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LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LDS-2 AIRFOIL (lds2-il)
Reynolds number: 100,000
Max Cl/Cd: 52.7 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lds2-il-100000.txt
Download as CSV file: xf-lds2-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4224   0.09343   0.08842  -0.0362   1.0000   0.1407
  -9.000  -0.4181   0.09066   0.08569  -0.0358   1.0000   0.1471
  -8.750  -0.4799   0.08630   0.08157  -0.0437   1.0000   0.1517
  -8.500  -0.4285   0.08390   0.07909  -0.0368   1.0000   0.1581
  -8.250  -0.4478   0.08080   0.07612  -0.0380   1.0000   0.1648
  -8.000  -0.5172   0.07744   0.07292  -0.0404   1.0000   0.1670
  -7.750  -0.4727   0.07511   0.07066  -0.0354   1.0000   0.1735
  -7.500  -0.4978   0.07269   0.06834  -0.0337   1.0000   0.1790
  -7.250  -0.5753   0.07137   0.06690  -0.0315   1.0000   0.1828
  -7.000  -0.5370   0.06844   0.06422  -0.0273   1.0000   0.1887
  -6.750  -0.5997   0.06737   0.06284  -0.0257   1.0000   0.1989
  -6.500  -0.5685   0.06421   0.06003  -0.0217   1.0000   0.2035
  -5.750  -0.5929   0.04136   0.03468  -0.0217   1.0000   0.0897
  -5.500  -0.5659   0.03721   0.02942  -0.0218   0.9956   0.0796
  -5.250  -0.5318   0.03464   0.02648  -0.0234   0.9900   0.0783
  -5.000  -0.4970   0.03172   0.02325  -0.0252   0.9852   0.0769
  -4.750  -0.4642   0.02963   0.02078  -0.0262   0.9794   0.0767
  -4.500  -0.4258   0.02844   0.01914  -0.0281   0.9740   0.0791
  -4.250  -0.3948   0.02641   0.01711  -0.0291   0.9682   0.0822
  -4.000  -0.3574   0.02519   0.01583  -0.0309   0.9630   0.0855
  -3.750  -0.3245   0.02437   0.01490  -0.0318   0.9570   0.0909
  -3.500  -0.2927   0.02326   0.01394  -0.0328   0.9509   0.0987
  -3.250  -0.2554   0.02239   0.01313  -0.0346   0.9461   0.1096
  -3.000  -0.2340   0.02169   0.01253  -0.0337   0.9377   0.1273
  -2.750  -0.2074   0.01967   0.01170  -0.0343   0.9327   0.3007
  -2.500  -0.1988   0.01887   0.01220  -0.0299   0.9247   0.6178
  -2.250  -0.1711   0.01886   0.01239  -0.0290   0.9183   0.6973
  -2.000  -0.1420   0.01893   0.01261  -0.0283   0.9128   0.7615
  -1.750  -0.1201   0.01911   0.01301  -0.0256   0.9056   0.8356
  -1.500  -0.0656   0.01967   0.01362  -0.0283   0.9027   0.9129
  -1.250   0.0120   0.01996   0.01369  -0.0376   0.9009   0.9368
  -1.000   0.0937   0.02009   0.01361  -0.0481   0.8997   0.9546
  -0.750   0.1682   0.02011   0.01347  -0.0576   0.8965   0.9729
  -0.500   0.2447   0.01994   0.01318  -0.0677   0.8929   0.9885
  -0.250   0.3118   0.01961   0.01275  -0.0763   0.8890   1.0000
   0.000   0.3463   0.01936   0.01241  -0.0786   0.8832   1.0000
   0.250   0.3435   0.01967   0.01266  -0.0743   0.8704   1.0000
   0.500   0.3540   0.01997   0.01289  -0.0720   0.8606   1.0000
   0.750   0.3826   0.02002   0.01288  -0.0724   0.8535   1.0000
   1.000   0.3933   0.02045   0.01326  -0.0699   0.8436   1.0000
   1.250   0.4274   0.02041   0.01319  -0.0709   0.8369   1.0000
   1.500   0.4430   0.02070   0.01345  -0.0687   0.8256   1.0000
   1.750   0.4882   0.02023   0.01296  -0.0709   0.8190   1.0000
