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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 200,000
Max Cl/Cd: 87.56 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae51-il-200000.txt
Download as CSV file: xf-dae51-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-51 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3424   0.09480   0.09152  -0.0402   1.0000   0.0429
  -8.000  -0.3652   0.09460   0.09142  -0.0358   1.0000   0.0429
  -7.750  -0.3904   0.09458   0.09149  -0.0307   1.0000   0.0429
  -7.500  -0.3682   0.08879   0.08570  -0.0447   0.9937   0.0433
  -7.250  -0.3555   0.08207   0.07899  -0.0483   0.9895   0.0441
  -7.000  -0.3377   0.07883   0.07574  -0.0474   0.9868   0.0452
  -6.750  -0.3123   0.07493   0.07181  -0.0519   0.9837   0.0468
  -6.500  -0.2882   0.07049   0.06733  -0.0588   0.9769   0.0489
  -6.250  -0.2319   0.06073   0.05715  -0.0851   0.9696   0.0548
  -6.000  -0.2130   0.05397   0.05035  -0.0899   0.9634   0.0562
  -5.750  -0.1861   0.05118   0.04762  -0.0917   0.9606   0.0580
  -5.500  -0.1514   0.04755   0.04388  -0.0969   0.9579   0.0619
  -5.250  -0.1182   0.04138   0.03715  -0.1049   0.9497   0.0697
  -5.000  -0.0888   0.03880   0.03460  -0.1069   0.9458   0.0727
  -4.750  -0.0519   0.03521   0.03063  -0.1117   0.9425   0.0847
  -4.500  -0.0291   0.03356   0.02894  -0.1118   0.9345   0.0909
  -4.250   0.0029   0.03074   0.02586  -0.1143   0.9299   0.1015
  -4.000   0.0471   0.02235   0.01565  -0.1147   0.9251   0.0431
  -3.750   0.0750   0.02012   0.01310  -0.1147   0.9184   0.0426
  -3.500   0.1066   0.01879   0.01146  -0.1150   0.9141   0.0432
  -3.250   0.1323   0.01718   0.00978  -0.1148   0.9070   0.0468
  -3.000   0.1607   0.01632   0.00883  -0.1145   0.9012   0.0500
  -2.750   0.1886   0.01556   0.00798  -0.1141   0.8956   0.0536
  -2.500   0.2148   0.01476   0.00721  -0.1137   0.8883   0.0610
  -2.250   0.2429   0.01403   0.00647  -0.1133   0.8835   0.0723
  -2.000   0.2693   0.01345   0.00601  -0.1131   0.8754   0.1029
  -1.750   0.2958   0.01206   0.00566  -0.1133   0.8698   0.3704
  -1.500   0.3190   0.01139   0.00573  -0.1124   0.8625   0.5897
  -1.250   0.3376   0.01080   0.00571  -0.1095   0.8559   0.7747
  -1.000   0.3670   0.01038   0.00547  -0.1087   0.8494   1.0000
  -0.750   0.3946   0.01040   0.00532  -0.1085   0.8420   1.0000
  -0.500   0.4222   0.01044   0.00520  -0.1082   0.8354   1.0000
  -0.250   0.4495   0.01047   0.00511  -0.1080   0.8274   1.0000
   0.000   0.4771   0.01051   0.00501  -0.1076   0.8206   1.0000
   0.250   0.5044   0.01054   0.00495  -0.1074   0.8124   1.0000
   0.500   0.5319   0.01058   0.00489  -0.1071   0.8049   1.0000
   0.750   0.5593   0.01061   0.00483  -0.1068   0.7967   1.0000
   1.000   0.5867   0.01067   0.00481  -0.1065   0.7883   1.0000
   1.250   0.6144   0.01067   0.00473  -0.1061   0.7805   1.0000
   1.500   0.6415   0.01074   0.00476  -0.1059   0.7708   1.0000
   1.750   0.6693   0.01075   0.00469  -0.1056   0.7631   1.0000
   2.000   0.6964   0.01080   0.00472  -0.1053   0.7527   1.0000
   2.250   0.7237   0.01086   0.00475  -0.1050   0.7428   1.0000
   2.500   0.7515   0.01088   0.00469  -0.1047   0.7339   1.0000
   2.750   0.7785   0.01094   0.00474  -0.1044   0.7226   1.0000
   3.000   0.8056   0.01100   0.00481  -0.1040   0.7112   1.0000
   3.250   0.8327   0.01107   0.00485  -0.1037   0.6999   1.0000
   3.500   0.8600   0.01113   0.00487  -0.1034   0.6885   1.0000
