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S5020 (s5020-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S5020 (s5020-il)
Reynolds number: 50,000
Max Cl/Cd: 25.26 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s5020-il-50000.txt
Download as CSV file: xf-s5020-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S5020                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5295   0.11603   0.11008   0.0240   1.0000   0.1725
  -8.500  -0.5117   0.11073   0.10480   0.0249   1.0000   0.1825
  -8.250  -0.5277   0.10972   0.10394   0.0202   1.0000   0.1875
  -8.000  -0.5122   0.10498   0.09922   0.0211   1.0000   0.2009
  -7.750  -0.5019   0.10094   0.09524   0.0211   1.0000   0.2141
  -7.500  -0.4944   0.09726   0.09162   0.0207   1.0000   0.2274
  -7.250  -0.4887   0.09382   0.08826   0.0201   1.0000   0.2412
  -7.000  -0.4846   0.09055   0.08509   0.0194   1.0000   0.2562
  -6.750  -0.4850   0.08769   0.08233   0.0179   1.0000   0.2728
  -6.500  -0.4756   0.08391   0.07861   0.0182   1.0000   0.2923
  -6.250  -0.4753   0.08143   0.07621   0.0167   1.0000   0.3177
  -6.000  -0.4683   0.07837   0.07323   0.0173   1.0000   0.3472
  -5.750  -0.4409   0.07404   0.06896   0.0229   1.0000   0.3851
  -5.500  -0.4292   0.07115   0.06614   0.0260   1.0000   0.4313
  -5.250  -0.4173   0.06860   0.06368   0.0309   1.0000   0.4919
  -5.000  -0.3568   0.06404   0.05899   0.0400   1.0000   0.6225
  -4.250  -0.2129   0.04972   0.04457   0.0358   1.0000   0.8296
  -4.000  -0.2727   0.05028   0.04547   0.0373   1.0000   0.7276
  -3.750  -0.3260   0.04965   0.04521   0.0363   1.0000   0.6560
  -3.500  -0.3327   0.04138   0.03502  -0.0146   1.0000   0.2333
  -3.250  -0.3056   0.03787   0.03064  -0.0159   1.0000   0.1763
  -3.000  -0.2852   0.03555   0.02776  -0.0153   1.0000   0.1543
  -2.750  -0.2649   0.03355   0.02522  -0.0145   1.0000   0.1405
  -2.500  -0.2431   0.03216   0.02307  -0.0134   1.0000   0.1299
  -2.250  -0.1966   0.02964   0.02027  -0.0172   0.9888   0.1250
  -2.000  -0.1457   0.02785   0.01802  -0.0212   0.9761   0.1246
  -1.750  -0.0936   0.02664   0.01631  -0.0253   0.9631   0.1299
  -1.500  -0.0373   0.02511   0.01474  -0.0299   0.9511   0.1376
  -1.250   0.0178   0.02402   0.01355  -0.0344   0.9386   0.1566
  -1.000   0.1351   0.01947   0.01136  -0.0483   0.9328   1.0000
  -0.750   0.1857   0.01990   0.01129  -0.0528   0.9167   1.0000
  -0.500   0.2283   0.02038   0.01142  -0.0557   0.9006   1.0000
  -0.250   0.2589   0.02097   0.01177  -0.0564   0.8838   1.0000
   0.000   0.2854   0.02161   0.01222  -0.0563   0.8670   1.0000
   0.250   0.3109   0.02227   0.01270  -0.0560   0.8508   1.0000
   0.500   0.3349   0.02293   0.01321  -0.0553   0.8348   1.0000
   0.750   0.3578   0.02361   0.01376  -0.0543   0.8192   1.0000
   1.000   0.3800   0.02429   0.01433  -0.0531   0.8038   1.0000
   1.250   0.4015   0.02497   0.01492  -0.0518   0.7886   1.0000
   1.500   0.4227   0.02565   0.01551  -0.0503   0.7735   1.0000
   1.750   0.4437   0.02632   0.01612  -0.0488   0.7586   1.0000
   2.000   0.4646   0.02699   0.01672  -0.0472   0.7437   1.0000
   2.250   0.4842   0.02778   0.01748  -0.0458   0.7275   1.0000
   2.500   0.5042   0.02854   0.01824  -0.0445   0.7116   1.0000
   2.750   0.5244   0.02929   0.01897  -0.0430   0.6957   1.0000
   3.000   0.5449   0.03002   0.01969  -0.0415   0.6798   1.0000
   3.250   0.5657   0.03072   0.02039  -0.0400   0.6641   1.0000
   3.500   0.5866   0.03136   0.02108  -0.0383   0.6483   1.0000
   3.750   0.6079   0.03197   0.02171  -0.0366   0.6327   1.0000
   4.000   0.6294   0.03250   0.02226  -0.0348   0.6172   1.0000
   4.250   0.6512   0.03297   0.02275  -0.0328   0.6017   1.0000
   4.500   0.6733   0.03336   0.02318  -0.0308   0.5864   1.0000
   4.750   0.6933   0.03424   0.02417  -0.0296   0.5686   1.0000
   5.000   0.7136   0.03502   0.02505  -0.0283   0.5509   1.0000
   5.250   0.7355   0.03546   0.02555  -0.0265   0.5343   1.0000
   5.500   0.7581   0.03576   0.02592  -0.0245   0.5181   1.0000
   5.750   0.7817   0.03583   0.02609  -0.0222   0.5021   1.0000
   6.000   0.8058   0.03579   0.02611  -0.0199   0.4864   1.0000
   6.250   0.8244   0.03701   0.02748  -0.0191   0.4666   1.0000
   6.500   0.8465   0.03744   0.02801  -0.0174   0.4489   1.0000
   6.750   0.8715   0.03723   0.02786  -0.0150   0.4318   1.0000
   7.000   0.8978   0.03683   0.02752  -0.0125   0.4153   1.0000
   7.250   0.9146   0.03844   0.02934  -0.0119   0.3949   1.0000
   7.500   0.9382   0.03865   0.02964  -0.0100   0.3766   1.0000
   7.750   0.9656   0.03823   0.02917  -0.0076   0.3589   1.0000
   8.000   0.9814   0.04005   0.03128  -0.0070   0.3395   1.0000
   8.250   1.0022   0.04095   0.03230  -0.0055   0.3209   1.0000
   8.500   1.0298   0.04077   0.03203  -0.0034   0.3025   1.0000
   8.750   1.0440   0.04290   0.03441  -0.0027   0.2851   1.0000
   9.000   1.0574   0.04513   0.03687  -0.0019   0.2688   1.0000
   9.250   1.0720   0.04702   0.03896  -0.0008   0.2525   1.0000
   9.500   1.0819   0.04986   0.04203  -0.0001   0.2396   1.0000
   9.750   1.0912   0.05246   0.04481   0.0007   0.2265   1.0000
  10.000   1.1003   0.05499   0.04749   0.0017   0.2140   1.0000
  10.250   1.0257   0.06775   0.06055  -0.0035   0.2228   1.0000
  10.500   1.0047   0.07392   0.06671  -0.0054   0.2194   1.0000
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