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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 50,000
Max Cl/Cd: 33.86 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1495-il-50000-n5.txt
Download as CSV file: xf-rg1495-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5285   0.09357   0.08630  -0.0296   1.0000   0.0525
  -9.500  -0.5343   0.08821   0.08100  -0.0326   1.0000   0.0525
  -9.250  -0.5410   0.08269   0.07555  -0.0361   1.0000   0.0522
  -9.000  -0.5537   0.07726   0.07017  -0.0392   1.0000   0.0520
  -8.750  -0.5684   0.07275   0.06566  -0.0403   1.0000   0.0518
  -8.500  -0.5808   0.06820   0.06106  -0.0410   1.0000   0.0517
  -8.250  -0.5922   0.06367   0.05638  -0.0411   1.0000   0.0518
  -8.000  -0.6008   0.05925   0.05171  -0.0406   1.0000   0.0523
  -7.750  -0.6054   0.05500   0.04712  -0.0396   1.0000   0.0528
  -7.500  -0.6058   0.05096   0.04264  -0.0382   1.0000   0.0533
  -7.250  -0.6001   0.04734   0.03875  -0.0368   1.0000   0.0539
  -7.000  -0.5907   0.04419   0.03533  -0.0353   1.0000   0.0547
  -6.750  -0.5789   0.04136   0.03222  -0.0338   1.0000   0.0558
  -6.500  -0.5649   0.03897   0.02957  -0.0324   1.0000   0.0578
  -6.250  -0.5496   0.03677   0.02703  -0.0309   1.0000   0.0613
  -6.000  -0.5327   0.03437   0.02406  -0.0294   1.0000   0.0645
  -5.750  -0.5135   0.03208   0.02138  -0.0280   1.0000   0.0666
  -5.500  -0.4940   0.03031   0.01951  -0.0267   1.0000   0.0693
  -5.250  -0.4734   0.02875   0.01777  -0.0254   1.0000   0.0734
  -5.000  -0.4522   0.02739   0.01614  -0.0240   1.0000   0.0801
  -4.750  -0.4320   0.02621   0.01497  -0.0228   1.0000   0.0877
  -4.500  -0.4106   0.02497   0.01359  -0.0213   1.0000   0.0957
  -4.250  -0.3901   0.02397   0.01256  -0.0200   1.0000   0.1100
  -4.000  -0.3697   0.02301   0.01163  -0.0188   1.0000   0.1304
  -3.750  -0.3489   0.02206   0.01078  -0.0178   1.0000   0.1628
  -3.500  -0.3297   0.02109   0.01008  -0.0167   1.0000   0.2097
  -3.250  -0.3116   0.02011   0.00950  -0.0154   1.0000   0.2796
  -3.000  -0.2951   0.01913   0.00904  -0.0138   1.0000   0.3835
  -2.750  -0.2812   0.01820   0.00887  -0.0110   1.0000   0.5271
  -2.500  -0.2685   0.01773   0.00921  -0.0062   1.0000   0.7067
  -2.250  -0.2461   0.01783   0.00940  -0.0034   1.0000   0.8481
  -2.000  -0.1808   0.01808   0.00934  -0.0091   1.0000   0.9476
  -1.750  -0.0973   0.01815   0.00895  -0.0199   1.0000   1.0000
  -1.500  -0.0942   0.01810   0.00875  -0.0166   1.0000   1.0000
  -1.250  -0.0893   0.01812   0.00862  -0.0135   1.0000   1.0000
  -1.000  -0.0751   0.01822   0.00856  -0.0122   0.9978   1.0000
  -0.750  -0.0312   0.01849   0.00863  -0.0162   0.9857   1.0000
  -0.500   0.0109   0.01872   0.00867  -0.0198   0.9731   1.0000
  -0.250   0.0518   0.01891   0.00873  -0.0230   0.9599   1.0000
   0.000   0.0919   0.01907   0.00878  -0.0259   0.9464   1.0000
   0.250   0.1316   0.01921   0.00883  -0.0286   0.9326   1.0000
   0.500   0.1713   0.01931   0.00887  -0.0313   0.9185   1.0000
   0.750   0.2112   0.01938   0.00891  -0.0338   0.9043   1.0000
