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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 100,000
Max Cl/Cd: 58.89 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e176-il-100000-n5.txt
Download as CSV file: xf-e176-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3861   0.09238   0.08774  -0.0239   1.0000   0.0560
  -8.000  -0.3845   0.08898   0.08440  -0.0259   1.0000   0.0566
  -7.750  -0.3976   0.08599   0.08158  -0.0340   1.0000   0.0594
  -7.500  -0.3941   0.08170   0.07732  -0.0396   1.0000   0.0597
  -7.000  -0.3817   0.06964   0.06529  -0.0407   1.0000   0.0330
  -6.750  -0.3773   0.06577   0.06146  -0.0426   1.0000   0.0319
  -6.500  -0.3755   0.06177   0.05748  -0.0444   1.0000   0.0309
  -6.250  -0.3489   0.05453   0.05005  -0.0533   0.9787   0.0290
  -6.000  -0.3189   0.04298   0.03772  -0.0636   0.9578   0.0259
  -5.750  -0.2886   0.03837   0.03255  -0.0674   0.9423   0.0253
  -5.500  -0.2612   0.03427   0.02791  -0.0698   0.9270   0.0252
  -5.250  -0.2338   0.03084   0.02394  -0.0713   0.9123   0.0251
  -5.000  -0.2078   0.02795   0.02061  -0.0721   0.8983   0.0264
  -4.750  -0.1814   0.02640   0.01881  -0.0725   0.8851   0.0283
  -4.500  -0.1550   0.02453   0.01652  -0.0724   0.8723   0.0293
  -4.250  -0.1287   0.02271   0.01429  -0.0719   0.8600   0.0296
  -4.000  -0.1023   0.02122   0.01247  -0.0714   0.8484   0.0301
  -3.750  -0.0761   0.01996   0.01092  -0.0708   0.8376   0.0309
  -3.500  -0.0501   0.01891   0.00967  -0.0701   0.8277   0.0320
  -3.250  -0.0243   0.01804   0.00864  -0.0695   0.8175   0.0334
  -3.000   0.0013   0.01726   0.00771  -0.0689   0.8077   0.0356
  -2.750   0.0274   0.01666   0.00701  -0.0685   0.7989   0.0415
  -2.500   0.0537   0.01606   0.00634  -0.0680   0.7899   0.0545
  -2.250   0.0796   0.01528   0.00573  -0.0676   0.7814   0.1033
  -2.000   0.1044   0.01445   0.00547  -0.0674   0.7737   0.2439
  -1.750   0.1275   0.01351   0.00539  -0.0668   0.7652   0.4692
  -1.500   0.1468   0.01269   0.00531  -0.0642   0.7587   0.7037
  -1.250   0.1991   0.01212   0.00501  -0.0678   0.7509   0.9770
  -1.000   0.2302   0.01218   0.00478  -0.0685   0.7443   1.0000
  -0.750   0.2561   0.01229   0.00468  -0.0681   0.7361   1.0000
  -0.500   0.2820   0.01241   0.00457  -0.0677   0.7297   1.0000
  -0.250   0.3082   0.01254   0.00455  -0.0674   0.7219   1.0000
   0.000   0.3344   0.01266   0.00449  -0.0670   0.7158   1.0000
   0.250   0.3607   0.01281   0.00453  -0.0668   0.7082   1.0000
   0.500   0.3871   0.01295   0.00451  -0.0664   0.7025   1.0000
   0.750   0.4135   0.01311   0.00461  -0.0662   0.6950   1.0000
   1.000   0.4400   0.01326   0.00465  -0.0659   0.6892   1.0000
   1.250   0.4665   0.01344   0.00478  -0.0657   0.6822   1.0000
   1.500   0.4930   0.01361   0.00487  -0.0654   0.6761   1.0000
   1.750   0.5195   0.01380   0.00503  -0.0652   0.6696   1.0000
   2.000   0.5461   0.01398   0.00519  -0.0649   0.6631   1.0000
   2.250   0.5726   0.01417   0.00536  -0.0646   0.6570   1.0000
   2.500   0.5990   0.01437   0.00557  -0.0644   0.6500   1.0000
   2.750   0.6256   0.01456   0.00575  -0.0641   0.6440   1.0000
