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NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(3)-618 (naca633618-il)
Reynolds number: 50,000
Max Cl/Cd: 5.09 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca633618-il-50000.txt
Download as CSV file: xf-naca633618-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(3)-618                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2603   0.12512   0.11799  -0.0390   1.0000   0.3312
 -11.000  -0.2985   0.12671   0.11978  -0.0368   1.0000   0.3361
 -10.000  -0.5650   0.08586   0.07966  -0.0529   1.0000   0.1683
  -9.750  -0.5613   0.08487   0.07872  -0.0497   1.0000   0.1704
  -9.500  -0.7611   0.07330   0.06689  -0.0502   1.0000   0.1515
  -9.250  -0.7792   0.06957   0.06299  -0.0487   1.0000   0.1510
  -9.000  -0.7958   0.06572   0.05888  -0.0476   1.0000   0.1510
  -8.750  -0.8063   0.06188   0.05470  -0.0467   1.0000   0.1512
  -8.500  -0.8037   0.05852   0.05125  -0.0459   1.0000   0.1530
  -8.250  -0.7972   0.05582   0.04843  -0.0449   1.0000   0.1550
  -8.000  -0.7901   0.05325   0.04566  -0.0443   1.0000   0.1579
  -7.750  -0.7818   0.05053   0.04259  -0.0440   1.0000   0.1612
  -7.500  -0.7704   0.04773   0.03929  -0.0442   1.0000   0.1648
  -7.250  -0.7557   0.04523   0.03638  -0.0442   1.0000   0.1685
  -7.000  -0.7398   0.04369   0.03491  -0.0433   1.0000   0.1743
  -6.750  -0.7223   0.04201   0.03290  -0.0431   1.0000   0.1809
  -6.500  -0.7046   0.04043   0.03122  -0.0425   1.0000   0.1873
  -6.250  -0.6866   0.03925   0.02994  -0.0420   1.0000   0.1968
  -6.000  -0.6690   0.03812   0.02888  -0.0410   1.0000   0.2071
  -5.750  -0.6386   0.03722   0.02804  -0.0423   0.9954   0.2245
  -5.500  -0.6054   0.03634   0.02730  -0.0441   0.9889   0.2528
  -5.250  -0.5719   0.03544   0.02700  -0.0460   0.9823   0.3055
  -5.000  -0.5488   0.03540   0.02796  -0.0452   0.9764   0.4056
  -4.750  -0.5314   0.03798   0.03093  -0.0407   0.9708   0.4835
  -4.500  -0.5158   0.04045   0.03339  -0.0362   0.9657   0.5299
  -4.250  -0.5075   0.04267   0.03565  -0.0301   0.9612   0.5562
  -4.000  -0.4941   0.04456   0.03744  -0.0257   0.9572   0.5856
  -3.750  -0.4800   0.04693   0.03977  -0.0202   0.9532   0.6091
  -3.500  -0.4752   0.04798   0.04077  -0.0149   0.9507   0.6304
  -3.250  -0.4687   0.04888   0.04160  -0.0101   0.9491   0.6528
  -3.000  -0.5370   0.04483   0.03772   0.0022   1.0000   0.6504
  -2.750  -0.5296   0.04553   0.03833   0.0064   1.0000   0.6737
  -2.500  -0.5216   0.04602   0.03873   0.0102   1.0000   0.6960
  -2.250  -0.5154   0.04642   0.03905   0.0145   1.0000   0.7153
  -2.000  -0.5082   0.04664   0.03919   0.0183   1.0000   0.7342
  -1.750  -0.5003   0.04674   0.03920   0.0217   1.0000   0.7529
  -1.500  -0.4919   0.04675   0.03911   0.0248   1.0000   0.7711
  -1.250  -0.4828   0.04669   0.03896   0.0275   1.0000   0.7889
  -1.000  -0.4720   0.04656   0.03873   0.0294   1.0000   0.8056
