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

DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.32 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-corrected-il-1000000.txt
Download as CSV file: xf-davis-corrected-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAVIS BASIC B-24 WING AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -1.0618   0.09629   0.09319  -0.0302   1.0000   0.0179
 -18.750  -1.0829   0.08923   0.08603  -0.0341   1.0000   0.0180
 -18.500  -1.1058   0.08201   0.07870  -0.0381   1.0000   0.0181
 -18.250  -1.1260   0.07537   0.07194  -0.0417   1.0000   0.0180
 -18.000  -1.1463   0.06876   0.06521  -0.0454   1.0000   0.0182
 -17.750  -1.1635   0.06274   0.05907  -0.0487   1.0000   0.0182
 -17.500  -1.1770   0.05730   0.05352  -0.0518   1.0000   0.0184
 -17.250  -1.1890   0.05222   0.04832  -0.0546   1.0000   0.0185
 -17.000  -1.1962   0.04789   0.04387  -0.0570   1.0000   0.0187
 -16.750  -1.2016   0.04396   0.03983  -0.0590   1.0000   0.0188
 -16.500  -1.2031   0.04067   0.03644  -0.0605   1.0000   0.0190
 -16.250  -1.2030   0.03774   0.03341  -0.0616   1.0000   0.0192
 -16.000  -1.2013   0.03516   0.03072  -0.0623   1.0000   0.0193
 -15.750  -1.1952   0.03319   0.02866  -0.0626   1.0000   0.0195
 -15.500  -1.2008   0.03034   0.02571  -0.0626   1.0000   0.0198
 -15.250  -1.2013   0.02821   0.02350  -0.0620   1.0000   0.0201
 -15.000  -1.1971   0.02662   0.02186  -0.0610   1.0000   0.0204
 -14.750  -1.1900   0.02537   0.02056  -0.0598   1.0000   0.0207
 -14.500  -1.1802   0.02438   0.01952  -0.0585   1.0000   0.0211
 -14.250  -1.1708   0.02344   0.01852  -0.0569   1.0000   0.0215
 -14.000  -1.1603   0.02262   0.01765  -0.0552   1.0000   0.0219
 -13.750  -1.1494   0.02188   0.01685  -0.0534   1.0000   0.0222
 -13.500  -1.1379   0.02121   0.01612  -0.0514   1.0000   0.0225
 -13.250  -1.1246   0.02067   0.01552  -0.0494   1.0000   0.0228
 -13.000  -1.1224   0.01972   0.01452  -0.0459   1.0000   0.0233
 -12.750  -1.1156   0.01907   0.01384  -0.0426   1.0000   0.0238
 -12.500  -1.1052   0.01858   0.01333  -0.0398   1.0000   0.0243
 -12.250  -1.0908   0.01811   0.01283  -0.0376   1.0000   0.0248
 -12.000  -1.0753   0.01766   0.01235  -0.0356   1.0000   0.0254
 -11.750  -1.0584   0.01728   0.01194  -0.0337   1.0000   0.0260
 -11.500  -1.0411   0.01692   0.01153  -0.0319   1.0000   0.0264
 -11.250  -1.0288   0.01628   0.01087  -0.0293   1.0000   0.0274
 -11.000  -1.0030   0.01574   0.01034  -0.0293   0.9896   0.0283
 -10.750  -0.9600   0.01522   0.00979  -0.0328   0.9742   0.0294
 -10.500  -0.9044   0.01468   0.00918  -0.0388   0.9495   0.0306
 -10.250  -0.8678   0.01407   0.00846  -0.0410   0.8995   0.0322
 -10.000  -0.8478   0.01389   0.00811  -0.0394   0.8551   0.0333
  -9.750  -0.8271   0.01372   0.00780  -0.0380   0.8230   0.0344
  -9.500  -0.8068   0.01346   0.00741  -0.0365   0.7970   0.0356
  -9.250  -0.7861   0.01315   0.00703  -0.0352   0.7754   0.0372
  -9.000  -0.7634   0.01294   0.00673  -0.0341   0.7561   0.0387
  -8.750  -0.7398   0.01277   0.00646  -0.0332   0.7384   0.0400
  -8.250  -0.6939   0.01221   0.00582  -0.0313   0.7082   0.0444
  -8.000  -0.6699   0.01199   0.00553  -0.0305   0.6948   0.0466
  -7.750  -0.6463   0.01173   0.00524  -0.0297   0.6818   0.0494
  -7.500  -0.6212   0.01157   0.00502  -0.0290   0.6694   0.0517