   3.750   0.8871   0.01121   0.00492  -0.1030   0.6763   1.0000
   4.000   0.9138   0.01131   0.00504  -0.1027   0.6627   1.0000
   4.250   0.9403   0.01142   0.00514  -0.1023   0.6485   1.0000
   4.500   0.9668   0.01154   0.00526  -0.1019   0.6337   1.0000
   4.750   0.9931   0.01169   0.00541  -0.1014   0.6183   1.0000
   5.000   1.0190   0.01186   0.00558  -0.1009   0.6014   1.0000
   5.250   1.0446   0.01204   0.00578  -0.1004   0.5826   1.0000
   5.500   1.0698   0.01225   0.00597  -0.0998   0.5628   1.0000
   5.750   1.0945   0.01250   0.00621  -0.0992   0.5410   1.0000
   6.000   1.1184   0.01279   0.00645  -0.0984   0.5160   1.0000
   6.250   1.1419   0.01310   0.00674  -0.0976   0.4889   1.0000
   6.500   1.1647   0.01348   0.00708  -0.0967   0.4599   1.0000
   6.750   1.1863   0.01396   0.00747  -0.0956   0.4270   1.0000
   7.000   1.2068   0.01450   0.00792  -0.0945   0.3880   1.0000
   7.250   1.2257   0.01519   0.00845  -0.0932   0.3455   1.0000
   7.500   1.2432   0.01601   0.00908  -0.0917   0.3006   1.0000
   7.750   1.2591   0.01698   0.00984  -0.0901   0.2545   1.0000
   8.000   1.2734   0.01809   0.01072  -0.0884   0.2057   1.0000
   8.250   1.2843   0.01948   0.01178  -0.0863   0.1521   1.0000
   8.500   1.2918   0.02117   0.01311  -0.0837   0.1035   1.0000
   8.750   1.2978   0.02291   0.01463  -0.0808   0.0770   1.0000
   9.000   1.3016   0.02455   0.01621  -0.0776   0.0639   1.0000
   9.250   1.3103   0.02581   0.01754  -0.0750   0.0556   1.0000
   9.500   1.3141   0.02751   0.01928  -0.0721   0.0506   1.0000
   9.750   1.3223   0.02893   0.02078  -0.0698   0.0463   1.0000
  10.000   1.3241   0.03103   0.02284  -0.0671   0.0429   1.0000
  10.250   1.3341   0.03248   0.02444  -0.0652   0.0401   1.0000
  10.500   1.3434   0.03407   0.02612  -0.0633   0.0377   1.0000
  10.750   1.3520   0.03580   0.02789  -0.0615   0.0357   1.0000
  11.000   1.3640   0.03846   0.03052  -0.0595   0.0335   1.0000
  11.250   1.3746   0.03992   0.03220  -0.0579   0.0322   1.0000
  11.500   1.3853   0.04163   0.03408  -0.0563   0.0306   1.0000
  11.750   1.3963   0.04355   0.03615  -0.0548   0.0293   1.0000
  12.000   1.4066   0.04563   0.03837  -0.0533   0.0283   1.0000
  12.250   1.4166   0.04788   0.04075  -0.0518   0.0274   1.0000
  12.500   1.4278   0.05062   0.04361  -0.0505   0.0267   1.0000
  12.750   1.4367   0.05552   0.04881  -0.0491   0.0258   1.0000
  13.000   1.4297   0.05849   0.05206  -0.0470   0.0255   1.0000
  13.250   1.4209   0.06145   0.05530  -0.0453   0.0252   1.0000
  13.500   1.4109   0.06488   0.05901  -0.0440   0.0250   1.0000
  13.750   1.3990   0.06883   0.06323  -0.0431   0.0247   1.0000
  14.000   1.3849   0.07326   0.06793  -0.0426   0.0246   1.0000
  14.250   1.3685   0.07820   0.07313  -0.0426   0.0246   1.0000
  14.500   1.3503   0.08358   0.07876  -0.0433   0.0246   1.0000
  14.750   1.3306   0.08945   0.08486  -0.0446   0.0247   1.0000
  15.000   1.3099   0.09577   0.09141  -0.0467   0.0248   1.0000
  15.250   1.2884   0.10274   0.09858  -0.0496   0.0249   1.0000
  15.500   1.2665   0.11032   0.10636  -0.0533   0.0251   1.0000
  15.750   1.2444   0.11851   0.11473  -0.0578   0.0253   1.0000
  16.000   1.2221   0.12740   0.12377  -0.0630   0.0255   1.0000
  16.250   1.1005   0.17249   0.16936  -0.0945   0.0323   1.0000
  16.500   1.0952   0.17948   0.17632  -0.0976   0.0332   1.0000
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