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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 50,000
Max Cl/Cd: 32.68 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1495-il-50000.txt
Download as CSV file: xf-rg1495-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9.5% AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5142   0.13070   0.12334  -0.0068   1.0000   0.2162
 -10.500  -0.4861   0.12422   0.11678  -0.0052   1.0000   0.2247
 -10.250  -0.5119   0.12418   0.11690  -0.0080   1.0000   0.2311
 -10.000  -0.4883   0.11864   0.11131  -0.0065   1.0000   0.2441
  -9.750  -0.4759   0.11445   0.10714  -0.0059   1.0000   0.2555
  -9.500  -0.4739   0.11111   0.10384  -0.0061   1.0000   0.2654
  -9.250  -0.4958   0.11042   0.10329  -0.0076   1.0000   0.2753
  -9.000  -0.4778   0.10580   0.09866  -0.0064   1.0000   0.2889
  -8.750  -0.4628   0.10144   0.09430  -0.0056   1.0000   0.2996
  -8.500  -0.4597   0.09814   0.09105  -0.0053   1.0000   0.3112
  -8.250  -0.4601   0.09516   0.08815  -0.0050   1.0000   0.3238
  -8.000  -0.4568   0.09208   0.08512  -0.0042   1.0000   0.3386
  -7.750  -0.4488   0.08901   0.08206  -0.0028   1.0000   0.3586
  -7.500  -0.4570   0.08693   0.08009  -0.0014   1.0000   0.3779
  -6.750  -0.5519   0.06171   0.05482  -0.0298   1.0000   0.1691
  -6.500  -0.5578   0.05421   0.04677  -0.0317   1.0000   0.1454
  -6.250  -0.5480   0.04983   0.04210  -0.0310   1.0000   0.1384
  -6.000  -0.5389   0.04567   0.03754  -0.0300   1.0000   0.1355
  -5.750  -0.5268   0.04214   0.03360  -0.0288   1.0000   0.1360
  -5.500  -0.5120   0.03884   0.02984  -0.0274   1.0000   0.1367
  -5.250  -0.4946   0.03574   0.02625  -0.0261   1.0000   0.1370
  -5.000  -0.4749   0.03301   0.02303  -0.0247   1.0000   0.1394
  -4.750  -0.4547   0.03075   0.02043  -0.0234   1.0000   0.1468
  -4.500  -0.4329   0.02888   0.01818  -0.0220   1.0000   0.1568
  -4.250  -0.4101   0.02692   0.01616  -0.0208   1.0000   0.1685
  -4.000  -0.3879   0.02529   0.01450  -0.0194   1.0000   0.1905
  -3.750  -0.3655   0.02371   0.01306  -0.0180   1.0000   0.2235
  -3.500  -0.3436   0.02214   0.01181  -0.0166   1.0000   0.2813
  -3.250  -0.3243   0.02032   0.01066  -0.0147   1.0000   0.3844
  -3.000  -0.3176   0.01807   0.01018  -0.0089   1.0000   0.6133
  -2.750  -0.0995   0.01905   0.01035  -0.0337   1.0000   1.0000
  -2.500  -0.0994   0.01867   0.00983  -0.0305   1.0000   1.0000
  -2.250  -0.0984   0.01841   0.00944  -0.0271   1.0000   1.0000
  -2.000  -0.0970   0.01823   0.00912  -0.0236   1.0000   1.0000
  -1.750  -0.0951   0.01813   0.00888  -0.0201   1.0000   1.0000
  -1.500  -0.0922   0.01807   0.00870  -0.0167   1.0000   1.0000
  -1.250  -0.0875   0.01808   0.00857  -0.0136   1.0000   1.0000
  -1.000  -0.0811   0.01814   0.00849  -0.0109   1.0000   1.0000
  -0.750  -0.0722   0.01826   0.00848  -0.0085   1.0000   1.0000
  -0.500  -0.0612   0.01845   0.00851  -0.0066   1.0000   1.0000