   1.000   0.2514   0.01940   0.00892  -0.0362   0.8899   1.0000
   1.250   0.2897   0.01940   0.00894  -0.0381   0.8747   1.0000
   1.500   0.3263   0.01938   0.00894  -0.0396   0.8588   1.0000
   1.750   0.3619   0.01936   0.00894  -0.0407   0.8425   1.0000
   2.000   0.3951   0.01933   0.00896  -0.0413   0.8251   1.0000
   2.250   0.4234   0.01937   0.00904  -0.0410   0.8052   1.0000
   2.500   0.4539   0.01937   0.00908  -0.0410   0.7859   1.0000
   2.750   0.4835   0.01937   0.00914  -0.0407   0.7659   1.0000
   3.000   0.5096   0.01945   0.00926  -0.0398   0.7437   1.0000
   3.250   0.5371   0.01949   0.00933  -0.0390   0.7208   1.0000
   3.500   0.5634   0.01951   0.00937  -0.0378   0.6941   1.0000
   3.750   0.5870   0.01958   0.00943  -0.0362   0.6634   1.0000
   4.000   0.6097   0.01971   0.00954  -0.0345   0.6314   1.0000
   4.250   0.6325   0.01991   0.00973  -0.0330   0.6007   1.0000
   4.500   0.6552   0.02018   0.01003  -0.0315   0.5712   1.0000
   4.750   0.6770   0.02049   0.01033  -0.0299   0.5395   1.0000
   5.000   0.6982   0.02084   0.01064  -0.0283   0.5059   1.0000
   5.250   0.7178   0.02126   0.01101  -0.0264   0.4678   1.0000
   5.500   0.7365   0.02175   0.01141  -0.0245   0.4274   1.0000
   5.750   0.7544   0.02234   0.01192  -0.0226   0.3850   1.0000
   6.000   0.7716   0.02304   0.01249  -0.0208   0.3424   1.0000
   6.250   0.7884   0.02388   0.01318  -0.0190   0.3017   1.0000
   6.500   0.8055   0.02481   0.01400  -0.0174   0.2649   1.0000
   6.750   0.8227   0.02584   0.01492  -0.0159   0.2340   1.0000
   7.000   0.8403   0.02695   0.01600  -0.0146   0.2079   1.0000
   7.250   0.8575   0.02813   0.01707  -0.0132   0.1863   1.0000
   7.500   0.8762   0.02938   0.01836  -0.0120   0.1678   1.0000
   7.750   0.8943   0.03069   0.01968  -0.0109   0.1512   1.0000
   8.000   0.9137   0.03213   0.02118  -0.0098   0.1378   1.0000
   8.250   0.9324   0.03358   0.02272  -0.0087   0.1255   1.0000
   8.500   0.9509   0.03508   0.02429  -0.0077   0.1154   1.0000
   8.750   0.9695   0.03666   0.02611  -0.0066   0.1059   1.0000
   9.000   0.9864   0.03838   0.02804  -0.0054   0.0973   1.0000
   9.250   1.0043   0.04012   0.02982  -0.0044   0.0911   1.0000
   9.500   1.0188   0.04239   0.03249  -0.0031   0.0845   1.0000
   9.750   1.0320   0.04408   0.03423  -0.0018   0.0786   1.0000
  10.000   1.0432   0.04694   0.03751  -0.0004   0.0744   1.0000
  10.250   1.0489   0.04977   0.04075   0.0015   0.0703   1.0000
  10.500   1.0570   0.05169   0.04273   0.0029   0.0661   1.0000
  10.750   1.0554   0.05473   0.04607   0.0048   0.0632   1.0000
  11.000   1.0440   0.05823   0.04999   0.0074   0.0615   1.0000
  11.250   1.0300   0.06191   0.05399   0.0093   0.0602   1.0000
  11.500   1.0129   0.06599   0.05834   0.0102   0.0595   1.0000
  11.750   0.9919   0.07077   0.06336   0.0099   0.0591   1.0000
  12.000   0.9655   0.07687   0.06967   0.0077   0.0594   1.0000
  12.250   0.9345   0.08469   0.07765   0.0033   0.0604   1.0000
  12.500   0.9031   0.09412   0.08717  -0.0028   0.0616   1.0000
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