  -0.750  -0.4586   0.04643   0.03848   0.0303   1.0000   0.8209
  -0.500  -0.4469   0.04624   0.03820   0.0320   1.0000   0.8338
  -0.250  -0.4329   0.04609   0.03794   0.0328   1.0000   0.8465
   0.000  -0.4173   0.04600   0.03775   0.0330   1.0000   0.8591
   0.250  -0.4009   0.04600   0.03764   0.0328   1.0000   0.8720
   0.500  -0.3850   0.04600   0.03754   0.0330   1.0000   0.8842
   0.750  -0.3677   0.04608   0.03753   0.0328   1.0000   0.8963
   1.000  -0.3425   0.04668   0.03805   0.0308   0.9966   0.9091
   1.250  -0.3105   0.04775   0.03901   0.0275   0.9898   0.9222
   1.500  -0.2691   0.04965   0.04081   0.0222   0.9815   0.9364
   1.750  -0.2334   0.05050   0.04159   0.0179   0.9717   0.9485
   2.000  -0.1906   0.05201   0.04303   0.0119   0.9630   0.9605
   2.250  -0.1286   0.05504   0.04599   0.0022   0.9534   0.9728
   2.500  -0.0866   0.05607   0.04698  -0.0039   0.9415   0.9828
   2.750  -0.0399   0.05795   0.04883  -0.0110   0.9315   0.9947
   3.000  -0.0139   0.05955   0.05035  -0.0143   0.9206   1.0000
   3.250  -0.0066   0.05909   0.04985  -0.0140   0.9077   1.0000
   3.500   0.0180   0.06062   0.05132  -0.0170   0.8998   1.0000
   3.750   0.0488   0.06211   0.05276  -0.0209   0.8872   1.0000
   4.000   0.0698   0.06318   0.05380  -0.0232   0.8774   1.0000
   4.250   0.1128   0.06612   0.05668  -0.0292   0.8677   1.0000
   4.500   0.1298   0.06685   0.05740  -0.0307   0.8562   1.0000
   4.750   0.1783   0.07077   0.06127  -0.0375   0.8484   1.0000
   5.000   0.1905   0.07104   0.06154  -0.0382   0.8354   1.0000
   5.250   0.2284   0.07438   0.06486  -0.0431   0.8281   1.0000
   5.500   0.2507   0.07568   0.06617  -0.0453   0.8146   1.0000
   5.750   0.2708   0.07757   0.06806  -0.0474   0.8048   1.0000
   6.000   0.3106   0.08088   0.07138  -0.0520   0.7941   1.0000
   6.250   0.3207   0.08195   0.07247  -0.0525   0.7820   1.0000
   6.500   0.3648   0.08634   0.07685  -0.0576   0.7739   1.0000
   6.750   0.3732   0.08699   0.07755  -0.0577   0.7599   1.0000
   7.000   0.3885   0.08909   0.07967  -0.0589   0.7494   1.0000
   7.250   0.4294   0.09306   0.08366  -0.0631   0.7388   1.0000
   7.500   0.4328   0.09397   0.08461  -0.0627   0.7253   1.0000
   7.750   0.4510   0.09662   0.08731  -0.0642   0.7152   1.0000
   8.000   0.4881   0.10037   0.09111  -0.0675   0.7030   1.0000
   8.250   0.4906   0.10154   0.09233  -0.0671   0.6891   1.0000
   8.500   0.5042   0.10413   0.09497  -0.0681   0.6782   1.0000
   8.750   0.5454   0.10862   0.09953  -0.0715   0.6665   1.0000
   9.000   0.5476   0.10977   0.10075  -0.0712   0.6518   1.0000
   9.250   0.5544   0.11199   0.10303  -0.0716   0.6387   1.0000
   9.500   0.5728   0.11520   0.10632  -0.0730   0.6276   1.0000
   9.750   0.6069   0.11920   0.11041  -0.0753   0.6136   1.0000
  10.000   0.6156   0.12113   0.11242  -0.0756   0.5982   1.0000
  10.250   0.6169   0.12326   0.11462  -0.0758   0.5846   1.0000
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