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davissm (davissm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 500,000
Max Cl/Cd: 131.74 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davissm-il-500000.txt
Download as CSV file: xf-davissm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: davissm                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3158   0.11401   0.11170  -0.0329   1.0000   0.0136
  -9.000  -0.3199   0.11253   0.11027  -0.0313   1.0000   0.0140
  -8.750  -0.3271   0.11156   0.10935  -0.0295   0.9995   0.0142
  -8.500  -0.3118   0.10808   0.10587  -0.0348   0.9972   0.0143
  -8.250  -0.2975   0.10460   0.10238  -0.0401   0.9939   0.0143
  -8.000  -0.2831   0.10111   0.09890  -0.0453   0.9886   0.0144
  -7.750  -0.2683   0.09587   0.09366  -0.0487   0.9848   0.0145
  -7.500  -0.2541   0.09173   0.08951  -0.0493   0.9824   0.0149
  -7.250  -0.2340   0.08795   0.08572  -0.0535   0.9795   0.0151
  -7.000  -0.2116   0.08419   0.08196  -0.0586   0.9772   0.0155
  -6.750  -0.1896   0.08055   0.07831  -0.0638   0.9732   0.0159
  -6.500  -0.1629   0.07661   0.07434  -0.0702   0.9706   0.0165
  -6.250  -0.1318   0.07243   0.07013  -0.0777   0.9686   0.0173
  -6.000  -0.0895   0.06788   0.06553  -0.0889   0.9666   0.0189
  -5.750  -0.0387   0.06313   0.06071  -0.1030   0.9623   0.0193
  -5.500   0.0008   0.05857   0.05607  -0.1117   0.9578   0.0194
  -5.250   0.0267   0.05284   0.05031  -0.1172   0.9541   0.0201
  -5.000   0.0521   0.05030   0.04773  -0.1199   0.9489   0.0209
  -4.750   0.0831   0.04755   0.04491  -0.1244   0.9427   0.0223
  -4.500   0.1237   0.04395   0.04120  -0.1315   0.9380   0.0241
  -4.250   0.1778   0.04038   0.03744  -0.1405   0.9318   0.0262
  -4.000   0.2188   0.03652   0.03339  -0.1461   0.9266   0.0264
  -3.750   0.2543   0.03043   0.02711  -0.1522   0.9218   0.0277
  -3.500   0.2813   0.02882   0.02544  -0.1537   0.9155   0.0289
  -3.250   0.3129   0.02708   0.02356  -0.1557   0.9105   0.0317
  -3.000   0.3531   0.02563   0.02178  -0.1575   0.9050   0.0360
  -2.250   0.4489   0.01780   0.01326  -0.1634   0.8880   0.0415
  -2.000   0.4784   0.01859   0.01381  -0.1627   0.8821   0.0485
  -1.750   0.5147   0.01377   0.00828  -0.1645   0.8770   0.0372
  -1.500   0.5434   0.01304   0.00739  -0.1645   0.8706   0.0367
  -1.250   0.5725   0.01193   0.00606  -0.1648   0.8652   0.0369
  -1.000   0.6005   0.01096   0.00499  -0.1649   0.8581   0.0393
  -0.750   0.6287   0.01046   0.00440  -0.1648   0.8521   0.0407
  -0.500   0.6563   0.01009   0.00400  -0.1647   0.8442   0.0426
  -0.250   0.6843   0.00980   0.00365  -0.1646   0.8377   0.0449
   0.000   0.7117   0.00960   0.00345  -0.1645   0.8295   0.0476
   0.250   0.7397   0.00929   0.00309  -0.1644   0.8227   0.0516
   0.500   0.7672   0.00911   0.00292  -0.1643   0.8140   0.0563
   0.750   0.7949   0.00902   0.00280  -0.1642   0.8060   0.0617
   1.000   0.8225   0.00886   0.00268  -0.1641   0.7970   0.0814
   1.250   0.8490   0.00712   0.00280  -0.1644   0.7880   1.0000
   1.500   0.8764   0.00720   0.00278  -0.1642   0.7787   1.0000
