Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

davissm (davissm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 100,000
Max Cl/Cd: 69.38 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davissm-il-100000-n5.txt
Download as CSV file: xf-davissm-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3298   0.10786   0.10307  -0.0266   1.0000   0.0326
  -7.500  -0.3402   0.10686   0.10215  -0.0237   1.0000   0.0330
  -7.250  -0.3507   0.10585   0.10123  -0.0210   1.0000   0.0334
  -7.000  -0.3305   0.10266   0.09802  -0.0278   0.9951   0.0349
  -6.750  -0.2980   0.10024   0.09557  -0.0414   0.9876   0.0359
  -6.500  -0.2656   0.09684   0.09212  -0.0521   0.9814   0.0362
  -6.250  -0.2536   0.09070   0.08600  -0.0525   0.9785   0.0368
  -6.000  -0.2422   0.08612   0.08143  -0.0513   0.9750   0.0377
  -5.750  -0.2223   0.08221   0.07748  -0.0541   0.9705   0.0388
  -5.500  -0.1948   0.07823   0.07346  -0.0596   0.9670   0.0403
  -5.250  -0.1671   0.07448   0.06967  -0.0654   0.9620   0.0421
  -5.000  -0.1338   0.07059   0.06571  -0.0726   0.9572   0.0443
  -4.750  -0.0621   0.06641   0.06126  -0.0917   0.9539   0.0482
  -4.500  -0.0144   0.06108   0.05578  -0.1019   0.9519   0.0491
  -4.250  -0.0127   0.05785   0.05265  -0.0978   0.9455   0.0515
  -4.000   0.0228   0.05447   0.04919  -0.1029   0.9421   0.0559
  -3.750   0.1075   0.05036   0.04449  -0.1208   0.9404   0.0623
  -3.500   0.1401   0.04537   0.03951  -0.1250   0.9386   0.0636
  -3.250   0.1826   0.04092   0.03478  -0.1300   0.9339   0.0474
  -2.750   0.2709   0.03379   0.02706  -0.1406   0.9276   0.0461
  -2.500   0.3168   0.03050   0.02339  -0.1456   0.9254   0.0443
  -2.250   0.3606   0.02769   0.02010  -0.1495   0.9225   0.0438
  -2.000   0.3957   0.02594   0.01786  -0.1511   0.9163   0.0470
  -1.750   0.4350   0.02421   0.01562  -0.1535   0.9127   0.0479
  -1.500   0.4747   0.02271   0.01369  -0.1559   0.9099   0.0485
  -1.250   0.5040   0.02153   0.01227  -0.1563   0.9028   0.0496
  -1.000   0.5381   0.02067   0.01133  -0.1578   0.8980   0.0541
  -0.750   0.5727   0.01992   0.01041  -0.1591   0.8935   0.0583
  -0.500   0.6010   0.01936   0.00973  -0.1590   0.8858   0.0605
  -0.250   0.6355   0.01865   0.00895  -0.1602   0.8812   0.0636
   0.000   0.6621   0.01835   0.00871  -0.1600   0.8727   0.0715
   0.250   0.6958   0.01791   0.00820  -0.1610   0.8672   0.0792
   0.500   0.7235   0.01773   0.00798  -0.1608   0.8585   0.0891
   0.750   0.7569   0.01732   0.00767  -0.1618   0.8525   0.1243
   1.000   0.7815   0.01570   0.00775  -0.1613   0.8434   1.0000
   1.250   0.8120   0.01570   0.00757  -0.1615   0.8363   1.0000
   1.500   0.8385   0.01580   0.00757  -0.1611   0.8264   1.0000
   1.750   0.8657   0.01589   0.00759  -0.1607   0.8168   1.0000
   2.000   0.8956   0.01587   0.00752  -0.1608   0.8088   1.0000
   2.250   0.9211   0.01601   0.00764  -0.1602   0.7976   1.0000
   2.500   0.9477   0.01611   0.00774  -0.1597   0.7870   1.0000
   2.750   0.9752   0.01618   0.00780  -0.1594   0.7767   1.0000
