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DF102 (df102-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DF102 (df102-il)
Reynolds number: 100,000
Max Cl/Cd: 49.07 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-df102-il-100000.txt
Download as CSV file: xf-df102-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DF102                                           
  
 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  -0.4091   0.09766   0.09274  -0.0280   1.0000   0.1384
  -9.000  -0.4424   0.09503   0.09027  -0.0337   1.0000   0.1454
  -8.750  -0.4411   0.09050   0.08581  -0.0337   1.0000   0.1470
  -8.500  -0.4264   0.08699   0.08231  -0.0318   1.0000   0.1489
  -8.250  -0.4250   0.08375   0.07911  -0.0315   1.0000   0.1508
  -8.000  -0.5702   0.05932   0.05439  -0.0482   1.0000   0.0765
  -7.750  -0.5666   0.05580   0.05096  -0.0461   1.0000   0.0742
  -7.500  -0.6058   0.04839   0.04252  -0.0428   1.0000   0.0646
  -7.250  -0.6034   0.04418   0.03823  -0.0407   1.0000   0.0633
  -7.000  -0.6008   0.04058   0.03435  -0.0383   1.0000   0.0621
  -6.750  -0.5958   0.03718   0.03055  -0.0359   1.0000   0.0611
  -6.500  -0.5871   0.03411   0.02703  -0.0336   1.0000   0.0607
  -6.250  -0.5747   0.03157   0.02404  -0.0315   1.0000   0.0610
  -6.000  -0.5598   0.02969   0.02170  -0.0295   1.0000   0.0630
  -5.750  -0.5430   0.02801   0.01957  -0.0277   1.0000   0.0651
  -5.500  -0.5244   0.02578   0.01727  -0.0264   1.0000   0.0673
  -5.250  -0.5048   0.02443   0.01584  -0.0250   1.0000   0.0705
  -5.000  -0.4850   0.02348   0.01468  -0.0235   1.0000   0.0759
  -4.750  -0.4656   0.02216   0.01341  -0.0222   1.0000   0.0814
  -4.500  -0.4461   0.02127   0.01244  -0.0208   1.0000   0.0888
  -4.250  -0.4275   0.02037   0.01162  -0.0194   1.0000   0.1017
  -4.000  -0.4091   0.01935   0.01081  -0.0179   1.0000   0.1268
  -3.750  -0.3916   0.01843   0.01046  -0.0166   1.0000   0.2236
  -3.500  -0.3739   0.01847   0.01053  -0.0153   1.0000   0.2730
  -3.250  -0.3454   0.01864   0.01066  -0.0162   0.9965   0.3122
  -3.000  -0.3065   0.01892   0.01101  -0.0190   0.9883   0.3591
  -2.750  -0.2672   0.01900   0.01118  -0.0216   0.9807   0.3992
  -2.500  -0.2285   0.01889   0.01112  -0.0241   0.9724   0.4339
  -2.250  -0.1926   0.01871   0.01111  -0.0259   0.9639   0.4700
  -2.000  -0.1518   0.01854   0.01116  -0.0286   0.9566   0.5195
  -1.750  -0.1204   0.01822   0.01116  -0.0293   0.9470   0.5856
  -1.500  -0.0802   0.01777   0.01135  -0.0309   0.9412   0.7216
  -1.250   0.0383   0.01765   0.01158  -0.0471   0.9446   1.0000
  -1.000   0.0758   0.01781   0.01150  -0.0497   0.9343   1.0000
  -0.750   0.1249   0.01795   0.01144  -0.0541   0.9270   1.0000
  -0.500   0.1567   0.01810   0.01145  -0.0552   0.9154   1.0000
  -0.250   0.1960   0.01822   0.01145  -0.0577   0.9060   1.0000
   0.000   0.2443   0.01822   0.01136  -0.0616   0.8982   1.0000
   0.250   0.2864   0.01811   0.01117  -0.0640   0.8862   1.0000
   0.500   0.3351   0.01767   0.01067  -0.0670   0.8736   1.0000
   0.750   0.3803   0.01711   0.01005  -0.0690   0.8600   1.0000
   1.000   0.4175   0.01662   0.00952  -0.0696   0.8459   1.0000
   1.250   0.4495   0.01624   0.00910  -0.0693   0.8319   1.0000
   1.500   0.4793   0.01594   0.00876  -0.0686   0.8187   1.0000
