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LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: LDS-2 AIRFOIL (lds2-il)
Reynolds number: 500,000
Max Cl/Cd: 77.58 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lds2-il-500000-n5.txt
Download as CSV file: xf-lds2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LDS-2 AIRFOIL                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7631   0.05724   0.05424  -0.0608   1.0000   0.0110
 -12.750  -0.7968   0.04829   0.04506  -0.0679   1.0000   0.0110
 -12.500  -0.8238   0.04210   0.03861  -0.0715   1.0000   0.0110
 -12.250  -0.8420   0.03829   0.03459  -0.0718   1.0000   0.0110
 -12.000  -0.8559   0.03563   0.03170  -0.0698   1.0000   0.0111
 -11.750  -0.8704   0.03354   0.02941  -0.0658   1.0000   0.0112
 -11.500  -0.8794   0.03163   0.02730  -0.0618   1.0000   0.0113
 -11.250  -0.8808   0.02991   0.02542  -0.0586   1.0000   0.0114
 -11.000  -0.8773   0.02863   0.02403  -0.0557   1.0000   0.0116
 -10.500  -0.8420   0.02640   0.02161  -0.0547   0.9937   0.0119
 -10.250  -0.8168   0.02522   0.02031  -0.0555   0.9872   0.0121
 -10.000  -0.7921   0.02379   0.01868  -0.0561   0.9804   0.0123
  -9.750  -0.7637   0.02268   0.01742  -0.0573   0.9747   0.0126
  -9.500  -0.7360   0.02144   0.01601  -0.0582   0.9677   0.0130
  -9.250  -0.7061   0.02020   0.01459  -0.0595   0.9612   0.0133
  -9.000  -0.6770   0.01917   0.01338  -0.0605   0.9524   0.0137
  -8.750  -0.6460   0.01823   0.01228  -0.0617   0.9442   0.0140
  -8.500  -0.6174   0.01729   0.01122  -0.0624   0.9337   0.0144
  -8.250  -0.5902   0.01659   0.01044  -0.0627   0.9224   0.0147
  -8.000  -0.5636   0.01610   0.00988  -0.0627   0.9112   0.0152
  -7.750  -0.5386   0.01561   0.00930  -0.0624   0.8998   0.0156
  -7.500  -0.5143   0.01521   0.00882  -0.0618   0.8888   0.0163
  -7.250  -0.4906   0.01473   0.00823  -0.0611   0.8784   0.0168
  -7.000  -0.4669   0.01430   0.00769  -0.0604   0.8684   0.0173
  -6.750  -0.4441   0.01379   0.00710  -0.0595   0.8589   0.0177
  -6.500  -0.4208   0.01334   0.00660  -0.0587   0.8498   0.0183
  -6.250  -0.3967   0.01299   0.00619  -0.0580   0.8406   0.0189
  -6.000  -0.3723   0.01268   0.00582  -0.0574   0.8326   0.0197
  -5.750  -0.3476   0.01238   0.00545  -0.0567   0.8241   0.0207
  -5.500  -0.3227   0.01211   0.00511  -0.0561   0.8164   0.0215
  -5.250  -0.2985   0.01174   0.00471  -0.0555   0.8081   0.0226
  -5.000  -0.2734   0.01148   0.00440  -0.0549   0.8009   0.0236
  -4.750  -0.2479   0.01123   0.00411  -0.0544   0.7935   0.0249
  -4.500  -0.2224   0.01100   0.00381  -0.0539   0.7866   0.0263
  -4.250  -0.1970   0.01074   0.00355  -0.0534   0.7794   0.0283
  -4.000  -0.1711   0.01056   0.00332  -0.0530   0.7721   0.0307
  -3.750  -0.1452   0.01035   0.00308  -0.0525   0.7654   0.0335
  -3.500  -0.1190   0.01017   0.00288  -0.0521   0.7586   0.0370