   3.000   1.0032   0.01622   0.00785  -0.1592   0.7663   1.0000
   3.250   1.0291   0.01635   0.00806  -0.1586   0.7537   1.0000
   3.500   1.0553   0.01645   0.00820  -0.1580   0.7402   1.0000
   3.750   1.0820   0.01646   0.00821  -0.1572   0.7230   1.0000
   4.000   1.1061   0.01651   0.00827  -0.1560   0.6980   1.0000
   4.250   1.1305   0.01659   0.00837  -0.1548   0.6714   1.0000
   4.500   1.1547   0.01675   0.00852  -0.1536   0.6447   1.0000
   4.750   1.1780   0.01698   0.00869  -0.1523   0.6117   1.0000
   5.000   1.2002   0.01730   0.00894  -0.1508   0.5733   1.0000
   5.250   1.2203   0.01779   0.00925  -0.1489   0.5240   1.0000
   5.500   1.2366   0.01856   0.00974  -0.1463   0.4538   1.0000
   5.750   1.2462   0.01992   0.01047  -0.1429   0.3465   1.0000
   6.250   1.2501   0.02492   0.01358  -0.1349   0.0872   1.0000
   6.500   1.2636   0.02625   0.01493  -0.1325   0.0733   1.0000
   6.750   1.2779   0.02740   0.01621  -0.1302   0.0636   1.0000
   7.000   1.2878   0.02882   0.01776  -0.1272   0.0573   1.0000
   7.250   1.2998   0.02997   0.01905  -0.1246   0.0506   1.0000
   7.500   1.3055   0.03155   0.02065  -0.1211   0.0462   1.0000
   7.750   1.3146   0.03289   0.02218  -0.1180   0.0432   1.0000
   8.000   1.3229   0.03426   0.02366  -0.1148   0.0398   1.0000
   8.250   1.3313   0.03569   0.02510  -0.1120   0.0365   1.0000
   8.500   1.3418   0.03743   0.02692  -0.1095   0.0341   1.0000
   8.750   1.3588   0.03920   0.02889  -0.1077   0.0320   1.0000
   9.000   1.3799   0.04114   0.03097  -0.1066   0.0301   1.0000
   9.250   1.3996   0.04302   0.03298  -0.1056   0.0283   1.0000
   9.500   1.4151   0.04500   0.03499  -0.1043   0.0264   1.0000
   9.750   1.4370   0.04751   0.03782  -0.1035   0.0246   1.0000
  10.000   1.4595   0.05068   0.04139  -0.1028   0.0236   1.0000
  10.250   1.4730   0.05396   0.04513  -0.1009   0.0228   1.0000
  10.500   1.4790   0.05727   0.04883  -0.0980   0.0223   1.0000
  10.750   1.4789   0.06057   0.05251  -0.0945   0.0219   1.0000
  11.000   1.4741   0.06370   0.05597  -0.0907   0.0214   1.0000
  11.250   1.4670   0.06665   0.05920  -0.0871   0.0209   1.0000
  11.500   1.4592   0.06946   0.06223  -0.0839   0.0203   1.0000
  11.750   1.4496   0.07246   0.06546  -0.0811   0.0198   1.0000
  12.000   1.4384   0.07578   0.06899  -0.0786   0.0195   1.0000
  12.250   1.4257   0.07944   0.07286  -0.0766   0.0192   1.0000
  12.500   1.4112   0.08352   0.07714  -0.0751   0.0189   1.0000
  12.750   1.3941   0.08823   0.08209  -0.0741   0.0188   1.0000
  13.000   1.3754   0.09339   0.08748  -0.0737   0.0187   1.0000
  13.250   1.3558   0.09895   0.09328  -0.0742   0.0186   1.0000
  13.500   1.3356   0.10501   0.09957  -0.0756   0.0186   1.0000
  13.750   1.3147   0.11166   0.10645  -0.0780   0.0187   1.0000
  14.000   1.2914   0.11959   0.11464  -0.0820   0.0189   1.0000
  14.250   1.2602   0.13101   0.12634  -0.0891   0.0194   1.0000
  14.500   0.9910   0.12941   0.12508  -0.0703   0.0242   1.0000
<< Back to davissm (davissm-il)

Polar data table (+)

Polar graphs


<< Back to davissm (davissm-il)