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SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD8020-010-88 (sd8020-il)
Reynolds number: 50,000
Max Cl/Cd: 26.14 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8020-il-50000.txt
Download as CSV file: xf-sd8020-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8020-010-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7449   0.07990   0.07297  -0.0233   1.0000   0.1347
  -9.500  -0.7581   0.07484   0.06785  -0.0234   1.0000   0.1330
  -9.250  -0.7728   0.06967   0.06260  -0.0234   1.0000   0.1320
  -9.000  -0.7877   0.06454   0.05731  -0.0230   1.0000   0.1311
  -8.750  -0.8002   0.05954   0.05204  -0.0219   1.0000   0.1307
  -8.500  -0.8084   0.05476   0.04689  -0.0203   1.0000   0.1309
  -8.250  -0.8125   0.05018   0.04180  -0.0183   1.0000   0.1319
  -8.000  -0.8128   0.04595   0.03691  -0.0158   1.0000   0.1338
  -7.750  -0.7955   0.04343   0.03448  -0.0145   1.0000   0.1435
  -7.500  -0.7855   0.04026   0.03094  -0.0124   1.0000   0.1519
  -7.250  -0.7744   0.03745   0.02759  -0.0100   1.0000   0.1625
  -7.000  -0.7568   0.03525   0.02537  -0.0084   1.0000   0.1784
  -6.750  -0.7386   0.03341   0.02352  -0.0067   1.0000   0.1973
  -6.500  -0.7220   0.03150   0.02138  -0.0046   1.0000   0.2184
  -6.250  -0.7029   0.02992   0.01991  -0.0029   1.0000   0.2423
  -6.000  -0.6841   0.02837   0.01836  -0.0011   1.0000   0.2686
  -5.750  -0.6650   0.02695   0.01698   0.0008   1.0000   0.2978
  -5.500  -0.6463   0.02572   0.01583   0.0028   1.0000   0.3317
  -5.250  -0.6275   0.02454   0.01474   0.0049   1.0000   0.3690
  -5.000  -0.6091   0.02351   0.01386   0.0072   1.0000   0.4114
  -4.750  -0.5907   0.02263   0.01322   0.0097   1.0000   0.4575
  -4.500  -0.5723   0.02189   0.01270   0.0124   1.0000   0.5067
  -4.250  -0.5546   0.02126   0.01224   0.0154   1.0000   0.5590
  -4.000  -0.5359   0.02083   0.01203   0.0187   1.0000   0.6115
  -3.750  -0.5171   0.02054   0.01190   0.0221   1.0000   0.6643
  -3.500  -0.4967   0.02044   0.01190   0.0257   1.0000   0.7163
  -3.250  -0.4730   0.02051   0.01198   0.0290   1.0000   0.7671
  -3.000  -0.4354   0.02094   0.01234   0.0302   1.0000   0.8169
  -2.750  -0.3721   0.02171   0.01284   0.0267   1.0000   0.8658
  -2.500  -0.2653   0.02249   0.01312   0.0143   1.0000   0.9098
  -2.250  -0.1644   0.02225   0.01248   0.0008   1.0000   0.9488
  -2.000  -0.0706   0.02126   0.01119  -0.0130   1.0000   0.9852
  -1.750  -0.0228   0.02021   0.01001  -0.0193   1.0000   1.0000
  -1.500  -0.0162   0.01962   0.00943  -0.0176   1.0000   1.0000
  -1.250  -0.0105   0.01913   0.00895  -0.0156   1.0000   1.0000
  -1.000  -0.0058   0.01874   0.00857  -0.0132   1.0000   1.0000
  -0.750  -0.0021   0.01842   0.00828  -0.0104   1.0000   1.0000
  -0.500   0.0001   0.01820   0.00807  -0.0073   1.0000   1.0000
  -0.250   0.0007   0.01806   0.00795  -0.0038   1.0000   1.0000
   0.000   0.0000   0.01801   0.00791   0.0000   1.0000   1.0000
   0.250  -0.0007   0.01805   0.00795   0.0038   1.0000   1.0000
   0.500  -0.0001   0.01819   0.00807   0.0073   1.0000   1.0000
   0.750   0.0021   0.01842   0.00827   0.0104   1.0000   1.0000
   1.000   0.0058   0.01873   0.00857   0.0132   1.0000   1.0000
   1.250   0.0106   0.01913   0.00895   0.0156   1.0000   1.0000
   1.500   0.0163   0.01962   0.00942   0.0176   1.0000   1.0000
   1.750   0.0229   0.02020   0.01001   0.0193   1.0000   1.0000
   2.000   0.0707   0.02126   0.01120   0.0130   0.9852   1.0000
   2.250   0.1641   0.02225   0.01247  -0.0007   0.9490   1.0000
   2.500   0.2653   0.02248   0.01311  -0.0143   0.9099   1.0000
   2.750   0.3722   0.02170   0.01283  -0.0267   0.8659   1.0000
   3.000   0.4353   0.02094   0.01234  -0.0302   0.8170   1.0000
   3.250   0.4729   0.02051   0.01198  -0.0290   0.7672   1.0000
   3.500   0.4967   0.02044   0.01190  -0.0257   0.7163   1.0000
   3.750   0.5171   0.02054   0.01190  -0.0221   0.6643   1.0000
   4.000   0.5359   0.02083   0.01203  -0.0187   0.6115   1.0000
   4.250   0.5546   0.02126   0.01224  -0.0154   0.5590   1.0000
   4.500   0.5723   0.02189   0.01270  -0.0124   0.5067   1.0000
   4.750   0.5907   0.02264   0.01322  -0.0097   0.4573   1.0000
   5.000   0.6091   0.02351   0.01386  -0.0072   0.4114   1.0000
   5.250   0.6274   0.02454   0.01474  -0.0049   0.3690   1.0000
   5.500   0.6462   0.02571   0.01579  -0.0028   0.3314   1.0000
   5.750   0.6650   0.02695   0.01697  -0.0008   0.2976   1.0000
   6.000   0.6841   0.02836   0.01834   0.0011   0.2682   1.0000
   6.250   0.7028   0.02992   0.01990   0.0029   0.2420   1.0000
   6.500   0.7218   0.03150   0.02139   0.0047   0.2180   1.0000
   6.750   0.7386   0.03342   0.02353   0.0067   0.1971   1.0000
   7.000   0.7569   0.03526   0.02538   0.0084   0.1783   1.0000
   7.250   0.7744   0.03747   0.02762   0.0100   0.1625   1.0000
   7.500   0.7855   0.04027   0.03095   0.0124   0.1518   1.0000
   7.750   0.7957   0.04346   0.03450   0.0145   0.1438   1.0000
   8.000   0.8132   0.04596   0.03690   0.0158   0.1339   1.0000
   8.250   0.8128   0.05018   0.04179   0.0183   0.1320   1.0000
   8.500   0.8087   0.05475   0.04687   0.0203   0.1310   1.0000
   8.750   0.8002   0.05956   0.05206   0.0219   0.1307   1.0000
   9.000   0.7882   0.06455   0.05731   0.0229   0.1312   1.0000
   9.250   0.7743   0.06965   0.06258   0.0234   0.1322   1.0000
   9.500   0.7604   0.07479   0.06780   0.0234   0.1331   1.0000
   9.750   0.7479   0.07986   0.07289   0.0233   0.1339   1.0000
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