  -0.250  -0.0487   0.01869   0.00863  -0.0050   1.0000   1.0000
   0.000  -0.0352   0.01900   0.00882  -0.0037   1.0000   1.0000
   0.250  -0.0210   0.01935   0.00908  -0.0026   1.0000   1.0000
   0.500  -0.0063   0.01977   0.00940  -0.0016   1.0000   1.0000
   0.750   0.0085   0.02025   0.00980  -0.0008   1.0000   1.0000
   1.000   0.0234   0.02079   0.01028  -0.0002   1.0000   1.0000
   1.250   0.0383   0.02140   0.01084   0.0003   1.0000   1.0000
   1.500   0.0572   0.02213   0.01154  -0.0001   0.9982   1.0000
   1.750   0.1179   0.02354   0.01294  -0.0082   0.9773   1.0000
   2.000   0.1787   0.02478   0.01422  -0.0158   0.9567   1.0000
   2.250   0.2277   0.02562   0.01513  -0.0210   0.9339   1.0000
   2.500   0.2848   0.02641   0.01602  -0.0271   0.9123   1.0000
   2.750   0.3312   0.02697   0.01671  -0.0310   0.8887   1.0000
   3.000   0.3827   0.02739   0.01728  -0.0353   0.8660   1.0000
   3.250   0.4373   0.02754   0.01762  -0.0396   0.8426   1.0000
   3.500   0.4893   0.02744   0.01776  -0.0428   0.8171   1.0000
   3.750   0.5474   0.02661   0.01717  -0.0455   0.7883   1.0000
   4.000   0.5977   0.02562   0.01642  -0.0462   0.7579   1.0000
   4.250   0.6373   0.02499   0.01596  -0.0456   0.7281   1.0000
   4.500   0.6726   0.02446   0.01555  -0.0443   0.6965   1.0000
   4.750   0.7040   0.02400   0.01518  -0.0422   0.6613   1.0000
   5.000   0.7302   0.02373   0.01491  -0.0394   0.6208   1.0000
   5.250   0.7543   0.02356   0.01463  -0.0363   0.5747   1.0000
   5.500   0.7728   0.02379   0.01474  -0.0330   0.5224   1.0000
   5.750   0.7916   0.02422   0.01494  -0.0298   0.4669   1.0000
   6.000   0.8103   0.02496   0.01533  -0.0270   0.4132   1.0000
   6.250   0.8275   0.02604   0.01620  -0.0245   0.3650   1.0000
   6.500   0.8468   0.02726   0.01714  -0.0225   0.3240   1.0000
   6.750   0.8655   0.02870   0.01855  -0.0206   0.2888   1.0000
   7.000   0.8857   0.03028   0.02006  -0.0191   0.2597   1.0000
   7.250   0.9067   0.03200   0.02169  -0.0178   0.2352   1.0000
   7.500   0.9265   0.03395   0.02376  -0.0163   0.2148   1.0000
   7.750   0.9476   0.03594   0.02570  -0.0152   0.1967   1.0000
   8.000   0.9671   0.03831   0.02825  -0.0139   0.1823   1.0000
   8.250   0.9824   0.04087   0.03114  -0.0122   0.1699   1.0000
   8.500   0.9934   0.04389   0.03458  -0.0102   0.1601   1.0000
   8.750   1.0106   0.04714   0.03792  -0.0091   0.1519   1.0000
   9.000   1.0098   0.05075   0.04219  -0.0063   0.1463   1.0000
   9.250   1.0277   0.05406   0.04543  -0.0055   0.1382   1.0000
   9.500   1.0195   0.05849   0.05046  -0.0028   0.1368   1.0000
   9.750   1.0066   0.06315   0.05557  -0.0006   0.1361   1.0000
  10.000   0.9895   0.06798   0.06073   0.0012   0.1361   1.0000
  10.250   0.9690   0.07295   0.06591   0.0025   0.1366   1.0000
  10.500   0.9476   0.07786   0.07094   0.0035   0.1375   1.0000
  10.750   0.9287   0.08330   0.07643   0.0033   0.1383   1.0000
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