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NACA 0018 (naca0018-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0018 (naca0018-il)
Reynolds number: 50,000
Max Cl/Cd: 26.37 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0018-il-50000-n5.txt
Download as CSV file: xf-naca0018-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0018                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6823   0.11378   0.10456  -0.0245   1.0000   0.1321
 -13.750  -0.8312   0.08288   0.07335  -0.0407   1.0000   0.1386
 -13.500  -0.9075   0.06950   0.05953  -0.0464   1.0000   0.1404
 -13.250  -0.9014   0.06742   0.05747  -0.0462   1.0000   0.1439
 -13.000  -0.9034   0.06454   0.05455  -0.0463   1.0000   0.1477
 -12.750  -0.9242   0.05981   0.04959  -0.0466   1.0000   0.1512
 -12.500  -0.9479   0.05528   0.04475  -0.0461   1.0000   0.1546
 -12.250  -0.9296   0.05457   0.04419  -0.0453   1.0000   0.1593
 -12.000  -0.9334   0.05212   0.04163  -0.0442   1.0000   0.1640
 -11.750  -0.9470   0.04909   0.03831  -0.0424   1.0000   0.1686
 -11.500  -0.9309   0.04826   0.03763  -0.0413   1.0000   0.1739
 -11.250  -0.9320   0.04640   0.03565  -0.0394   1.0000   0.1795
 -11.000  -0.9316   0.04468   0.03384  -0.0372   1.0000   0.1852
 -10.750  -0.9228   0.04362   0.03283  -0.0353   1.0000   0.1913
 -10.500  -0.9266   0.04200   0.03102  -0.0322   1.0000   0.1978
 -10.250  -0.9162   0.04112   0.03024  -0.0302   1.0000   0.2042
 -10.000  -0.9145   0.03998   0.02904  -0.0270   1.0000   0.2113
  -9.750  -0.9081   0.03896   0.02802  -0.0244   1.0000   0.2185
  -9.500  -0.9012   0.03805   0.02711  -0.0217   1.0000   0.2264
  -9.250  -0.8952   0.03708   0.02610  -0.0188   1.0000   0.2345
  -9.000  -0.8869   0.03630   0.02535  -0.0161   1.0000   0.2430
  -8.750  -0.8797   0.03544   0.02448  -0.0132   1.0000   0.2519
  -8.500  -0.8711   0.03472   0.02378  -0.0104   1.0000   0.2613
  -8.250  -0.8619   0.03400   0.02308  -0.0077   1.0000   0.2707
  -8.000  -0.8540   0.03329   0.02232  -0.0047   1.0000   0.2813
  -7.750  -0.8430   0.03271   0.02183  -0.0021   1.0000   0.2912
  -7.500  -0.8354   0.03201   0.02105   0.0009   1.0000   0.3027
  -7.250  -0.8232   0.03154   0.02069   0.0034   1.0000   0.3134
  -7.000  -0.8129   0.03098   0.02013   0.0061   1.0000   0.3249
  -6.750  -0.8030   0.03045   0.01957   0.0088   1.0000   0.3375
  -6.500  -0.7902   0.03005   0.01927   0.0112   1.0000   0.3491
  -6.250  -0.7790   0.02959   0.01881   0.0138   1.0000   0.3620
  -6.000  -0.7675   0.02917   0.01836   0.0163   1.0000   0.3755
  -5.750  -0.7537   0.02885   0.01815   0.0185   1.0000   0.3882
  -5.500  -0.7408   0.02851   0.01783   0.0207   1.0000   0.4019
  -5.250  -0.7283   0.02817   0.01746   0.0230   1.0000   0.4167
  -5.000  -0.7135   0.02796   0.01732   0.0250   1.0000   0.4305
  -4.750  -0.6987   0.02775   0.01718   0.0269   1.0000   0.4446
  -4.500  -0.6605   0.02761   0.01706   0.0244   0.9918   0.4637
  -4.250  -0.6221   0.02747   0.01695   0.0219   0.9821   0.4828
  -4.000  -0.5845   0.02734   0.01685   0.0197   0.9720   0.5017
  -3.750  -0.5459   0.02724   0.01678   0.0174   0.9622   0.5210
  -3.500  -0.5074   0.02715   0.01672   0.0152   0.9519   0.5401
  -3.250  -0.4727   0.02704   0.01664   0.0138   0.9402   0.5587
  -3.000  -0.4338   0.02696   0.01660   0.0117   0.9300   0.5779
  -2.750  -0.3969   0.02687   0.01653   0.0101   0.9185   0.5967
  -2.500  -0.3629   0.02678   0.01648   0.0090   0.9063   0.6154
  -2.250  -0.3183   0.02672   0.01646   0.0063   0.8974   0.6343
  -2.000  -0.2854   0.02672   0.01653   0.0058   0.8839   0.6509
  -1.750  -0.2467   0.02667   0.01653   0.0043   0.8728   0.6683
  -1.500  -0.2093   0.02661   0.01652   0.0032   0.8609   0.6852
  -1.250  -0.1773   0.02658   0.01651   0.0029   0.8471   0.7021
  -1.000  -0.1375   0.02646   0.01640   0.0015   0.8366   0.7194
  -0.750  -0.1074   0.02642   0.01638   0.0017   0.8218   0.7362
