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davissm (davissm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: davissm (davissm-il)
Reynolds number: 500,000
Max Cl/Cd: 118.79 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davissm-il-500000-n5.txt
Download as CSV file: xf-davissm-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3270   0.12122   0.11883  -0.0328   1.0000   0.0103
  -9.750  -0.3233   0.11841   0.11604  -0.0334   1.0000   0.0104
  -9.500  -0.3206   0.11571   0.11337  -0.0337   1.0000   0.0104
  -9.250  -0.3117   0.11229   0.10996  -0.0361   0.9987   0.0104
  -9.000  -0.3019   0.10876   0.10643  -0.0385   0.9863   0.0105
  -8.500  -0.2753   0.10123   0.09889  -0.0461   0.9739   0.0105
  -8.250  -0.2609   0.09721   0.09486  -0.0484   0.9710   0.0108
  -8.000  -0.2427   0.09409   0.09174  -0.0520   0.9682   0.0113
  -7.750  -0.2234   0.09051   0.08814  -0.0566   0.9644   0.0118
  -7.500  -0.2041   0.08677   0.08438  -0.0616   0.9586   0.0120
  -7.250  -0.1814   0.08285   0.08044  -0.0675   0.9534   0.0122
  -7.000  -0.1570   0.07693   0.07447  -0.0765   0.9444   0.0104
  -6.500  -0.1168   0.07011   0.06757  -0.0851   0.9297   0.0100
  -6.250  -0.0932   0.06620   0.06361  -0.0907   0.9227   0.0100
  -6.000  -0.0673   0.06164   0.05899  -0.0975   0.9151   0.0102
  -5.750  -0.0344   0.05623   0.05350  -0.1064   0.9088   0.0106
  -5.500  -0.0097   0.05361   0.05084  -0.1101   0.9024   0.0109
  -5.250   0.0162   0.05171   0.04889  -0.1132   0.8967   0.0117
  -5.000   0.0482   0.04845   0.04556  -0.1187   0.8911   0.0127
  -4.750   0.0855   0.04408   0.04109  -0.1258   0.8854   0.0127
  -4.500   0.1273   0.03925   0.03609  -0.1336   0.8807   0.0128
  -4.250   0.1779   0.03267   0.02925  -0.1433   0.8757   0.0137
  -4.000   0.2268   0.02606   0.02226  -0.1512   0.8710   0.0148
  -3.750   0.2559   0.02514   0.02124  -0.1525   0.8659   0.0156
  -3.500   0.2937   0.02143   0.01720  -0.1559   0.8605   0.0165
  -3.250   0.3355   0.01533   0.01024  -0.1597   0.8559   0.0183
  -3.000   0.3662   0.01368   0.00816  -0.1605   0.8508   0.0194
  -2.750   0.3956   0.01237   0.00657  -0.1611   0.8446   0.0205
  -2.500   0.4240   0.01191   0.00597  -0.1613   0.8386   0.0213
  -2.250   0.4523   0.01145   0.00540  -0.1615   0.8319   0.0222
  -2.000   0.4806   0.01099   0.00480  -0.1615   0.8249   0.0232
  -1.750   0.5087   0.01058   0.00428  -0.1616   0.8181   0.0243
  -1.500   0.5367   0.01036   0.00397  -0.1616   0.8109   0.0256
  -1.250   0.5647   0.01017   0.00372  -0.1616   0.8038   0.0264
  -1.000   0.5927   0.00965   0.00312  -0.1617   0.7963   0.0282
  -0.750   0.6206   0.00947   0.00292  -0.1617   0.7880   0.0298
  -0.500   0.6482   0.00934   0.00275  -0.1617   0.7793   0.0315
  -0.250   0.6759   0.00925   0.00263  -0.1616   0.7698   0.0339
   0.000   0.7035   0.00920   0.00254  -0.1616   0.7605   0.0359
   0.250   0.7312   0.00907   0.00237  -0.1615   0.7512   0.0389
   0.500   0.7587   0.00902   0.00230  -0.1615   0.7407   0.0426
   0.750   0.7861   0.00901   0.00226  -0.1614   0.7300   0.0472
   1.000   0.8134   0.00900   0.00225  -0.1612   0.7185   0.0579
   1.250   0.8405   0.00898   0.00227  -0.1611   0.7064   0.0839
   1.500   0.8675   0.00883   0.00237  -0.1611   0.6937   0.2197
   1.750   0.8938   0.00863   0.00253  -0.1610   0.6762   0.4174
   2.250   0.9444   0.00795   0.00266  -0.1601   0.6255   1.0000
   2.500   0.9702   0.00817   0.00277  -0.1597   0.6027   1.0000
   2.750   0.9955   0.00844   0.00290  -0.1592   0.5760   1.0000
   3.000   1.0202   0.00875   0.00308  -0.1586   0.5449   1.0000
   3.250   1.0450   0.00907   0.00326  -0.1580   0.5154   1.0000
   3.500   1.0697   0.00940   0.00346  -0.1574   0.4863   1.0000
