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RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 200,000
Max Cl/Cd: 73.64 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg8-il-200000.txt
Download as CSV file: xf-rg8-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 8 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4780   0.09569   0.09216  -0.0407   1.0000   0.0626
  -9.500  -0.4951   0.08959   0.08614  -0.0459   1.0000   0.0629
  -9.250  -0.5202   0.08392   0.08049  -0.0502   1.0000   0.0630
  -9.000  -0.4985   0.08163   0.07826  -0.0432   1.0000   0.0648
  -8.750  -0.4822   0.08172   0.07835  -0.0389   1.0000   0.0672
  -8.500  -0.4928   0.07779   0.07448  -0.0398   1.0000   0.0679
  -8.250  -0.5074   0.07423   0.07099  -0.0402   1.0000   0.0696
  -8.000  -0.5408   0.06798   0.06479  -0.0441   1.0000   0.0685
  -7.750  -0.5564   0.06368   0.06045  -0.0450   1.0000   0.0697
  -7.500  -0.5688   0.05948   0.05614  -0.0454   1.0000   0.0714
  -7.250  -0.6144   0.03962   0.03456  -0.0482   1.0000   0.0404
  -7.000  -0.6009   0.03604   0.03081  -0.0473   1.0000   0.0386
  -6.750  -0.5880   0.03176   0.02612  -0.0468   1.0000   0.0373
  -6.500  -0.5702   0.02824   0.02213  -0.0462   1.0000   0.0363
  -6.250  -0.5495   0.02559   0.01906  -0.0456   1.0000   0.0360
  -6.000  -0.5270   0.02359   0.01672  -0.0450   1.0000   0.0363
  -5.750  -0.5041   0.02213   0.01500  -0.0443   1.0000   0.0373
  -5.500  -0.4814   0.02120   0.01387  -0.0435   1.0000   0.0389
  -5.250  -0.4585   0.02013   0.01262  -0.0428   1.0000   0.0401
  -5.000  -0.4357   0.01849   0.01094  -0.0423   1.0000   0.0419
  -4.750  -0.4131   0.01765   0.01010  -0.0417   1.0000   0.0444
  -4.500  -0.3815   0.01695   0.00935  -0.0428   0.9980   0.0484
  -4.250  -0.3423   0.01615   0.00856  -0.0455   0.9945   0.0584
  -4.000  -0.3044   0.01505   0.00766  -0.0480   0.9903   0.1010
  -3.750  -0.2651   0.01443   0.00734  -0.0510   0.9860   0.1653
  -3.500  -0.2268   0.01387   0.00714  -0.0539   0.9816   0.2488
  -3.250  -0.1913   0.01301   0.00700  -0.0564   0.9763   0.4022
  -3.000  -0.1515   0.01284   0.00724  -0.0589   0.9720   0.5331
  -2.750  -0.1177   0.01281   0.00725  -0.0600   0.9646   0.5833
  -2.500  -0.0772   0.01287   0.00729  -0.0623   0.9598   0.6206
  -2.250  -0.0437   0.01286   0.00726  -0.0633   0.9521   0.6492
  -2.000  -0.0041   0.01282   0.00723  -0.0653   0.9470   0.6724
  -1.750   0.0299   0.01274   0.00713  -0.0663   0.9394   0.6918
  -1.500   0.0690   0.01261   0.00699  -0.0682   0.9338   0.7098
  -1.250   0.1043   0.01246   0.00685  -0.0694   0.9269   0.7259
  -1.000   0.1419   0.01226   0.00666  -0.0709   0.9206   0.7414
  -0.750   0.1854   0.01199   0.00640  -0.0736   0.9173   0.7562
  -0.500   0.2163   0.01180   0.00622  -0.0738   0.9078   0.7701
  -0.250   0.2599   0.01149   0.00593  -0.0764   0.9039   0.7843
   0.000   0.2922   0.01127   0.00574  -0.0769   0.8941   0.7976
   0.250   0.3334   0.01094   0.00544  -0.0790   0.8886   0.8098
   0.500   0.3640   0.01072   0.00525  -0.0790   0.8768   0.8217
   0.750   0.3964   0.01049   0.00506  -0.0794   0.8650   0.8335
   1.000   0.4290   0.01029   0.00487  -0.0799   0.8521   0.8454
   1.250   0.4600   0.01012   0.00471  -0.0801   0.8376   0.8579
   1.500   0.4890   0.00999   0.00459  -0.0798   0.8214   0.8712
   1.750   0.5162   0.00988   0.00448  -0.0792   0.8042   0.8856
