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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 200,000
Max Cl/Cd: 57.7 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg149-il-200000-n5.txt
Download as CSV file: xf-rg149-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5585   0.08282   0.07920  -0.0275   1.0000   0.0151
  -9.750  -0.5679   0.07691   0.07334  -0.0308   1.0000   0.0149
  -9.500  -0.5850   0.06879   0.06529  -0.0364   1.0000   0.0148
  -9.250  -0.6122   0.05894   0.05540  -0.0439   1.0000   0.0145
  -9.000  -0.6400   0.05247   0.04877  -0.0442   1.0000   0.0144
  -8.750  -0.6595   0.04669   0.04271  -0.0433   1.0000   0.0143
  -8.500  -0.6749   0.04081   0.03638  -0.0413   1.0000   0.0144
  -8.250  -0.6802   0.03603   0.03109  -0.0389   1.0000   0.0147
  -8.000  -0.6780   0.03211   0.02657  -0.0365   1.0000   0.0151
  -7.750  -0.6696   0.02914   0.02313  -0.0343   1.0000   0.0155
  -7.500  -0.6562   0.02739   0.02124  -0.0327   1.0000   0.0164
  -7.250  -0.6393   0.02639   0.02013  -0.0313   1.0000   0.0173
  -7.000  -0.6222   0.02522   0.01875  -0.0299   1.0000   0.0186
  -6.750  -0.6051   0.02355   0.01676  -0.0282   1.0000   0.0197
  -6.500  -0.5868   0.02206   0.01497  -0.0266   1.0000   0.0206
  -6.250  -0.5673   0.02095   0.01360  -0.0252   1.0000   0.0214
  -6.000  -0.5490   0.01951   0.01207  -0.0238   1.0000   0.0230
  -5.750  -0.5291   0.01885   0.01135  -0.0226   1.0000   0.0247
  -5.500  -0.5062   0.01798   0.01036  -0.0219   0.9994   0.0261
  -5.250  -0.4729   0.01704   0.00928  -0.0232   0.9960   0.0275
  -5.000  -0.4395   0.01632   0.00844  -0.0245   0.9924   0.0296
  -4.750  -0.4075   0.01541   0.00749  -0.0258   0.9881   0.0321
  -4.500  -0.3730   0.01480   0.00681  -0.0273   0.9842   0.0345
  -4.250  -0.3410   0.01426   0.00619  -0.0284   0.9790   0.0372
  -4.000  -0.3079   0.01370   0.00560  -0.0296   0.9738   0.0422
  -3.750  -0.2727   0.01323   0.00514  -0.0313   0.9697   0.0529
  -3.500  -0.2428   0.01273   0.00469  -0.0318   0.9625   0.0727
  -3.250  -0.2079   0.01228   0.00435  -0.0335   0.9578   0.1040
  -3.000  -0.1772   0.01185   0.00407  -0.0342   0.9505   0.1419
  -2.750  -0.1441   0.01124   0.00380  -0.0357   0.9448   0.2223
  -2.500  -0.1144   0.01055   0.00359  -0.0365   0.9371   0.3354
  -2.250  -0.0824   0.00999   0.00338  -0.0375   0.9301   0.4333
  -2.000  -0.0547   0.00942   0.00323  -0.0375   0.9206   0.5433
  -1.750  -0.0268   0.00886   0.00321  -0.0371   0.9126   0.6812
  -1.500   0.0001   0.00867   0.00329  -0.0360   0.9021   0.7810
  -1.250   0.0289   0.00861   0.00326  -0.0356   0.8908   0.8270
  -1.000   0.0587   0.00857   0.00320  -0.0354   0.8789   0.8564
  -0.750   0.0889   0.00854   0.00314  -0.0352   0.8660   0.8793
  -0.500   0.1188   0.00854   0.00308  -0.0351   0.8517   0.8999
  -0.250   0.1505   0.00854   0.00302  -0.0353   0.8365   0.9160
   0.000   0.1831   0.00856   0.00297  -0.0359   0.8202   0.9300
   0.250   0.2172   0.00859   0.00293  -0.0367   0.8029   0.9431
   0.500   0.2535   0.00864   0.00289  -0.0381   0.7844   0.9538
   0.750   0.2906   0.00869   0.00286  -0.0398   0.7636   0.9623
   1.000   0.3259   0.00877   0.00283  -0.0412   0.7397   0.9712
   1.250   0.3644   0.00886   0.00279  -0.0432   0.7110   0.9775
   1.500   0.3991   0.00896   0.00276  -0.0446   0.6819   0.9843
   1.750   0.4344   0.00907   0.00276  -0.0462   0.6533   0.9898
   2.000   0.4674   0.00920   0.00277  -0.0473   0.6245   0.9954
   2.250   0.4983   0.00935   0.00279  -0.0480   0.5914   1.0000