  -3.250  -0.0930   0.00999   0.00269  -0.0517   0.7526   0.0426
  -3.000  -0.0667   0.00980   0.00252  -0.0514   0.7461   0.0520
  -2.750  -0.0409   0.00959   0.00235  -0.0509   0.7395   0.0706
  -2.500  -0.0159   0.00925   0.00218  -0.0504   0.7332   0.1184
  -2.250   0.0073   0.00872   0.00197  -0.0498   0.7264   0.2161
  -2.000   0.0297   0.00816   0.00182  -0.0489   0.7201   0.3392
  -1.750   0.0543   0.00787   0.00176  -0.0483   0.7125   0.4109
  -1.500   0.0796   0.00771   0.00171  -0.0478   0.7053   0.4611
  -1.250   0.1048   0.00753   0.00171  -0.0472   0.6981   0.5175
  -1.000   0.1294   0.00736   0.00171  -0.0465   0.6919   0.5720
  -0.750   0.1559   0.00730   0.00169  -0.0461   0.6866   0.5970
  -0.500   0.1828   0.00725   0.00167  -0.0458   0.6805   0.6133
  -0.250   0.2094   0.00723   0.00165  -0.0454   0.6740   0.6295
   0.000   0.2362   0.00720   0.00165  -0.0451   0.6663   0.6450
   0.250   0.2626   0.00718   0.00164  -0.0447   0.6590   0.6622
   0.750   0.3149   0.00709   0.00167  -0.0437   0.6444   0.7068
   1.000   0.3400   0.00705   0.00168  -0.0430   0.6320   0.7360
   1.250   0.3644   0.00700   0.00171  -0.0421   0.6172   0.7704
   1.500   0.3891   0.00695   0.00176  -0.0412   0.6056   0.8092
   2.000   0.4433   0.00695   0.00190  -0.0405   0.5800   0.8863
   2.250   0.4763   0.00705   0.00199  -0.0415   0.5620   0.9157
   2.500   0.5132   0.00718   0.00208  -0.0434   0.5415   0.9362
   2.750   0.5490   0.00735   0.00217  -0.0451   0.5185   0.9504
   3.000   0.5825   0.00757   0.00228  -0.0464   0.4877   0.9620
   3.250   0.6144   0.00792   0.00242  -0.0475   0.4403   0.9713
   3.500   0.6449   0.00838   0.00264  -0.0483   0.3894   0.9790
   3.750   0.6730   0.00895   0.00291  -0.0488   0.3248   0.9867
   4.000   0.7033   0.00944   0.00318  -0.0497   0.2821   0.9932
   4.250   0.7351   0.00989   0.00345  -0.0510   0.2422   0.9985
   4.500   0.7593   0.01031   0.00370  -0.0506   0.2097   1.0000
   4.750   0.7783   0.01065   0.00393  -0.0490   0.1884   1.0000
   5.000   0.7976   0.01097   0.00417  -0.0474   0.1689   1.0000
   5.250   0.8171   0.01130   0.00441  -0.0459   0.1522   1.0000
   5.500   0.8368   0.01161   0.00466  -0.0444   0.1385   1.0000
   5.750   0.8567   0.01192   0.00491  -0.0430   0.1264   1.0000
   6.000   0.8763   0.01225   0.00518  -0.0415   0.1147   1.0000
   6.250   0.8960   0.01257   0.00546  -0.0401   0.1054   1.0000
   6.500   0.9161   0.01287   0.00574  -0.0387   0.0983   1.0000
   6.750   0.9353   0.01322   0.00605  -0.0372   0.0911   1.0000
   7.000   0.9554   0.01351   0.00634  -0.0358   0.0854   1.0000
   7.250   0.9745   0.01387   0.00667  -0.0343   0.0797   1.0000
   7.500   0.9942   0.01418   0.00699  -0.0329   0.0760   1.0000
   7.750   1.0136   0.01451   0.00734  -0.0315   0.0721   1.0000
   8.000   1.0317   0.01491   0.00772  -0.0298   0.0679   1.0000
   8.250   1.0506   0.01525   0.00808  -0.0284   0.0651   1.0000