  -7.250  -0.5971   0.01130   0.00474  -0.0283   0.6587   0.0554
  -6.750  -0.5472   0.01090   0.00428  -0.0270   0.6375   0.0632
  -6.500  -0.5216   0.01076   0.00409  -0.0265   0.6274   0.0670
  -6.250  -0.4966   0.01051   0.00386  -0.0258   0.6185   0.0732
  -6.000  -0.4712   0.01035   0.00367  -0.0253   0.6095   0.0792
  -5.750  -0.4452   0.01017   0.00349  -0.0248   0.6011   0.0857
  -5.500  -0.4200   0.00999   0.00331  -0.0242   0.5921   0.0946
  -5.250  -0.3940   0.00979   0.00314  -0.0238   0.5846   0.1041
  -5.000  -0.3682   0.00964   0.00299  -0.0233   0.5767   0.1146
  -4.750  -0.3422   0.00946   0.00284  -0.0228   0.5696   0.1268
  -4.500  -0.3162   0.00929   0.00270  -0.0224   0.5621   0.1407
  -4.250  -0.2904   0.00914   0.00257  -0.0219   0.5548   0.1564
  -4.000  -0.2643   0.00895   0.00245  -0.0215   0.5483   0.1740
  -3.750  -0.2384   0.00879   0.00233  -0.0210   0.5416   0.1940
  -3.500  -0.2123   0.00864   0.00223  -0.0206   0.5355   0.2157
  -3.250  -0.1861   0.00846   0.00213  -0.0202   0.5292   0.2396
  -3.000  -0.1603   0.00832   0.00204  -0.0197   0.5225   0.2664
  -2.750  -0.1342   0.00815   0.00196  -0.0193   0.5169   0.2938
  -2.500  -0.1079   0.00800   0.00189  -0.0189   0.5113   0.3234
  -2.250  -0.0822   0.00785   0.00183  -0.0184   0.5054   0.3553
  -2.000  -0.0561   0.00771   0.00177  -0.0180   0.5001   0.3877
  -1.750  -0.0300   0.00755   0.00172  -0.0175   0.4946   0.4219
  -1.500  -0.0041   0.00744   0.00168  -0.0171   0.4890   0.4555
  -1.250   0.0218   0.00733   0.00166  -0.0166   0.4838   0.4898
  -1.000   0.0481   0.00720   0.00163  -0.0161   0.4793   0.5248
  -0.750   0.0740   0.00709   0.00162  -0.0156   0.4741   0.5599
  -0.500   0.0995   0.00702   0.00161  -0.0151   0.4686   0.5940
  -0.250   0.1255   0.00692   0.00162  -0.0145   0.4643   0.6270
   0.000   0.1513   0.00683   0.00162  -0.0140   0.4597   0.6603
   0.250   0.1771   0.00677   0.00164  -0.0134   0.4550   0.6914
   0.500   0.2024   0.00675   0.00167  -0.0127   0.4499   0.7214
   0.750   0.2286   0.00667   0.00169  -0.0122   0.4463   0.7498
   1.000   0.2547   0.00663   0.00172  -0.0117   0.4416   0.7776
   1.250   0.2806   0.00663   0.00177  -0.0111   0.4369   0.8026
   1.500   0.3064   0.00664   0.00183  -0.0105   0.4324   0.8270
   1.750   0.3335   0.00662   0.00188  -0.0101   0.4290   0.8491
   2.000   0.3605   0.00663   0.00194  -0.0097   0.4247   0.8697
   2.250   0.3877   0.00668   0.00201  -0.0094   0.4201   0.8883
   2.500   0.4155   0.00675   0.00210  -0.0092   0.4155   0.9052
   2.750   0.4452   0.00679   0.00218  -0.0095   0.4122   0.9194
   3.000   0.4756   0.00686   0.00226  -0.0098   0.4082   0.9318
   3.250   0.5049   0.00696   0.00235  -0.0100   0.4039   0.9434
   3.500   0.5389   0.00711   0.00248  -0.0113   0.3990   0.9509
   3.750   0.5707   0.00719   0.00257  -0.0120   0.3957   0.9588
   4.000   0.6070   0.00730   0.00269  -0.0137   0.3918   0.9630
   4.250   0.6389   0.00744   0.00280  -0.0145   0.3876   0.9690
   4.500   0.6742   0.00762   0.00294  -0.0161   0.3825   0.9719
   4.750   0.7125   0.00772   0.00306  -0.0183   0.3793   0.9736
   5.000   0.7493   0.00783   0.00318  -0.0202   0.3755   0.9758
   5.250   0.7840   0.00797   0.00331  -0.0217   0.3713   0.9788
   5.500   0.8149   0.00818   0.00347  -0.0224   0.3663   0.9828
   5.750   0.8528   0.00825   0.00358  -0.0245   0.3633   0.9841
