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

RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 500,000
Max Cl/Cd: 71.88 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1410-il-500000-n5.txt
Download as CSV file: xf-rg1410-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 10% AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7935   0.08664   0.08404  -0.0305   1.0000   0.0083
 -13.750  -0.8697   0.06704   0.06430  -0.0423   1.0000   0.0080
 -13.500  -0.9215   0.05039   0.04737  -0.0560   1.0000   0.0077
 -13.250  -0.9457   0.04311   0.03987  -0.0618   1.0000   0.0076
 -13.000  -0.9622   0.03892   0.03548  -0.0629   1.0000   0.0078
 -12.750  -0.9762   0.03589   0.03225  -0.0618   1.0000   0.0078
 -12.500  -0.9875   0.03367   0.02986  -0.0591   1.0000   0.0079
 -12.250  -0.9954   0.03201   0.02803  -0.0553   1.0000   0.0080
 -12.000  -0.9948   0.03033   0.02616  -0.0526   1.0000   0.0082
 -11.750  -0.9906   0.02878   0.02440  -0.0501   1.0000   0.0084
 -11.500  -0.9843   0.02738   0.02287  -0.0477   1.0000   0.0087
 -11.250  -0.9717   0.02653   0.02196  -0.0459   1.0000   0.0090
 -11.000  -0.9586   0.02565   0.02098  -0.0441   1.0000   0.0092
 -10.750  -0.9440   0.02487   0.02011  -0.0424   1.0000   0.0095
 -10.500  -0.9291   0.02408   0.01921  -0.0407   1.0000   0.0098
 -10.250  -0.9149   0.02312   0.01812  -0.0388   1.0000   0.0102
 -10.000  -0.9000   0.02220   0.01706  -0.0370   1.0000   0.0106
  -9.750  -0.8843   0.02133   0.01604  -0.0352   1.0000   0.0111
  -9.500  -0.8680   0.02051   0.01507  -0.0335   1.0000   0.0114
  -9.250  -0.8513   0.01973   0.01416  -0.0317   1.0000   0.0117
  -9.000  -0.8356   0.01884   0.01320  -0.0299   1.0000   0.0122
  -8.750  -0.8091   0.01829   0.01258  -0.0302   0.9989   0.0128
  -8.500  -0.7780   0.01780   0.01204  -0.0313   0.9969   0.0136
  -8.250  -0.7470   0.01718   0.01132  -0.0324   0.9950   0.0144
  -8.000  -0.7168   0.01655   0.01057  -0.0333   0.9929   0.0151
  -7.750  -0.6872   0.01597   0.00987  -0.0339   0.9902   0.0155
  -7.500  -0.6579   0.01512   0.00895  -0.0347   0.9874   0.0164
  -7.250  -0.6263   0.01456   0.00836  -0.0359   0.9850   0.0174
  -7.000  -0.5933   0.01411   0.00786  -0.0372   0.9832   0.0183
  -6.750  -0.5661   0.01362   0.00731  -0.0373   0.9785   0.0191
  -6.500  -0.5352   0.01316   0.00678  -0.0381   0.9748   0.0200
  -6.250  -0.5024   0.01274   0.00630  -0.0393   0.9720   0.0208
  -6.000  -0.4729   0.01214   0.00567  -0.0398   0.9679   0.0221
  -5.750  -0.4441   0.01173   0.00523  -0.0401   0.9625   0.0232
  -5.500  -0.4118   0.01135   0.00481  -0.0411   0.9590   0.0246
  -5.250  -0.3802   0.01102   0.00444  -0.0420   0.9547   0.0262
  -5.000  -0.3511   0.01067   0.00407  -0.0423   0.9482   0.0288
  -4.750  -0.3180   0.01033   0.00374  -0.0434   0.9437   0.0326
  -4.500  -0.2878   0.01001   0.00343  -0.0439   0.9366   0.0394