   8.500   1.0690   0.01561   0.00846  -0.0268   0.0621   1.0000
   8.750   1.0859   0.01602   0.00887  -0.0251   0.0592   1.0000
   9.000   1.1003   0.01647   0.00932  -0.0228   0.0566   1.0000
   9.250   1.1162   0.01683   0.00973  -0.0209   0.0549   1.0000
   9.500   1.1316   0.01724   0.01018  -0.0189   0.0526   1.0000
   9.750   1.1463   0.01771   0.01067  -0.0169   0.0505   1.0000
  10.000   1.1599   0.01827   0.01123  -0.0149   0.0484   1.0000
  10.250   1.1748   0.01878   0.01179  -0.0131   0.0469   1.0000
  10.500   1.1900   0.01930   0.01237  -0.0114   0.0456   1.0000
  10.750   1.2046   0.01987   0.01299  -0.0097   0.0441   1.0000
  11.000   1.2184   0.02051   0.01366  -0.0081   0.0425   1.0000
  11.250   1.2313   0.02123   0.01441  -0.0064   0.0410   1.0000
  11.500   1.2431   0.02205   0.01526  -0.0047   0.0397   1.0000
  11.750   1.2574   0.02273   0.01602  -0.0033   0.0385   1.0000
  12.000   1.2707   0.02350   0.01686  -0.0019   0.0374   1.0000
  12.250   1.2832   0.02434   0.01776  -0.0005   0.0363   1.0000
  12.500   1.2947   0.02528   0.01874   0.0008   0.0351   1.0000
  12.750   1.3051   0.02634   0.01984   0.0022   0.0341   1.0000
  13.000   1.3152   0.02745   0.02100   0.0034   0.0329   1.0000
  13.250   1.3261   0.02853   0.02217   0.0046   0.0322   1.0000
  13.500   1.3365   0.02967   0.02340   0.0057   0.0315   1.0000
  13.750   1.3467   0.03086   0.02466   0.0066   0.0304   1.0000
  14.000   1.3561   0.03214   0.02600   0.0076   0.0294   1.0000
  14.250   1.3632   0.03366   0.02759   0.0085   0.0288   1.0000
  14.500   1.3682   0.03540   0.02937   0.0094   0.0279   1.0000
  14.750   1.3755   0.03698   0.03105   0.0101   0.0272   1.0000
  15.000   1.3829   0.03858   0.03276   0.0107   0.0264   1.0000
  15.250   1.3881   0.04043   0.03471   0.0113   0.0259   1.0000
  15.500   1.3937   0.04229   0.03666   0.0117   0.0251   1.0000
  15.750   1.3983   0.04430   0.03873   0.0120   0.0243   1.0000
  16.000   1.4007   0.04660   0.04110   0.0122   0.0237   1.0000
  16.250   1.4001   0.04931   0.04388   0.0122   0.0229   1.0000
  16.500   1.4016   0.05186   0.04655   0.0122   0.0225   1.0000
  16.750   1.4025   0.05457   0.04939   0.0119   0.0221   1.0000
  17.000   1.4033   0.05738   0.05231   0.0115   0.0215   1.0000
  17.250   1.4018   0.06054   0.05558   0.0110   0.0210   1.0000
  17.500   1.3997   0.06388   0.05902   0.0102   0.0203   1.0000
  17.750   1.3955   0.06762   0.06287   0.0091   0.0199   1.0000
  18.000   1.3895   0.07175   0.06710   0.0078   0.0196   1.0000
  18.250   1.3808   0.07637   0.07182   0.0061   0.0192   1.0000
  18.500   1.3696   0.08157   0.07713   0.0041   0.0189   1.0000
  18.750   1.3581   0.08697   0.08266   0.0018   0.0186   1.0000
  19.000   1.3458   0.09263   0.08847  -0.0008   0.0184   1.0000
  19.250   1.3340   0.09835   0.09433  -0.0034   0.0180   1.0000
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