   1.750   0.9033   0.00728   0.00277  -0.1639   0.7662   1.0000
   2.000   0.9297   0.00736   0.00279  -0.1635   0.7500   1.0000
   2.250   0.9563   0.00746   0.00282  -0.1631   0.7350   1.0000
   2.500   0.9827   0.00757   0.00287  -0.1628   0.7193   1.0000
   2.750   1.0089   0.00771   0.00294  -0.1624   0.7014   1.0000
   3.000   1.0346   0.00788   0.00304  -0.1618   0.6811   1.0000
   3.250   1.0605   0.00805   0.00315  -0.1614   0.6611   1.0000
   3.500   1.0858   0.00827   0.00329  -0.1608   0.6388   1.0000
   3.750   1.1100   0.00856   0.00344  -0.1600   0.6072   1.0000
   4.000   1.1338   0.00889   0.00366  -0.1592   0.5722   1.0000
   4.250   1.1560   0.00936   0.00391  -0.1581   0.5247   1.0000
   4.500   1.1769   0.00998   0.00424  -0.1568   0.4658   1.0000
   4.750   1.1960   0.01081   0.00468  -0.1552   0.3904   1.0000
   5.000   1.2097   0.01226   0.00542  -0.1529   0.2624   1.0000
   5.250   1.2164   0.01457   0.00671  -0.1495   0.0835   1.0000
   5.500   1.2384   0.01515   0.00728  -0.1485   0.0682   1.0000
   5.750   1.2604   0.01572   0.00782  -0.1475   0.0572   1.0000
   6.000   1.2814   0.01636   0.00844  -0.1463   0.0466   1.0000
   6.250   1.3043   0.01677   0.00886  -0.1455   0.0399   1.0000
   6.500   1.3240   0.01749   0.00962  -0.1440   0.0334   1.0000
   6.750   1.3450   0.01804   0.01017  -0.1428   0.0289   1.0000
   7.000   1.3611   0.01900   0.01120  -0.1407   0.0252   1.0000
   7.250   1.3800   0.01965   0.01192  -0.1390   0.0233   1.0000
   7.500   1.3975   0.02038   0.01270  -0.1372   0.0215   1.0000
   7.750   1.4117   0.02132   0.01369  -0.1348   0.0200   1.0000
   8.000   1.4160   0.02306   0.01558  -0.1305   0.0188   1.0000
   8.250   1.4261   0.02433   0.01696  -0.1274   0.0181   1.0000
   8.500   1.4408   0.02511   0.01782  -0.1251   0.0173   1.0000
   8.750   1.4524   0.02602   0.01882  -0.1223   0.0164   1.0000
   9.000   1.4623   0.02720   0.02009  -0.1193   0.0157   1.0000
   9.250   1.4730   0.02840   0.02139  -0.1165   0.0151   1.0000
   9.500   1.4838   0.02971   0.02280  -0.1138   0.0146   1.0000
   9.750   1.4944   0.03106   0.02423  -0.1113   0.0140   1.0000
  10.000   1.5051   0.03310   0.02638  -0.1089   0.0134   1.0000
  10.250   1.5211   0.03637   0.02991  -0.1074   0.0126   1.0000
  10.500   1.5300   0.03740   0.03110  -0.1046   0.0121   1.0000
  10.750   1.5406   0.03940   0.03331  -0.1022   0.0117   1.0000
  11.000   1.5488   0.04175   0.03589  -0.0996   0.0114   1.0000
  11.250   1.5536   0.04423   0.03862  -0.0967   0.0110   1.0000
  11.500   1.5546   0.04702   0.04166  -0.0935   0.0107   1.0000
  11.750   1.5512   0.05029   0.04523  -0.0901   0.0106   1.0000
  12.000   1.5432   0.05393   0.04916  -0.0865   0.0104   1.0000
  12.250   1.5312   0.05795   0.05346  -0.0829   0.0103   1.0000
  12.500   1.5094   0.06357   0.05945  -0.0791   0.0104   1.0000
  12.750   1.4803   0.07023   0.06648  -0.0758   0.0106   1.0000
  13.000   1.4505   0.07699   0.07355  -0.0737   0.0108   1.0000
  13.250   1.4209   0.08396   0.08076  -0.0728   0.0110   1.0000
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