   1.750   0.5072   0.01568   0.00846  -0.0676   0.8051   1.0000
   2.000   0.5317   0.01549   0.00825  -0.0661   0.7897   1.0000
   2.250   0.5552   0.01535   0.00809  -0.0644   0.7733   1.0000
   2.500   0.5784   0.01522   0.00792  -0.0627   0.7555   1.0000
   2.750   0.6023   0.01506   0.00774  -0.0610   0.7368   1.0000
   3.000   0.6271   0.01489   0.00751  -0.0594   0.7174   1.0000
   3.250   0.6490   0.01482   0.00742  -0.0575   0.6940   1.0000
   3.500   0.6723   0.01473   0.00725  -0.0557   0.6689   1.0000
   3.750   0.6935   0.01471   0.00716  -0.0536   0.6383   1.0000
   4.000   0.7133   0.01476   0.00712  -0.0512   0.5998   1.0000
   4.250   0.7316   0.01491   0.00706  -0.0487   0.5495   1.0000
   4.500   0.7462   0.01532   0.00712  -0.0456   0.4778   1.0000
   4.750   0.7592   0.01610   0.00737  -0.0426   0.4037   1.0000
   5.000   0.7745   0.01701   0.00784  -0.0403   0.3560   1.0000
   5.250   0.7929   0.01788   0.00840  -0.0386   0.3257   1.0000
   5.500   0.8133   0.01868   0.00903  -0.0373   0.3027   1.0000
   5.750   0.8347   0.01951   0.00968  -0.0362   0.2850   1.0000
   6.000   0.8575   0.02035   0.01041  -0.0354   0.2704   1.0000
   6.250   0.8812   0.02123   0.01123  -0.0347   0.2583   1.0000
   6.500   0.9058   0.02217   0.01209  -0.0342   0.2480   1.0000
   6.750   0.9306   0.02311   0.01293  -0.0338   0.2381   1.0000
   7.000   0.9536   0.02399   0.01395  -0.0330   0.2290   1.0000
   7.250   0.9804   0.02516   0.01495  -0.0330   0.2215   1.0000
   7.500   1.0026   0.02607   0.01611  -0.0321   0.2146   1.0000
   7.750   1.0283   0.02719   0.01721  -0.0318   0.2087   1.0000
   8.000   1.0507   0.02839   0.01858  -0.0311   0.2030   1.0000
   8.250   1.0726   0.02943   0.01977  -0.0302   0.1970   1.0000
   8.500   1.0989   0.03091   0.02115  -0.0303   0.1921   1.0000
   8.750   1.1163   0.03217   0.02282  -0.0288   0.1880   1.0000
   9.000   1.1365   0.03355   0.02446  -0.0277   0.1839   1.0000
   9.250   1.1590   0.03489   0.02586  -0.0272   0.1798   1.0000
   9.500   1.1776   0.03669   0.02784  -0.0262   0.1760   1.0000
   9.750   1.1897   0.03837   0.02994  -0.0242   0.1721   1.0000
  10.000   1.2052   0.04016   0.03200  -0.0228   0.1689   1.0000
  10.250   1.2258   0.04177   0.03371  -0.0222   0.1655   1.0000
  10.500   1.2420   0.04409   0.03617  -0.0212   0.1623   1.0000
  10.750   1.2403   0.04649   0.03911  -0.0180   0.1593   1.0000
  11.000   1.2411   0.04905   0.04204  -0.0153   0.1564   1.0000
  11.250   1.2477   0.05127   0.04450  -0.0134   0.1534   1.0000
  11.500   1.2828   0.05274   0.04574  -0.0147   0.1486   1.0000
  11.750   1.2606   0.05595   0.04950  -0.0101   0.1469   1.0000
  12.000   1.2352   0.05960   0.05353  -0.0059   0.1453   1.0000
  12.250   1.2028   0.06341   0.05761  -0.0016   0.1447   1.0000
  12.500   1.1632   0.06833   0.06274   0.0013   0.1449   1.0000
  12.750   1.1150   0.07519   0.06976   0.0017   0.1459   1.0000
  13.000   1.0635   0.08444   0.07911  -0.0010   0.1474   1.0000
  13.250   1.0189   0.09538   0.09010  -0.0058   0.1485   1.0000
  13.750   1.2745   0.06419   0.05846   0.0063   0.1074   1.0000
  14.000   1.2388   0.06942   0.06395   0.0074   0.1073   1.0000
  14.250   1.2027   0.07578   0.07053   0.0069   0.1076   1.0000
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