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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 200,000
Max Cl/Cd: 47.81 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e171-il-200000-n5.txt
Download as CSV file: xf-e171-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: (Dicke 12.28%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8164   0.09117   0.08733  -0.0142   1.0000   0.0088
 -13.750  -0.8477   0.08043   0.07634  -0.0210   1.0000   0.0086
 -13.500  -0.8678   0.07315   0.06889  -0.0254   1.0000   0.0086
 -13.250  -0.8865   0.06674   0.06226  -0.0289   1.0000   0.0086
 -13.000  -0.9007   0.06153   0.05686  -0.0314   1.0000   0.0087
 -12.750  -0.9145   0.05667   0.05179  -0.0333   1.0000   0.0087
 -12.500  -0.9247   0.05259   0.04751  -0.0344   1.0000   0.0087
 -12.250  -0.9329   0.04899   0.04371  -0.0349   1.0000   0.0088
 -12.000  -0.9388   0.04584   0.04038  -0.0350   1.0000   0.0090
 -11.750  -0.9421   0.04307   0.03742  -0.0345   1.0000   0.0091
 -11.500  -0.9440   0.04058   0.03475  -0.0337   1.0000   0.0094
 -11.250  -0.9438   0.03820   0.03215  -0.0326   1.0000   0.0094
 -11.000  -0.9416   0.03615   0.02988  -0.0311   1.0000   0.0098
 -10.750  -0.9375   0.03423   0.02778  -0.0294   1.0000   0.0101
 -10.500  -0.9315   0.03249   0.02585  -0.0276   1.0000   0.0104
 -10.250  -0.9242   0.03084   0.02403  -0.0256   1.0000   0.0108
 -10.000  -0.9154   0.02945   0.02247  -0.0235   1.0000   0.0115
  -9.750  -0.9031   0.02858   0.02141  -0.0216   1.0000   0.0123
  -9.500  -0.8956   0.02684   0.01960  -0.0194   1.0000   0.0131
  -9.250  -0.8837   0.02569   0.01841  -0.0177   1.0000   0.0141
  -9.000  -0.8706   0.02455   0.01718  -0.0159   1.0000   0.0149
  -8.750  -0.8569   0.02345   0.01597  -0.0141   1.0000   0.0160
  -8.500  -0.8424   0.02243   0.01483  -0.0123   1.0000   0.0172
  -8.250  -0.8295   0.02130   0.01358  -0.0103   1.0000   0.0186
  -8.000  -0.8141   0.02042   0.01268  -0.0088   1.0000   0.0211
  -7.750  -0.7964   0.01974   0.01192  -0.0073   1.0000   0.0241
  -7.500  -0.7810   0.01885   0.01097  -0.0055   1.0000   0.0270
  -7.250  -0.7640   0.01814   0.01024  -0.0040   1.0000   0.0316
  -7.000  -0.7465   0.01747   0.00951  -0.0023   1.0000   0.0365
  -6.750  -0.7298   0.01676   0.00881  -0.0006   1.0000   0.0438
  -6.500  -0.7130   0.01609   0.00815   0.0011   1.0000   0.0562
  -6.250  -0.6964   0.01542   0.00758   0.0028   1.0000   0.0747
  -6.000  -0.6741   0.01478   0.00703   0.0032   0.9965   0.0992
  -5.750  -0.6410   0.01406   0.00645   0.0014   0.9837   0.1358
  -5.500  -0.6101   0.01326   0.00589  -0.0001   0.9673   0.1889
  -5.250  -0.5809   0.01232   0.00534  -0.0013   0.9477   0.2695
  -5.000  -0.5502   0.01152   0.00487  -0.0026   0.9290   0.3526
  -4.750  -0.5181   0.01106   0.00460  -0.0037   0.9105   0.4157
  -4.500  -0.4873   0.01081   0.00441  -0.0044   0.8915   0.4607
  -4.250  -0.4582   0.01067   0.00427  -0.0046   0.8729   0.4960
  -4.000  -0.4302   0.01060   0.00414  -0.0044   0.8556   0.5201
  -3.750  -0.4032   0.01055   0.00399  -0.0041   0.8393   0.5389
  -3.500  -0.3767   0.01053   0.00387  -0.0037   0.8243   0.5553
  -3.250  -0.3502   0.01050   0.00376  -0.0033   0.8106   0.5697
  -3.000  -0.3238   0.01049   0.00367  -0.0029   0.7981   0.5822
  -2.750  -0.2973   0.01047   0.00356  -0.0025   0.7862   0.5940
  -2.500  -0.2707   0.01045   0.00348  -0.0021   0.7749   0.6051
  -2.250  -0.2440   0.01044   0.00340  -0.0018   0.7646   0.6157
  -2.000  -0.2172   0.01043   0.00331  -0.0015   0.7551   0.6253
  -1.750  -0.1903   0.01041   0.00326  -0.0012   0.7455   0.6341
  -1.500  -0.1633   0.01040   0.00319  -0.0010   0.7366   0.6435
  -1.250  -0.1363   0.01039   0.00315  -0.0008   0.7285   0.6520
  -1.000  -0.1091   0.01037   0.00311  -0.0006   0.7198   0.6600
  -0.750  -0.0820   0.01037   0.00307  -0.0004   0.7125   0.6679