   3.000   0.6519   0.01478   0.00603  -0.0639   0.6364   1.0000
   3.250   0.6784   0.01496   0.00623  -0.0636   0.6298   1.0000
   3.500   0.7044   0.01516   0.00649  -0.0632   0.6213   1.0000
   3.750   0.7305   0.01535   0.00673  -0.0629   0.6130   1.0000
   4.000   0.7568   0.01550   0.00694  -0.0624   0.6045   1.0000
   4.250   0.7824   0.01568   0.00722  -0.0620   0.5939   1.0000
   4.500   0.8081   0.01583   0.00745  -0.0615   0.5832   1.0000
   4.750   0.8338   0.01595   0.00765  -0.0609   0.5720   1.0000
   5.000   0.8593   0.01607   0.00790  -0.0603   0.5600   1.0000
   5.250   0.8846   0.01620   0.00813  -0.0597   0.5463   1.0000
   5.500   0.9094   0.01633   0.00841  -0.0590   0.5302   1.0000
   5.750   0.9339   0.01646   0.00867  -0.0583   0.5118   1.0000
   6.000   0.9582   0.01659   0.00888  -0.0574   0.4915   1.0000
   6.250   0.9817   0.01679   0.00924  -0.0566   0.4659   1.0000
   6.500   1.0040   0.01705   0.00956  -0.0555   0.4299   1.0000
   6.750   1.0222   0.01757   0.00982  -0.0538   0.3602   1.0000
   7.000   1.0344   0.01883   0.01050  -0.0518   0.2683   1.0000
   7.250   1.0448   0.02047   0.01162  -0.0500   0.1884   1.0000
   7.500   1.0552   0.02214   0.01285  -0.0483   0.1221   1.0000
   7.750   1.0648   0.02389   0.01418  -0.0466   0.0663   1.0000
   8.000   1.0740   0.02565   0.01573  -0.0446   0.0360   1.0000
   8.250   1.0854   0.02714   0.01727  -0.0427   0.0274   1.0000
   8.500   1.0955   0.02868   0.01892  -0.0406   0.0239   1.0000
   8.750   1.1052   0.03014   0.02055  -0.0387   0.0218   1.0000
   9.000   1.1118   0.03165   0.02220  -0.0364   0.0204   1.0000
   9.250   1.1169   0.03327   0.02394  -0.0342   0.0195   1.0000
   9.500   1.1199   0.03519   0.02598  -0.0321   0.0188   1.0000
   9.750   1.1238   0.03723   0.02812  -0.0302   0.0181   1.0000
  10.000   1.1316   0.03909   0.03017  -0.0287   0.0173   1.0000
  10.250   1.1400   0.04098   0.03223  -0.0275   0.0163   1.0000
  10.750   1.1553   0.04513   0.03674  -0.0253   0.0147   1.0000
  11.000   1.1626   0.04746   0.03923  -0.0243   0.0143   1.0000
  11.250   1.1691   0.05003   0.04197  -0.0234   0.0140   1.0000
  11.500   1.1744   0.05276   0.04490  -0.0226   0.0138   1.0000
  11.750   1.1778   0.05578   0.04813  -0.0219   0.0136   1.0000
  12.000   1.1789   0.05907   0.05164  -0.0214   0.0135   1.0000
  12.250   1.1769   0.06272   0.05552  -0.0212   0.0134   1.0000
  12.500   1.1721   0.06674   0.05980  -0.0214   0.0133   1.0000
  12.750   1.1645   0.07108   0.06439  -0.0220   0.0133   1.0000
  13.000   1.1547   0.07581   0.06938  -0.0231   0.0133   1.0000
  13.250   1.1428   0.08092   0.07474  -0.0247   0.0133   1.0000
  13.500   1.1294   0.08647   0.08054  -0.0269   0.0133   1.0000
  13.750   1.1132   0.09279   0.08709  -0.0299   0.0133   1.0000
  14.000   1.0959   0.09975   0.09429  -0.0337   0.0135   1.0000
  14.250   1.0765   0.10784   0.10262  -0.0385   0.0136   1.0000
  14.500   1.0535   0.11770   0.11272  -0.0448   0.0138   1.0000
  14.750   1.0248   0.13068   0.12592  -0.0534   0.0141   1.0000
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