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

SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 200,000
Max Cl/Cd: 62.76 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd5060-il-200000-n5.txt
Download as CSV file: xf-sd5060-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5691   0.08248   0.07895  -0.0194   1.0000   0.0169
 -10.000  -0.5951   0.07215   0.06867  -0.0257   1.0000   0.0167
  -9.750  -0.6247   0.06074   0.05726  -0.0344   1.0000   0.0162
  -9.500  -0.6554   0.04961   0.04597  -0.0469   1.0000   0.0159
  -9.250  -0.6701   0.04320   0.03917  -0.0514   1.0000   0.0159
  -9.000  -0.6729   0.03816   0.03365  -0.0533   1.0000   0.0162
  -8.750  -0.6664   0.03425   0.02925  -0.0538   1.0000   0.0164
  -8.500  -0.6540   0.03122   0.02574  -0.0538   1.0000   0.0167
  -8.250  -0.6393   0.02845   0.02259  -0.0535   1.0000   0.0171
  -8.000  -0.6226   0.02620   0.02012  -0.0530   1.0000   0.0176
  -7.750  -0.6040   0.02469   0.01847  -0.0523   1.0000   0.0182
  -7.500  -0.5852   0.02363   0.01729  -0.0514   1.0000   0.0191
  -7.250  -0.5676   0.02254   0.01605  -0.0501   1.0000   0.0201
  -6.750  -0.5054   0.01978   0.01282  -0.0526   0.9864   0.0217
  -6.500  -0.4724   0.01866   0.01151  -0.0540   0.9793   0.0224
  -6.250  -0.4405   0.01737   0.01013  -0.0554   0.9717   0.0234
  -6.000  -0.4089   0.01656   0.00925  -0.0565   0.9636   0.0253
  -5.750  -0.3761   0.01587   0.00846  -0.0578   0.9563   0.0272
  -5.500  -0.3460   0.01521   0.00769  -0.0583   0.9470   0.0286
  -5.250  -0.3156   0.01457   0.00694  -0.0589   0.9387   0.0305
  -5.000  -0.2867   0.01400   0.00630  -0.0591   0.9294   0.0337
  -4.750  -0.2589   0.01355   0.00576  -0.0590   0.9198   0.0390
  -4.500  -0.2316   0.01299   0.00526  -0.0588   0.9109   0.0556
  -4.250  -0.2053   0.01251   0.00489  -0.0585   0.9010   0.0836
  -4.000  -0.1789   0.01218   0.00459  -0.0582   0.8914   0.1084
  -3.750  -0.1525   0.01191   0.00435  -0.0577   0.8827   0.1332
  -3.500  -0.1261   0.01167   0.00415  -0.0574   0.8727   0.1588
  -3.250  -0.0997   0.01143   0.00398  -0.0570   0.8633   0.1886
  -3.000  -0.0734   0.01121   0.00379  -0.0565   0.8545   0.2165
  -2.750  -0.0467   0.01101   0.00362  -0.0561   0.8444   0.2399
  -2.500  -0.0201   0.01082   0.00347  -0.0557   0.8352   0.2660
  -2.250   0.0064   0.01063   0.00332  -0.0553   0.8259   0.2959
  -2.000   0.0333   0.01044   0.00319  -0.0550   0.8158   0.3282
  -1.750   0.0599   0.01026   0.00308  -0.0546   0.8063   0.3639
  -1.500   0.0865   0.01008   0.00298  -0.0541   0.7965   0.4037
  -1.250   0.1132   0.00989   0.00291  -0.0538   0.7860   0.4487
  -1.000   0.1395   0.00970   0.00285  -0.0533   0.7757   0.4993
  -0.750   0.1655   0.00951   0.00280  -0.0526   0.7655   0.5552
  -0.500   0.1912   0.00931   0.00278  -0.0519   0.7539   0.6162
  -0.250   0.2162   0.00912   0.00277  -0.0509   0.7423   0.6809
   0.000   0.2403   0.00893   0.00277  -0.0496   0.7305   0.7512
   0.250   0.2641   0.00877   0.00276  -0.0481   0.7181   0.8247
   0.500   0.2936   0.00865   0.00271  -0.0477   0.7046   0.9045
   0.750   0.3356   0.00859   0.00261  -0.0503   0.6887   0.9838
   1.000   0.3650   0.00866   0.00257  -0.0505   0.6725   1.0000
   1.250   0.3916   0.00875   0.00256  -0.0501   0.6561   1.0000
   1.500   0.4182   0.00885   0.00257  -0.0497   0.6391   1.0000
   1.750   0.4449   0.00897   0.00259  -0.0493   0.6215   1.0000
   2.000   0.4715   0.00910   0.00262  -0.0489   0.6027   1.0000
   2.250   0.4982   0.00924   0.00267  -0.0485   0.5822   1.0000
   2.500   0.5246   0.00941   0.00273  -0.0481   0.5607   1.0000