  -0.500  -0.0546   0.01036   0.00305  -0.0003   0.7042   0.6749
  -0.250  -0.0273   0.01036   0.00303  -0.0001   0.6973   0.6825
   0.000   0.0000   0.01035   0.00303   0.0000   0.6894   0.6894
   0.250   0.0273   0.01036   0.00303   0.0001   0.6825   0.6972
   0.500   0.0546   0.01036   0.00305   0.0003   0.6749   0.7042
   0.750   0.0819   0.01037   0.00307   0.0004   0.6679   0.7125
   1.000   0.1091   0.01037   0.00311   0.0006   0.6600   0.7198
   1.250   0.1363   0.01039   0.00315   0.0008   0.6520   0.7285
   1.500   0.1633   0.01040   0.00319   0.0010   0.6435   0.7366
   1.750   0.1903   0.01041   0.00326   0.0012   0.6341   0.7454
   2.000   0.2172   0.01043   0.00332   0.0015   0.6253   0.7551
   2.250   0.2440   0.01044   0.00340   0.0018   0.6157   0.7646
   2.500   0.2708   0.01045   0.00348   0.0021   0.6052   0.7749
   2.750   0.2973   0.01047   0.00356   0.0025   0.5940   0.7862
   3.000   0.3238   0.01049   0.00367   0.0029   0.5824   0.7981
   3.250   0.3502   0.01050   0.00376   0.0033   0.5697   0.8106
   3.500   0.3767   0.01053   0.00387   0.0037   0.5554   0.8243
   3.750   0.4033   0.01055   0.00399   0.0041   0.5389   0.8393
   4.000   0.4302   0.01060   0.00414   0.0044   0.5199   0.8556
   4.250   0.4582   0.01067   0.00427   0.0046   0.4959   0.8729
   4.500   0.4873   0.01081   0.00441   0.0044   0.4607   0.8914
   4.750   0.5181   0.01106   0.00460   0.0037   0.4155   0.9106
   5.000   0.5503   0.01151   0.00487   0.0026   0.3534   0.9291
   5.250   0.5809   0.01232   0.00534   0.0013   0.2694   0.9479
   5.500   0.6101   0.01326   0.00589   0.0001   0.1892   0.9675
   5.750   0.6411   0.01406   0.00645  -0.0014   0.1358   0.9839
   6.000   0.6743   0.01478   0.00703  -0.0033   0.0993   0.9967
   6.250   0.6961   0.01543   0.00758  -0.0027   0.0744   1.0000
   6.500   0.7128   0.01609   0.00815  -0.0010   0.0566   1.0000
   6.750   0.7297   0.01676   0.00880   0.0006   0.0439   1.0000
   7.000   0.7465   0.01747   0.00951   0.0024   0.0365   1.0000
   7.250   0.7640   0.01813   0.01024   0.0040   0.0315   1.0000
   7.500   0.7811   0.01885   0.01097   0.0055   0.0269   1.0000
   7.750   0.7966   0.01973   0.01191   0.0073   0.0240   1.0000
   8.000   0.8143   0.02042   0.01268   0.0087   0.0212   1.0000
   8.250   0.8300   0.02128   0.01356   0.0103   0.0186   1.0000
   8.500   0.8428   0.02243   0.01483   0.0123   0.0172   1.0000
   8.750   0.8573   0.02345   0.01598   0.0140   0.0160   1.0000
   9.000   0.8711   0.02455   0.01718   0.0158   0.0148   1.0000
   9.250   0.8842   0.02570   0.01841   0.0176   0.0140   1.0000
   9.500   0.8963   0.02685   0.01963   0.0193   0.0131   1.0000
   9.750   0.9040   0.02855   0.02139   0.0215   0.0123   1.0000
  10.000   0.9153   0.02970   0.02270   0.0234   0.0118   1.0000
  10.250   0.9251   0.03085   0.02404   0.0254   0.0108   1.0000
  10.500   0.9324   0.03249   0.02586   0.0274   0.0104   1.0000
  10.750   0.9384   0.03429   0.02784   0.0293   0.0101   1.0000
  11.000   0.9425   0.03618   0.02992   0.0309   0.0097   1.0000
  11.250   0.9445   0.03829   0.03226   0.0324   0.0095   1.0000
  11.500   0.9450   0.04053   0.03468   0.0336   0.0092   1.0000
  11.750   0.9433   0.04311   0.03747   0.0344   0.0091   1.0000
  12.000   0.9393   0.04590   0.04044   0.0348   0.0089   1.0000
  12.250   0.9341   0.04897   0.04368   0.0347   0.0088   1.0000
  12.500   0.9265   0.05248   0.04738   0.0341   0.0086   1.0000
  12.750   0.9145   0.05689   0.05203   0.0330   0.0087   1.0000
  13.000   0.9028   0.06143   0.05676   0.0312   0.0087   1.0000
  13.250   0.8877   0.06677   0.06228   0.0287   0.0086   1.0000
  13.500   0.8686   0.07330   0.06903   0.0251   0.0086   1.0000
  13.750   0.8432   0.08171   0.07769   0.0200   0.0088   1.0000
  14.000   0.8111   0.09285   0.08906   0.0129   0.0090   1.0000
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