   6.000   0.8898   0.00835   0.00369  -0.0265   0.3589   0.9857
   6.250   0.9249   0.00853   0.00381  -0.0282   0.3505   0.9878
   6.500   0.9601   0.00860   0.00390  -0.0298   0.3421   0.9901
   6.750   0.9925   0.00880   0.00405  -0.0310   0.3334   0.9928
   7.000   1.0283   0.00889   0.00415  -0.0328   0.3273   0.9943
   7.250   1.0637   0.00905   0.00429  -0.0346   0.3195   0.9960
   7.500   1.0990   0.00916   0.00441  -0.0363   0.3131   0.9978
   7.750   1.1335   0.00934   0.00457  -0.0380   0.3047   0.9994
   8.000   1.1608   0.00949   0.00472  -0.0381   0.2974   1.0000
   8.250   1.1801   0.00969   0.00490  -0.0366   0.2891   1.0000
   8.500   1.1998   0.00987   0.00508  -0.0352   0.2806   1.0000
   8.750   1.2178   0.01014   0.00531  -0.0335   0.2702   1.0000
   9.000   1.2350   0.01044   0.00556  -0.0317   0.2568   1.0000
   9.250   1.2510   0.01080   0.00586  -0.0297   0.2414   1.0000
   9.500   1.2650   0.01125   0.00622  -0.0273   0.2210   1.0000
   9.750   1.2743   0.01189   0.00672  -0.0243   0.1950   1.0000
  10.000   1.2792   0.01271   0.00736  -0.0206   0.1645   1.0000
  10.250   1.2801   0.01364   0.00811  -0.0163   0.1349   1.0000
  10.500   1.2825   0.01447   0.00882  -0.0123   0.1153   1.0000
  10.750   1.2819   0.01516   0.00944  -0.0076   0.1016   1.0000
  11.000   1.2811   0.01588   0.01012  -0.0032   0.0904   1.0000
  11.250   1.2833   0.01672   0.01092   0.0002   0.0810   1.0000
  11.500   1.2868   0.01768   0.01186   0.0030   0.0732   1.0000
  11.750   1.2931   0.01866   0.01285   0.0051   0.0671   1.0000
  12.000   1.2982   0.01987   0.01406   0.0069   0.0615   1.0000
  12.250   1.3023   0.02133   0.01552   0.0083   0.0564   1.0000
  12.500   1.3096   0.02271   0.01694   0.0093   0.0528   1.0000
  12.750   1.3129   0.02453   0.01876   0.0101   0.0491   1.0000
  13.000   1.3198   0.02616   0.02044   0.0107   0.0465   1.0000
  13.250   1.3227   0.02822   0.02253   0.0111   0.0439   1.0000
  13.500   1.3261   0.03031   0.02466   0.0114   0.0417   1.0000
  13.750   1.3297   0.03242   0.02682   0.0117   0.0399   1.0000
  14.000   1.3298   0.03490   0.02934   0.0118   0.0381   1.0000
  14.250   1.3291   0.03751   0.03200   0.0119   0.0366   1.0000
  14.500   1.3311   0.03986   0.03442   0.0120   0.0354   1.0000
  14.750   1.3300   0.04256   0.03716   0.0120   0.0341   1.0000
  15.000   1.3265   0.04554   0.04019   0.0119   0.0330   1.0000
  15.250   1.3215   0.04878   0.04349   0.0116   0.0319   1.0000
  15.500   1.3221   0.05150   0.04628   0.0114   0.0311   1.0000
  15.750   1.3213   0.05441   0.04925   0.0110   0.0302   1.0000
  16.000   1.3181   0.05763   0.05252   0.0105   0.0293   1.0000
  16.250   1.3143   0.06097   0.05591   0.0100   0.0285   1.0000
  16.500   1.3070   0.06480   0.05980   0.0093   0.0277   1.0000
  16.750   1.3067   0.06782   0.06289   0.0087   0.0271   1.0000
  17.000   1.3064   0.07087   0.06600   0.0081   0.0264   1.0000
  17.250   1.3035   0.07429   0.06948   0.0074   0.0258   1.0000
  17.500   1.3006   0.07771   0.07294   0.0066   0.0251   1.0000
  17.750   1.2948   0.08154   0.07682   0.0057   0.0245   1.0000
  18.000   1.2856   0.08590   0.08125   0.0046   0.0238   1.0000
<< Back to DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)

Polar data table (+)

Polar graphs


<< Back to DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)