   2.500   0.5180   0.00951   0.00287  -0.0464   0.5655   1.0000
   2.750   0.5380   0.00968   0.00296  -0.0449   0.5415   1.0000
   3.000   0.5575   0.00988   0.00306  -0.0433   0.5138   1.0000
   3.500   0.5961   0.01040   0.00333  -0.0400   0.4475   1.0000
   3.750   0.6157   0.01069   0.00350  -0.0384   0.4141   1.0000
   4.000   0.6356   0.01102   0.00369  -0.0369   0.3793   1.0000
   4.250   0.6561   0.01137   0.00391  -0.0356   0.3435   1.0000
   4.500   0.6768   0.01176   0.00419  -0.0343   0.3084   1.0000
   4.750   0.6980   0.01217   0.00447  -0.0332   0.2715   1.0000
   5.000   0.7189   0.01266   0.00480  -0.0321   0.2319   1.0000
   5.250   0.7400   0.01318   0.00516  -0.0310   0.1960   1.0000
   5.500   0.7615   0.01371   0.00556  -0.0301   0.1677   1.0000
   5.750   0.7834   0.01422   0.00602  -0.0292   0.1472   1.0000
   6.000   0.8056   0.01471   0.00647  -0.0283   0.1301   1.0000
   6.250   0.8279   0.01520   0.00694  -0.0275   0.1135   1.0000
   6.500   0.8504   0.01569   0.00741  -0.0267   0.0989   1.0000
   6.750   0.8723   0.01623   0.00792  -0.0258   0.0862   1.0000
   7.000   0.8942   0.01679   0.00851  -0.0250   0.0760   1.0000
   7.250   0.9161   0.01735   0.00913  -0.0241   0.0686   1.0000
   7.500   0.9364   0.01807   0.00984  -0.0230   0.0618   1.0000
   7.750   0.9582   0.01864   0.01052  -0.0221   0.0560   1.0000
   8.000   0.9774   0.01945   0.01133  -0.0210   0.0501   1.0000
   8.250   0.9990   0.02002   0.01203  -0.0201   0.0452   1.0000
   8.500   1.0185   0.02077   0.01281  -0.0190   0.0396   1.0000
   8.750   1.0391   0.02142   0.01357  -0.0181   0.0354   1.0000
   9.000   1.0584   0.02216   0.01438  -0.0170   0.0314   1.0000
   9.250   1.0759   0.02307   0.01537  -0.0157   0.0277   1.0000
   9.500   1.0944   0.02386   0.01627  -0.0145   0.0243   1.0000
   9.750   1.1083   0.02504   0.01750  -0.0129   0.0216   1.0000
  10.000   1.1236   0.02611   0.01875  -0.0113   0.0195   1.0000
  10.250   1.1379   0.02716   0.01994  -0.0097   0.0176   1.0000
  10.500   1.1475   0.02849   0.02132  -0.0077   0.0159   1.0000
  10.750   1.1579   0.02966   0.02269  -0.0055   0.0147   1.0000
  11.000   1.1653   0.03100   0.02419  -0.0032   0.0137   1.0000
  11.250   1.1712   0.03244   0.02578  -0.0009   0.0129   1.0000
  11.500   1.1755   0.03400   0.02748   0.0013   0.0123   1.0000
  11.750   1.1776   0.03576   0.02937   0.0033   0.0119   1.0000
  12.000   1.1758   0.03795   0.03170   0.0052   0.0115   1.0000
  12.250   1.1723   0.04050   0.03442   0.0067   0.0112   1.0000
  12.500   1.1693   0.04321   0.03736   0.0078   0.0109   1.0000
  12.750   1.1648   0.04622   0.04058   0.0083   0.0107   1.0000
  13.000   1.1585   0.04966   0.04424   0.0082   0.0105   1.0000
  13.250   1.1503   0.05357   0.04838   0.0075   0.0104   1.0000
  13.500   1.1398   0.05813   0.05319   0.0060   0.0101   1.0000
  13.750   1.1279   0.06326   0.05853   0.0037   0.0100   1.0000
  14.000   1.1137   0.06918   0.06465   0.0007   0.0100   1.0000
  14.250   1.0972   0.07595   0.07162  -0.0032   0.0100   1.0000
  14.500   1.0789   0.08354   0.07937  -0.0079   0.0100   1.0000
  14.750   1.0564   0.09249   0.08851  -0.0134   0.0101   1.0000
  15.000   1.0340   0.10209   0.09827  -0.0193   0.0103   1.0000
  15.250   1.0091   0.11275   0.10908  -0.0258   0.0105   1.0000
  15.500   0.9808   0.12500   0.12145  -0.0329   0.0108   1.0000
  15.750   0.9503   0.13851   0.13504  -0.0405   0.0111   1.0000
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