  -0.500  -0.0710   0.02650   0.01651   0.0011   0.8077   0.7501
  -0.250  -0.0312   0.02643   0.01644  -0.0001   0.7957   0.7649
   0.000   0.0000   0.02640   0.01641   0.0000   0.7805   0.7806
   0.250   0.0312   0.02643   0.01644   0.0001   0.7649   0.7957
   0.500   0.0710   0.02650   0.01651  -0.0011   0.7501   0.8077
   0.750   0.1074   0.02642   0.01638  -0.0017   0.7362   0.8218
   1.000   0.1375   0.02645   0.01640  -0.0015   0.7194   0.8366
   1.250   0.1773   0.02658   0.01651  -0.0029   0.7021   0.8471
   1.500   0.2093   0.02661   0.01652  -0.0032   0.6852   0.8609
   1.750   0.2466   0.02667   0.01653  -0.0043   0.6683   0.8728
   2.000   0.2854   0.02671   0.01653  -0.0057   0.6509   0.8839
   2.250   0.3183   0.02671   0.01645  -0.0063   0.6343   0.8974
   2.500   0.3629   0.02678   0.01647  -0.0090   0.6154   0.9063
   2.750   0.3969   0.02686   0.01653  -0.0101   0.5967   0.9185
   3.000   0.4337   0.02696   0.01659  -0.0117   0.5779   0.9300
   3.250   0.4726   0.02703   0.01664  -0.0138   0.5587   0.9402
   3.500   0.5075   0.02714   0.01672  -0.0152   0.5401   0.9519
   3.750   0.5458   0.02724   0.01678  -0.0174   0.5210   0.9623
   4.000   0.5845   0.02733   0.01685  -0.0197   0.5017   0.9721
   4.250   0.6222   0.02746   0.01694  -0.0219   0.4828   0.9822
   4.500   0.6605   0.02760   0.01705  -0.0244   0.4637   0.9919
   4.750   0.6985   0.02775   0.01717  -0.0268   0.4446   1.0000
   5.000   0.7133   0.02795   0.01731  -0.0249   0.4305   1.0000
   5.250   0.7281   0.02816   0.01745  -0.0229   0.4167   1.0000
   5.500   0.7406   0.02850   0.01782  -0.0207   0.4019   1.0000
   5.750   0.7536   0.02885   0.01814  -0.0185   0.3882   1.0000
   6.000   0.7673   0.02916   0.01835  -0.0162   0.3755   1.0000
   6.250   0.7788   0.02958   0.01880  -0.0138   0.3620   1.0000
   6.500   0.7901   0.03004   0.01926  -0.0112   0.3491   1.0000
   6.750   0.8029   0.03045   0.01956  -0.0088   0.3375   1.0000
   7.000   0.8128   0.03098   0.02012  -0.0061   0.3249   1.0000
   7.250   0.8231   0.03153   0.02068  -0.0034   0.3134   1.0000
   7.500   0.8353   0.03200   0.02104  -0.0009   0.3027   1.0000
   7.750   0.8429   0.03270   0.02182   0.0021   0.2912   1.0000
   8.000   0.8539   0.03328   0.02232   0.0047   0.2813   1.0000
   8.250   0.8619   0.03399   0.02307   0.0077   0.2707   1.0000
   8.500   0.8711   0.03472   0.02377   0.0104   0.2613   1.0000
   8.750   0.8797   0.03544   0.02447   0.0132   0.2518   1.0000
   9.000   0.8870   0.03629   0.02535   0.0161   0.2430   1.0000
   9.250   0.8953   0.03707   0.02609   0.0188   0.2344   1.0000
   9.500   0.9014   0.03804   0.02710   0.0216   0.2263   1.0000
   9.750   0.9084   0.03895   0.02801   0.0243   0.2184   1.0000
  10.000   0.9148   0.03998   0.02903   0.0270   0.2112   1.0000
  10.250   0.9167   0.04111   0.03023   0.0301   0.2041   1.0000
  10.500   0.9270   0.04200   0.03102   0.0322   0.1977   1.0000
  10.750   0.9234   0.04362   0.03282   0.0353   0.1912   1.0000
  11.000   0.9324   0.04466   0.03381   0.0371   0.1851   1.0000
  11.250   0.9326   0.04640   0.03565   0.0393   0.1795   1.0000
  11.500   0.9319   0.04824   0.03761   0.0412   0.1738   1.0000
  11.750   0.9481   0.04907   0.03827   0.0422   0.1685   1.0000
  12.000   0.9342   0.05212   0.04163   0.0440   0.1639   1.0000
  12.250   0.9309   0.05453   0.04414   0.0451   0.1592   1.0000
  12.500   0.9498   0.05521   0.04464   0.0460   0.1545   1.0000
  12.750   0.9251   0.05982   0.04961   0.0464   0.1511   1.0000
  13.000   0.9050   0.06448   0.05448   0.0461   0.1476   1.0000
  13.250   0.9046   0.06718   0.05722   0.0461   0.1438   1.0000
  13.500   0.9079   0.06961   0.05964   0.0462   0.1403   1.0000
  13.750   0.8310   0.08312   0.07360   0.0404   0.1385   1.0000
  14.000   0.6851   0.11354   0.10433   0.0244   0.1321   1.0000
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