   2.000   0.5422   0.00979   0.00437  -0.0782   0.7864   0.9016
   2.250   0.5654   0.00972   0.00430  -0.0767   0.7659   0.9212
   2.500   0.5942   0.00967   0.00424  -0.0765   0.7451   0.9450
   2.750   0.6332   0.00967   0.00421  -0.0787   0.7216   0.9715
   3.000   0.6723   0.00975   0.00419  -0.0811   0.6969   1.0000
   3.250   0.6984   0.00992   0.00427  -0.0811   0.6718   1.0000
   3.500   0.7248   0.01012   0.00437  -0.0809   0.6463   1.0000
   3.750   0.7504   0.01035   0.00449  -0.0805   0.6204   1.0000
   4.000   0.7754   0.01061   0.00463  -0.0800   0.5939   1.0000
   4.250   0.7996   0.01089   0.00483  -0.0792   0.5664   1.0000
   4.500   0.8233   0.01118   0.00503  -0.0784   0.5382   1.0000
   4.750   0.8465   0.01150   0.00525  -0.0775   0.5094   1.0000
   5.000   0.8694   0.01185   0.00552  -0.0765   0.4803   1.0000
   5.250   0.8918   0.01222   0.00580  -0.0755   0.4509   1.0000
   5.500   0.9139   0.01261   0.00610  -0.0744   0.4211   1.0000
   5.750   0.9356   0.01304   0.00643  -0.0733   0.3908   1.0000
   6.000   0.9567   0.01350   0.00681  -0.0721   0.3599   1.0000
   6.250   0.9775   0.01400   0.00721  -0.0709   0.3289   1.0000
   6.500   0.9982   0.01452   0.00764  -0.0698   0.2977   1.0000
   6.750   1.0185   0.01508   0.00812  -0.0685   0.2664   1.0000
   7.000   1.0382   0.01570   0.00864  -0.0673   0.2355   1.0000
   7.250   1.0572   0.01638   0.00923  -0.0659   0.2046   1.0000
   7.500   1.0752   0.01716   0.00987  -0.0644   0.1731   1.0000
   7.750   1.0926   0.01800   0.01055  -0.0630   0.1413   1.0000
   8.000   1.1097   0.01888   0.01129  -0.0615   0.1131   1.0000
   8.250   1.1258   0.01984   0.01214  -0.0598   0.0910   1.0000
   8.500   1.1415   0.02084   0.01312  -0.0581   0.0716   1.0000
   8.750   1.1525   0.02220   0.01437  -0.0556   0.0543   1.0000
   9.000   1.1593   0.02378   0.01592  -0.0524   0.0413   1.0000
   9.250   1.1685   0.02506   0.01723  -0.0497   0.0342   1.0000
   9.500   1.1760   0.02657   0.01882  -0.0467   0.0304   1.0000
   9.750   1.1857   0.02792   0.02026  -0.0442   0.0279   1.0000
  10.000   1.1930   0.02956   0.02193  -0.0417   0.0261   1.0000
  10.250   1.2010   0.03201   0.02444  -0.0394   0.0247   1.0000
  10.500   1.2144   0.03368   0.02628  -0.0376   0.0238   1.0000
  10.750   1.2277   0.03561   0.02841  -0.0359   0.0230   1.0000
  11.000   1.2395   0.03760   0.03058  -0.0343   0.0222   1.0000
  11.250   1.2479   0.03935   0.03249  -0.0324   0.0212   1.0000
  11.500   1.2550   0.04126   0.03452  -0.0306   0.0204   1.0000
  11.750   1.2608   0.04336   0.03672  -0.0289   0.0197   1.0000
  12.000   1.2660   0.04625   0.03978  -0.0275   0.0192   1.0000
  12.250   1.2661   0.05000   0.04378  -0.0258   0.0189   1.0000
  12.500   1.2613   0.05361   0.04766  -0.0241   0.0188   1.0000
  12.750   1.2520   0.05752   0.05185  -0.0227   0.0188   1.0000
  13.000   1.2418   0.06126   0.05585  -0.0217   0.0188   1.0000
  13.250   1.2284   0.06551   0.06035  -0.0213   0.0188   1.0000
  13.500   1.2146   0.06989   0.06496  -0.0217   0.0188   1.0000
  13.750   1.1991   0.07474   0.07004  -0.0228   0.0189   1.0000
  14.000   1.1836   0.07987   0.07539  -0.0246   0.0189   1.0000
  14.250   1.1661   0.08571   0.08145  -0.0274   0.0191   1.0000
  14.500   1.1458   0.09254   0.08851  -0.0313   0.0192   1.0000
  14.750   1.1199   0.10126   0.09751  -0.0371   0.0195   1.0000
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