   2.000   0.5031   0.02048   0.01320  -0.0684   0.8065   1.0000
   2.250   0.5285   0.02048   0.01319  -0.0675   0.7965   1.0000
   2.500   0.5662   0.01992   0.01263  -0.0679   0.7870   1.0000
   2.750   0.5874   0.01984   0.01256  -0.0660   0.7736   1.0000
   3.000   0.6115   0.01968   0.01241  -0.0644   0.7612   1.0000
   3.250   0.6415   0.01929   0.01202  -0.0636   0.7503   1.0000
   3.500   0.6712   0.01884   0.01158  -0.0627   0.7383   1.0000
   3.750   0.6942   0.01861   0.01137  -0.0608   0.7236   1.0000
   4.000   0.7185   0.01830   0.01107  -0.0591   0.7083   1.0000
   4.250   0.7432   0.01798   0.01078  -0.0574   0.6924   1.0000
   4.500   0.7685   0.01762   0.01042  -0.0558   0.6754   1.0000
   4.750   0.7925   0.01730   0.01010  -0.0540   0.6566   1.0000
   5.000   0.8121   0.01712   0.00998  -0.0516   0.6338   1.0000
   5.250   0.8351   0.01681   0.00964  -0.0496   0.6090   1.0000
   5.500   0.8538   0.01665   0.00946  -0.0471   0.5774   1.0000
   5.750   0.8699   0.01660   0.00937  -0.0441   0.5349   1.0000
   6.000   0.8827   0.01675   0.00932  -0.0407   0.4729   1.0000
   6.250   0.8897   0.01746   0.00947  -0.0365   0.3915   1.0000
   6.500   0.8941   0.01866   0.01010  -0.0324   0.3216   1.0000
   6.750   0.9017   0.01996   0.01096  -0.0291   0.2754   1.0000
   7.000   0.9132   0.02113   0.01185  -0.0266   0.2428   1.0000
   7.250   0.9276   0.02228   0.01274  -0.0245   0.2192   1.0000
   7.500   0.9448   0.02337   0.01371  -0.0229   0.1998   1.0000
   7.750   0.9637   0.02448   0.01471  -0.0216   0.1844   1.0000
   8.000   0.9849   0.02566   0.01581  -0.0207   0.1718   1.0000
   8.250   1.0088   0.02695   0.01693  -0.0204   0.1609   1.0000
   8.500   1.0285   0.02800   0.01813  -0.0191   0.1515   1.0000
   8.750   1.0545   0.02950   0.01955  -0.0191   0.1436   1.0000
   9.000   1.0750   0.03068   0.02089  -0.0181   0.1365   1.0000
   9.250   1.1009   0.03235   0.02248  -0.0182   0.1300   1.0000
   9.500   1.1196   0.03375   0.02415  -0.0169   0.1247   1.0000
   9.750   1.1417   0.03523   0.02567  -0.0163   0.1198   1.0000
  10.000   1.1618   0.03729   0.02788  -0.0156   0.1154   1.0000
  10.250   1.1750   0.03898   0.02990  -0.0137   0.1115   1.0000
  10.500   1.1919   0.04078   0.03187  -0.0125   0.1080   1.0000
  10.750   1.2146   0.04315   0.03418  -0.0126   0.1043   1.0000
  11.000   1.2174   0.04545   0.03693  -0.0096   0.1020   1.0000
  11.250   1.2175   0.04783   0.03973  -0.0065   0.1000   1.0000
  11.500   1.2165   0.05047   0.04272  -0.0036   0.0983   1.0000
  11.750   1.2140   0.05307   0.04561  -0.0007   0.0966   1.0000
  12.000   1.2160   0.05529   0.04798   0.0016   0.0945   1.0000
  12.250   1.2381   0.05789   0.05049   0.0012   0.0914   1.0000
  12.500   1.2270   0.06181   0.05463   0.0041   0.0906   1.0000
  12.750   1.2053   0.06484   0.05794   0.0080   0.0904   1.0000
  13.000   1.1811   0.06838   0.06174   0.0110   0.0903   1.0000
  13.250   1.1553   0.07251   0.06609   0.0129   0.0904   1.0000
  13.500   1.1301   0.07730   0.07109   0.0137   0.0905   1.0000
  13.750   1.1018   0.08290   0.07687   0.0135   0.0907   1.0000
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