.0436   0.6799   1.0000
   4.000   0.6523   0.01391   0.00672  -0.0416   0.6464   1.0000
   4.250   0.6731   0.01411   0.00683  -0.0396   0.6115   1.0000
   4.500   0.6932   0.01435   0.00699  -0.0375   0.5735   1.0000
   4.750   0.7130   0.01465   0.00719  -0.0355   0.5334   1.0000
   5.000   0.7321   0.01501   0.00743  -0.0334   0.4884   1.0000
   5.250   0.7500   0.01547   0.00771  -0.0313   0.4370   1.0000
   5.500   0.7666   0.01610   0.00809  -0.0290   0.3776   1.0000
   5.750   0.7825   0.01697   0.00862  -0.0268   0.3159   1.0000
   6.000   0.7988   0.01798   0.00933  -0.0249   0.2640   1.0000
   6.250   0.8165   0.01906   0.01017  -0.0232   0.2237   1.0000
   6.500   0.8348   0.02021   0.01110  -0.0217   0.1929   1.0000
   6.750   0.8545   0.02143   0.01220  -0.0204   0.1682   1.0000
   7.000   0.8751   0.02290   0.01344  -0.0195   0.1487   1.0000
   7.250   0.8967   0.02431   0.01491  -0.0184   0.1322   1.0000
   7.500   0.9183   0.02572   0.01636  -0.0175   0.1180   1.0000
   7.750   0.9408   0.02735   0.01795  -0.0167   0.1064   1.0000
   8.000   0.9616   0.02868   0.01947  -0.0155   0.0962   1.0000
   8.250   0.9823   0.03059   0.02162  -0.0144   0.0873   1.0000
   8.500   1.0025   0.03269   0.02377  -0.0136   0.0795   1.0000
   8.750   1.0198   0.03455   0.02602  -0.0119   0.0727   1.0000
   9.000   1.0360   0.03723   0.02883  -0.0108   0.0669   1.0000
   9.250   1.0472   0.03980   0.03195  -0.0084   0.0626   1.0000
   9.500   1.0606   0.04246   0.03484  -0.0069   0.0592   1.0000
  10.000   1.0674   0.04950   0.04260  -0.0026   0.0546   1.0000
  10.250   1.0604   0.05318   0.04679   0.0004   0.0534   1.0000
  10.500   1.0489   0.05727   0.05127   0.0031   0.0532   1.0000
  10.750   1.0322   0.06117   0.05547   0.0058   0.0533   1.0000
  11.000   1.0118   0.06504   0.05956   0.0081   0.0536   1.0000
  11.250   0.9903   0.06933   0.06404   0.0090   0.0540   1.0000
  11.500   0.9672   0.07428   0.06915   0.0082   0.0544   1.0000
  11.750   0.9459   0.07999   0.07497   0.0059   0.0550   1.0000
  12.000   0.9244   0.08668   0.08175   0.0024   0.0555   1.0000
  12.250   0.6557   0.13446   0.12983  -0.0275   0.1477   1.0000
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