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RG-12 (rg12-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 50,000
Max Cl/Cd: 34.36 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12-il-50000-n5.txt
Download as CSV file: xf-rg12-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-12                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5414   0.08101   0.07399  -0.0389   1.0000   0.0395
  -8.750  -0.5510   0.07687   0.06988  -0.0400   1.0000   0.0392
  -8.500  -0.5603   0.07301   0.06603  -0.0404   1.0000   0.0390
  -8.250  -0.5680   0.06903   0.06200  -0.0407   1.0000   0.0387
  -8.000  -0.5747   0.06502   0.05790  -0.0406   1.0000   0.0385
  -7.750  -0.5798   0.06094   0.05367  -0.0401   1.0000   0.0384
  -7.500  -0.5819   0.05696   0.04947  -0.0394   1.0000   0.0383
  -7.250  -0.5808   0.05307   0.04530  -0.0384   1.0000   0.0382
  -7.000  -0.5768   0.04920   0.04107  -0.0372   1.0000   0.0383
  -6.750  -0.5694   0.04547   0.03691  -0.0358   1.0000   0.0385
  -6.500  -0.5587   0.04200   0.03295  -0.0344   1.0000   0.0389
  -6.250  -0.5446   0.03881   0.02922  -0.0329   1.0000   0.0394
  -6.000  -0.5295   0.03606   0.02630  -0.0317   1.0000   0.0414
  -5.750  -0.5121   0.03418   0.02422  -0.0305   1.0000   0.0450
  -5.500  -0.4924   0.03205   0.02167  -0.0292   1.0000   0.0493
  -5.250  -0.4710   0.02981   0.01904  -0.0277   1.0000   0.0525
  -5.000  -0.4506   0.02805   0.01723  -0.0264   1.0000   0.0573
  -4.750  -0.4296   0.02663   0.01559  -0.0250   1.0000   0.0675
  -4.500  -0.4084   0.02521   0.01403  -0.0235   1.0000   0.0791
  -4.250  -0.3884   0.02401   0.01288  -0.0222   1.0000   0.0990
  -4.000  -0.3681   0.02277   0.01168  -0.0209   1.0000   0.1260
  -3.750  -0.3479   0.02150   0.01060  -0.0199   1.0000   0.1686
  -3.500  -0.3299   0.02024   0.00976  -0.0187   1.0000   0.2418
  -3.250  -0.3139   0.01888   0.00914  -0.0172   1.0000   0.3719
  -3.000  -0.3035   0.01778   0.00907  -0.0132   1.0000   0.5659
  -2.750  -0.2937   0.01771   0.00941  -0.0077   1.0000   0.7267
  -2.500  -0.2807   0.01779   0.00946  -0.0034   1.0000   0.8099
  -2.250  -0.2598   0.01789   0.00944  -0.0005   1.0000   0.8756
  -2.000  -0.2068   0.01809   0.00931  -0.0039   1.0000   0.9374
  -1.750  -0.1192   0.01821   0.00887  -0.0150   1.0000   0.9824
  -1.500  -0.0769   0.01810   0.00850  -0.0188   1.0000   1.0000
  -1.250  -0.0762   0.01798   0.00830  -0.0152   1.0000   1.0000
  -1.000  -0.0745   0.01791   0.00814  -0.0117   1.0000   1.0000
  -0.750  -0.0702   0.01790   0.00802  -0.0088   1.0000   1.0000
  -0.500  -0.0409   0.01811   0.00803  -0.0103   0.9932   1.0000
  -0.250   0.0023   0.01838   0.00815  -0.0143   0.9809   1.0000
   0.000   0.0440   0.01861   0.00825  -0.0179   0.9679   1.0000
   0.250   0.0845   0.01880   0.00833  -0.0211   0.9543   1.0000
   0.500   0.1243   0.01895   0.00841  -0.0240   0.9402   1.0000
   0.750   0.1637   0.01906   0.00848  -0.0267   0.9258   1.0000