  -4.250  -0.2551   0.00970   0.00315  -0.0450   0.9298   0.0508
  -4.000  -0.2246   0.00942   0.00291  -0.0455   0.9206   0.0636
  -3.750  -0.1934   0.00916   0.00267  -0.0462   0.9111   0.0793
  -3.500  -0.1642   0.00891   0.00247  -0.0465   0.8999   0.0980
  -3.250  -0.1362   0.00869   0.00229  -0.0465   0.8875   0.1198
  -3.000  -0.1088   0.00846   0.00212  -0.0464   0.8745   0.1464
  -2.750  -0.0823   0.00819   0.00197  -0.0462   0.8609   0.1884
  -2.500  -0.0563   0.00793   0.00183  -0.0458   0.8464   0.2370
  -2.250  -0.0304   0.00770   0.00171  -0.0454   0.8310   0.2830
  -2.000  -0.0048   0.00750   0.00160  -0.0449   0.8149   0.3314
  -1.750   0.0205   0.00728   0.00151  -0.0444   0.7983   0.3865
  -1.500   0.0456   0.00707   0.00143  -0.0438   0.7815   0.4441
  -1.250   0.0698   0.00681   0.00136  -0.0431   0.7644   0.5208
  -1.000   0.0935   0.00654   0.00131  -0.0422   0.7468   0.6012
  -0.750   0.1167   0.00630   0.00131  -0.0411   0.7285   0.6824
  -0.500   0.1402   0.00623   0.00136  -0.0399   0.7076   0.7483
  -0.250   0.1650   0.00627   0.00139  -0.0390   0.6844   0.7839
   0.000   0.1902   0.00635   0.00141  -0.0383   0.6619   0.8074
   0.250   0.2156   0.00642   0.00145  -0.0375   0.6419   0.8265
   0.500   0.2408   0.00652   0.00148  -0.0368   0.6186   0.8415
   0.750   0.2662   0.00663   0.00152  -0.0361   0.5950   0.8540
   1.000   0.2914   0.00675   0.00156  -0.0354   0.5733   0.8657
   1.250   0.3167   0.00685   0.00162  -0.0346   0.5536   0.8773
   1.500   0.3420   0.00695   0.00168  -0.0340   0.5346   0.8877
   2.000   0.3922   0.00721   0.00181  -0.0325   0.4910   0.9067
   2.250   0.4166   0.00736   0.00189  -0.0317   0.4671   0.9172
   2.500   0.4414   0.00750   0.00197  -0.0309   0.4447   0.9280
   2.750   0.4668   0.00767   0.00208  -0.0303   0.4234   0.9380
   3.000   0.4930   0.00789   0.00219  -0.0299   0.3922   0.9478
   3.250   0.5199   0.00814   0.00232  -0.0298   0.3596   0.9573
   3.500   0.5499   0.00838   0.00246  -0.0303   0.3308   0.9637
   4.000   0.6098   0.00894   0.00278  -0.0316   0.2724   0.9748
   4.250   0.6400   0.00926   0.00298  -0.0323   0.2410   0.9803
   4.500   0.6706   0.00959   0.00319  -0.0332   0.2116   0.9852
   5.000   0.7322   0.01034   0.00370  -0.0351   0.1572   0.9955
   5.250   0.7616   0.01065   0.00396  -0.0357   0.1433   1.0000
   5.500   0.7819   0.01093   0.00419  -0.0343   0.1326   1.0000
   5.750   0.8036   0.01119   0.00443  -0.0332   0.1212   1.0000
   6.000   0.8259   0.01149   0.00467  -0.0323   0.1081   1.0000
   6.250   0.8483   0.01182   0.00496  -0.0314   0.0949   1.0000
   6.500   0.8713   0.01214   0.00525  -0.0305   0.0852   1.0000
   6.750   0.8944   0.01247   0.00556  -0.0298   0.0776   1.0000
   7.000   0.9173   0.01283   0.00590  -0.0290   0.0705   1.0000
   7.250   0.9405   0.01317   0.00626  -0.0282   0.0645   1.0000