   3.750   1.0928   0.00989   0.00373  -0.1566   0.4412   1.0000
   4.000   1.1149   0.01049   0.00406  -0.1556   0.3870   1.0000
   4.250   1.1354   0.01128   0.00450  -0.1545   0.3186   1.0000
   4.500   1.1528   0.01243   0.00511  -0.1528   0.2189   1.0000
   4.750   1.1654   0.01415   0.00609  -0.1504   0.0778   1.0000
   5.000   1.1891   0.01455   0.00647  -0.1497   0.0659   1.0000
   5.250   1.2128   0.01496   0.00685  -0.1491   0.0567   1.0000
   5.500   1.2361   0.01537   0.00725  -0.1483   0.0482   1.0000
   5.750   1.2597   0.01574   0.00762  -0.1476   0.0413   1.0000
   6.000   1.2825   0.01618   0.00803  -0.1468   0.0345   1.0000
   6.250   1.3051   0.01660   0.00846  -0.1460   0.0292   1.0000
   6.500   1.3271   0.01708   0.00896  -0.1450   0.0248   1.0000
   6.750   1.3487   0.01757   0.00946  -0.1440   0.0215   1.0000
   7.000   1.3688   0.01817   0.01007  -0.1427   0.0183   1.0000
   7.250   1.3896   0.01866   0.01063  -0.1415   0.0167   1.0000
   7.500   1.4093   0.01923   0.01124  -0.1401   0.0153   1.0000
   7.750   1.4275   0.01988   0.01195  -0.1385   0.0140   1.0000
   8.000   1.4422   0.02079   0.01293  -0.1361   0.0128   1.0000
   8.250   1.4590   0.02146   0.01368  -0.1343   0.0123   1.0000
   8.500   1.4744   0.02219   0.01450  -0.1321   0.0118   1.0000
   8.750   1.4891   0.02293   0.01532  -0.1299   0.0111   1.0000
   9.000   1.5027   0.02367   0.01613  -0.1275   0.0105   1.0000
   9.250   1.5140   0.02444   0.01698  -0.1247   0.0099   1.0000
   9.500   1.5227   0.02542   0.01804  -0.1216   0.0095   1.0000
   9.750   1.5285   0.02667   0.01937  -0.1181   0.0091   1.0000
  10.000   1.5325   0.02815   0.02097  -0.1144   0.0087   1.0000
  10.250   1.5415   0.02931   0.02224  -0.1117   0.0085   1.0000
  10.500   1.5498   0.03057   0.02363  -0.1091   0.0083   1.0000
  10.750   1.5578   0.03191   0.02510  -0.1066   0.0080   1.0000
  11.000   1.5659   0.03327   0.02657  -0.1042   0.0076   1.0000
  11.250   1.5749   0.03457   0.02799  -0.1020   0.0073   1.0000
  11.500   1.5834   0.03593   0.02945  -0.1000   0.0069   1.0000
  11.750   1.5905   0.03746   0.03108  -0.0978   0.0067   1.0000
  12.000   1.5964   0.03913   0.03286  -0.0957   0.0065   1.0000
  12.250   1.6012   0.04096   0.03480  -0.0936   0.0063   1.0000
  12.500   1.6032   0.04313   0.03710  -0.0914   0.0061   1.0000
  12.750   1.6008   0.04585   0.03997  -0.0889   0.0059   1.0000
  13.000   1.5998   0.04851   0.04281  -0.0867   0.0058   1.0000
  13.250   1.6011   0.05096   0.04543  -0.0849   0.0057   1.0000
  13.500   1.6006   0.05365   0.04831  -0.0832   0.0056   1.0000
  13.750   1.5988   0.05656   0.05143  -0.0816   0.0055   1.0000
  14.000   1.5954   0.05976   0.05483  -0.0802   0.0053   1.0000
  14.250   1.5897   0.06334   0.05862  -0.0789   0.0052   1.0000
  14.500   1.5826   0.06722   0.06270  -0.0780   0.0051   1.0000
  14.750   1.5734   0.07155   0.06725  -0.0774   0.0051   1.0000
  15.000   1.5634   0.07618   0.07209  -0.0772   0.0050   1.0000
  15.250   1.5517   0.08126   0.07738  -0.0774   0.0049   1.0000
  15.500   1.5382   0.08684   0.08317  -0.0782   0.0048   1.0000
  15.750   1.5238   0.09285   0.08938  -0.0795   0.0048   1.0000
  16.000   1.5068   0.09965   0.09639  -0.0816   0.0047   1.0000
  16.250   1.4894   0.10684   0.10380  -0.0843   0.0047   1.0000
  16.500   1.4699   0.11482   0.11198  -0.0877   0.0047   1.0000
  16.750   1.4465   0.12415   0.12152  -0.0924   0.0047   1.0000
  17.000   1.4239   0.13395   0.13152  -0.0978   0.0047   1.0000
  17.250   1.3970   0.14565   0.14343  -0.1049   0.0048   1.0000
  17.500   1.3655   0.15986   0.15783  -0.1140   0.0049   1.0000
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