   1.000   0.2030   0.01915   0.00854  -0.0292   0.9110   1.0000
   1.250   0.2424   0.01919   0.00859  -0.0316   0.8961   1.0000
   1.500   0.2823   0.01919   0.00863  -0.0340   0.8807   1.0000
   1.750   0.3204   0.01918   0.00867  -0.0358   0.8646   1.0000
   2.000   0.3580   0.01913   0.00868  -0.0374   0.8479   1.0000
   2.250   0.3921   0.01910   0.00870  -0.0383   0.8293   1.0000
   2.500   0.4239   0.01908   0.00879  -0.0386   0.8091   1.0000
   2.750   0.4574   0.01902   0.00880  -0.0391   0.7890   1.0000
   3.000   0.4864   0.01904   0.00889  -0.0388   0.7659   1.0000
   3.250   0.5149   0.01908   0.00898  -0.0383   0.7418   1.0000
   3.500   0.5433   0.01913   0.00914  -0.0377   0.7167   1.0000
   3.750   0.5705   0.01923   0.00929  -0.0370   0.6899   1.0000
   4.000   0.5963   0.01938   0.00948  -0.0360   0.6614   1.0000
   4.250   0.6211   0.01958   0.00972  -0.0348   0.6312   1.0000
   4.500   0.6452   0.01982   0.00998  -0.0336   0.5994   1.0000
   4.750   0.6689   0.02010   0.01032  -0.0322   0.5667   1.0000
   5.000   0.6908   0.02047   0.01071  -0.0307   0.5312   1.0000
   5.250   0.7125   0.02088   0.01110  -0.0292   0.4950   1.0000
   5.500   0.7331   0.02136   0.01156  -0.0276   0.4569   1.0000
   5.750   0.7528   0.02191   0.01209  -0.0260   0.4169   1.0000
   6.000   0.7716   0.02256   0.01268  -0.0243   0.3753   1.0000
   6.250   0.7895   0.02330   0.01343  -0.0226   0.3328   1.0000
   6.500   0.8065   0.02417   0.01421  -0.0210   0.2902   1.0000
   6.750   0.8227   0.02518   0.01511  -0.0193   0.2477   1.0000
   7.000   0.8385   0.02635   0.01618  -0.0178   0.2076   1.0000
   7.250   0.8541   0.02770   0.01743  -0.0163   0.1713   1.0000
   7.500   0.8690   0.02920   0.01883  -0.0148   0.1411   1.0000
   7.750   0.8836   0.03081   0.02040  -0.0133   0.1158   1.0000
   8.000   0.8976   0.03260   0.02215  -0.0118   0.0980   1.0000
   8.250   0.9130   0.03438   0.02407  -0.0104   0.0821   1.0000
   8.500   0.9285   0.03640   0.02610  -0.0090   0.0719   1.0000
   8.750   0.9435   0.03832   0.02824  -0.0076   0.0620   1.0000
   9.000   0.9606   0.04078   0.03098  -0.0064   0.0554   1.0000
   9.250   0.9771   0.04341   0.03386  -0.0052   0.0511   1.0000
   9.500   0.9907   0.04628   0.03681  -0.0041   0.0475   1.0000
   9.750   0.9973   0.04925   0.04035  -0.0023   0.0439   1.0000
  10.000   1.0010   0.05194   0.04335  -0.0006   0.0407   1.0000
  10.250   1.0030   0.05478   0.04639   0.0011   0.0388   1.0000
  10.500   1.0015   0.05796   0.04977   0.0028   0.0378   1.0000
  11.000   0.9831   0.06553   0.05779   0.0056   0.0369   1.0000
  11.250   0.9673   0.06977   0.06231   0.0058   0.0368   1.0000
  11.500   0.9498   0.07457   0.06734   0.0048   0.0368   1.0000
  11.750   0.9314   0.08001   0.07297   0.0026   0.0369   1.0000
  12.000   0.9134   0.08608   0.07919  -0.0008   0.0370   1.0000
  12.250   0.8753   0.09712   0.09054  -0.0094   0.0385   1.0000
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