   7.500   0.9633   0.01355   0.00663  -0.0275   0.0585   1.0000
   7.750   0.9863   0.01391   0.00702  -0.0267   0.0538   1.0000
   8.000   1.0088   0.01431   0.00742  -0.0259   0.0486   1.0000
   8.250   1.0311   0.01473   0.00785  -0.0251   0.0440   1.0000
   8.500   1.0532   0.01516   0.00828  -0.0243   0.0388   1.0000
   8.750   1.0748   0.01562   0.00875  -0.0234   0.0347   1.0000
   9.000   1.0966   0.01605   0.00922  -0.0225   0.0319   1.0000
   9.250   1.1172   0.01658   0.00974  -0.0215   0.0283   1.0000
   9.500   1.1382   0.01705   0.01027  -0.0205   0.0263   1.0000
   9.750   1.1586   0.01755   0.01082  -0.0195   0.0241   1.0000
  10.000   1.1776   0.01815   0.01144  -0.0183   0.0215   1.0000
  10.250   1.1973   0.01867   0.01202  -0.0172   0.0199   1.0000
  10.500   1.2156   0.01927   0.01265  -0.0159   0.0175   1.0000
  10.750   1.2329   0.01991   0.01334  -0.0145   0.0157   1.0000
  11.000   1.2497   0.02055   0.01404  -0.0130   0.0140   1.0000
  11.250   1.2630   0.02129   0.01483  -0.0110   0.0123   1.0000
  11.500   1.2761   0.02198   0.01560  -0.0090   0.0114   1.0000
  11.750   1.2877   0.02276   0.01645  -0.0068   0.0103   1.0000
  12.000   1.2981   0.02363   0.01739  -0.0046   0.0095   1.0000
  12.250   1.3067   0.02464   0.01847  -0.0023   0.0089   1.0000
  12.500   1.3160   0.02560   0.01953  -0.0002   0.0084   1.0000
  12.750   1.3245   0.02663   0.02066   0.0017   0.0079   1.0000
  13.000   1.3310   0.02784   0.02197   0.0037   0.0076   1.0000
  13.250   1.3364   0.02918   0.02342   0.0055   0.0071   1.0000
  13.500   1.3401   0.03072   0.02506   0.0072   0.0068   1.0000
  13.750   1.3404   0.03263   0.02708   0.0089   0.0065   1.0000
  14.000   1.3397   0.03475   0.02932   0.0101   0.0063   1.0000
  14.250   1.3400   0.03692   0.03162   0.0110   0.0062   1.0000
  14.500   1.3387   0.03942   0.03425   0.0115   0.0061   1.0000
  14.750   1.3372   0.04211   0.03708   0.0116   0.0059   1.0000
  15.000   1.3327   0.04533   0.04044   0.0113   0.0059   1.0000
  15.250   1.3266   0.04899   0.04424   0.0105   0.0057   1.0000
  15.500   1.3180   0.05323   0.04864   0.0092   0.0057   1.0000
  15.750   1.3081   0.05792   0.05348   0.0073   0.0057   1.0000
  16.000   1.2972   0.06306   0.05877   0.0050   0.0055   1.0000
  16.250   1.2818   0.06920   0.06507   0.0019   0.0056   1.0000
  16.500   1.2662   0.07570   0.07172  -0.0015   0.0055   1.0000
  16.750   1.2469   0.08317   0.07935  -0.0055   0.0055   1.0000
  17.000   1.2258   0.09127   0.08761  -0.0100   0.0055   1.0000
  17.250   1.2024   0.10016   0.09665  -0.0150   0.0056   1.0000
  17.500   1.1777   0.10955   0.10620  -0.0203   0.0056   1.0000
  17.750   1.1532   0.11923   0.11602  -0.0257   0.0057   1.0000
<< Back to RG 14 10% AIRFOIL (rg1410-il)

Polar data table (+)

Polar graphs


<< Back to RG 14 10% AIRFOIL (rg1410-il)