   2.750   0.5511   0.00959   0.00283  -0.0478   0.5365   1.0000
   3.000   0.5774   0.00980   0.00293  -0.0474   0.5118   1.0000
   3.250   0.6035   0.01003   0.00305  -0.0470   0.4852   1.0000
   3.500   0.6294   0.01029   0.00320  -0.0466   0.4572   1.0000
   3.750   0.6551   0.01058   0.00337  -0.0462   0.4275   1.0000
   4.000   0.6807   0.01091   0.00357  -0.0458   0.3963   1.0000
   4.250   0.7060   0.01127   0.00380  -0.0454   0.3646   1.0000
   4.500   0.7312   0.01165   0.00408  -0.0450   0.3347   1.0000
   4.750   0.7562   0.01206   0.00436  -0.0446   0.3057   1.0000
   5.000   0.7810   0.01249   0.00468  -0.0442   0.2780   1.0000
   5.250   0.8058   0.01293   0.00502  -0.0438   0.2540   1.0000
   5.500   0.8307   0.01336   0.00540  -0.0434   0.2327   1.0000
   5.750   0.8552   0.01383   0.00579  -0.0430   0.2132   1.0000
   6.000   0.8798   0.01427   0.00620  -0.0426   0.1963   1.0000
   6.250   0.9043   0.01473   0.00662  -0.0422   0.1815   1.0000
   6.500   0.9286   0.01520   0.00709  -0.0417   0.1679   1.0000
   6.750   0.9526   0.01570   0.00757  -0.0412   0.1557   1.0000
   7.000   0.9766   0.01618   0.00805  -0.0408   0.1445   1.0000
   7.250   1.0005   0.01666   0.00856  -0.0403   0.1345   1.0000
   7.500   1.0239   0.01719   0.00912  -0.0397   0.1256   1.0000
   7.750   1.0467   0.01775   0.00969  -0.0391   0.1164   1.0000
   8.000   1.0701   0.01826   0.01026  -0.0386   0.1079   1.0000
   8.250   1.0923   0.01886   0.01088  -0.0379   0.1004   1.0000
   8.500   1.1148   0.01942   0.01151  -0.0373   0.0927   1.0000
   8.750   1.1364   0.02005   0.01220  -0.0366   0.0858   1.0000
   9.000   1.1575   0.02070   0.01289  -0.0358   0.0784   1.0000
   9.250   1.1785   0.02136   0.01364  -0.0350   0.0719   1.0000
   9.500   1.1979   0.02214   0.01443  -0.0341   0.0652   1.0000
   9.750   1.2177   0.02285   0.01525  -0.0332   0.0591   1.0000
  10.000   1.2352   0.02373   0.01613  -0.0321   0.0526   1.0000
  10.250   1.2535   0.02451   0.01701  -0.0312   0.0457   1.0000
  10.500   1.2697   0.02543   0.01799  -0.0300   0.0398   1.0000
  10.750   1.2839   0.02647   0.01903  -0.0287   0.0342   1.0000
  11.000   1.2975   0.02746   0.02015  -0.0272   0.0305   1.0000
  11.250   1.3069   0.02860   0.02135  -0.0252   0.0271   1.0000
  11.500   1.3138   0.02990   0.02275  -0.0232   0.0246   1.0000
  11.750   1.3211   0.03123   0.02422  -0.0214   0.0220   1.0000
  12.000   1.3248   0.03291   0.02597  -0.0197   0.0197   1.0000
  12.250   1.3278   0.03473   0.02795  -0.0182   0.0179   1.0000
  12.500   1.3306   0.03665   0.03001  -0.0170   0.0162   1.0000
  12.750   1.3307   0.03893   0.03240  -0.0160   0.0149   1.0000
  13.000   1.3278   0.04165   0.03524  -0.0154   0.0139   1.0000
  13.250   1.3268   0.04437   0.03815  -0.0151   0.0129   1.0000
  13.500   1.3230   0.04755   0.04149  -0.0153   0.0124   1.0000
  13.750   1.3179   0.05110   0.04520  -0.0159   0.0118   1.0000
  14.000   1.3107   0.05516   0.04941  -0.0170   0.0114   1.0000
  14.250   1.3016   0.05974   0.05416  -0.0186   0.0112   1.0000
  14.500   1.2897   0.06503   0.05960  -0.0209   0.0109   1.0000
  14.750   1.2765   0.07086   0.06560  -0.0237   0.0108   1.0000
  15.000   1.2604   0.07754   0.07245  -0.0272   0.0107   1.0000
  15.250   1.2441   0.08466   0.07973  -0.0310   0.0106   1.0000
  15.500   1.2264   0.09241   0.08765  -0.0353   0.0105   1.0000
  15.750   1.2096   0.10031   0.09571  -0.0398   0.0106   1.0000
<< Back to SD5060 (9.5%) (sd5060-il)

Polar data table (+)

Polar graphs


<< Back to SD5060 (9.5%) (sd5060-il)