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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 100,000
Max Cl/Cd: 41.51 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e171-il-100000-n5.txt
Download as CSV file: xf-e171-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7521   0.09272   0.08764  -0.0167   1.0000   0.0191
 -12.750  -0.7909   0.08106   0.07571  -0.0248   1.0000   0.0185
 -12.500  -0.8154   0.07380   0.06820  -0.0294   1.0000   0.0181
 -12.250  -0.8339   0.06825   0.06244  -0.0322   1.0000   0.0181
 -12.000  -0.8504   0.06336   0.05736  -0.0340   1.0000   0.0182
 -11.750  -0.8638   0.05924   0.05303  -0.0349   1.0000   0.0182
 -11.500  -0.8757   0.05543   0.04903  -0.0352   1.0000   0.0184
 -11.250  -0.8850   0.05209   0.04547  -0.0347   1.0000   0.0185
 -11.000  -0.8916   0.04911   0.04228  -0.0336   1.0000   0.0187
 -10.750  -0.8955   0.04641   0.03937  -0.0320   1.0000   0.0190
 -10.500  -0.8964   0.04400   0.03675  -0.0301   1.0000   0.0194
 -10.250  -0.8944   0.04174   0.03429  -0.0280   1.0000   0.0199
 -10.000  -0.8887   0.03954   0.03186  -0.0261   1.0000   0.0206
  -9.750  -0.8789   0.03737   0.02945  -0.0245   1.0000   0.0215
  -9.500  -0.8663   0.03533   0.02718  -0.0230   1.0000   0.0226
  -9.250  -0.8523   0.03378   0.02534  -0.0215   1.0000   0.0248
  -9.000  -0.8394   0.03173   0.02323  -0.0201   1.0000   0.0268
  -8.750  -0.8257   0.03025   0.02166  -0.0186   1.0000   0.0290
  -8.500  -0.8107   0.02878   0.02006  -0.0170   1.0000   0.0313
  -8.250  -0.7946   0.02761   0.01870  -0.0155   1.0000   0.0348
  -8.000  -0.7827   0.02618   0.01730  -0.0137   1.0000   0.0388
  -7.750  -0.7686   0.02500   0.01603  -0.0118   1.0000   0.0432
  -7.500  -0.7549   0.02382   0.01477  -0.0098   1.0000   0.0480
  -7.250  -0.7403   0.02280   0.01373  -0.0081   1.0000   0.0568
  -7.000  -0.7269   0.02168   0.01265  -0.0061   1.0000   0.0675
  -6.750  -0.7125   0.02066   0.01162  -0.0041   1.0000   0.0834
  -6.500  -0.6985   0.01966   0.01078  -0.0022   1.0000   0.1097
  -6.250  -0.6850   0.01867   0.01002  -0.0003   1.0000   0.1480
  -6.000  -0.6723   0.01769   0.00934   0.0018   1.0000   0.1989
  -5.750  -0.6603   0.01673   0.00873   0.0040   1.0000   0.2623
  -5.500  -0.6486   0.01588   0.00826   0.0063   1.0000   0.3300
  -5.250  -0.6358   0.01532   0.00801   0.0088   1.0000   0.3938
  -5.000  -0.6155   0.01501   0.00789   0.0099   0.9961   0.4514
  -4.750  -0.5789   0.01489   0.00774   0.0079   0.9827   0.5022
  -4.500  -0.5430   0.01484   0.00764   0.0062   0.9687   0.5361
  -4.250  -0.5067   0.01480   0.00750   0.0045   0.9550   0.5623
  -4.000  -0.4711   0.01476   0.00733   0.0030   0.9413   0.5847
  -3.750  -0.4357   0.01472   0.00718   0.0016   0.9278   0.6025
  -3.500  -0.4009   0.01468   0.00705   0.0004   0.9143   0.6184
  -3.250  -0.3673   0.01464   0.00691  -0.0006   0.9009   0.6329
  -3.000  -0.3351   0.01459   0.00676  -0.0013   0.8875   0.6460
  -2.750  -0.3044   0.01454   0.00657  -0.0017   0.8740   0.6581
  -2.500  -0.2750   0.01450   0.00644  -0.0018   0.8611   0.6691
  -2.250  -0.2462   0.01446   0.00635  -0.0018   0.8486   0.6788
  -2.000  -0.2183   0.01442   0.00621  -0.0016   0.8368   0.6887
  -1.750  -0.1909   0.01438   0.00608  -0.0014   0.8258   0.6989
  -1.500  -0.1632   0.01435   0.00602  -0.0012   0.8148   0.7069
  -1.250  -0.1361   0.01432   0.00593  -0.0010   0.8040   0.7158
  -1.000  -0.1087   0.01429   0.00585  -0.0008   0.7942   0.7241
  -0.750  -0.0810   0.01427   0.00579  -0.0007   0.7852   0.7322
  -0.500  -0.0545   0.01425   0.00574  -0.0004   0.7752   0.7413
  -0.250  -0.0270   0.01424   0.00573  -0.0002   0.7664   0.7489
   0.000   0.0000   0.01423   0.00570   0.0000   0.7579   0.7579
   0.250   0.0270   0.01424   0.00573   0.0002   0.7489   0.7664
   0.500   0.0545   0.01425   0.00574   0.0004   0.7412   0.7752
   0.750   0.0810   0.01427   0.00579   0.0007   0.7322   0.7852
   1.000   0.1087   0.01429   0.00585   0.0008   0.7241   0.7942
   1.250   0.1361   0.01432   0.00593   0.0010   0.7158   0.8041
   1.500   0.1631   0.01435   0.00602   0.0012   0.7069   0.8148
   1.750   0.1909   0.01438   0.00608   0.0014   0.6989   0.8258
   2.000   0.2183   0.01442   0.00623   0.0016   0.6887   0.8368
   2.250   0.2462   0.01446   0.00635   0.0018   0.6788   0.8486
   2.500   0.2749   0.01450   0.00644   0.0018   0.6690   0.8611
   2.750   0.3044   0.01454   0.00657   0.0017   0.6581   0.8741
   3.000   0.3350   0.01459   0.00676   0.0013   0.6460   0.8875
   3.250   0.3672   0.01464   0.00690   0.0006   0.6329   0.9010
   3.500   0.4008   0.01468   0.00704  -0.0004   0.6184   0.9144
   3.750   0.4356   0.01472   0.00718  -0.0016   0.6025   0.9278
   4.000   0.4711   0.01475   0.00733  -0.0030   0.5847   0.9414
   4.250   0.5067   0.01480   0.00750  -0.0045   0.5623   0.9552
   4.500   0.5428   0.01484   0.00764  -0.0062   0.5362   0.9689
   4.750   0.5789   0.01489   0.00774  -0.0079   0.5019   0.9829
   5.000   0.6155   0.01501   0.00789  -0.0099   0.4511   0.9963
   5.250   0.6355   0.01531   0.00801  -0.0087   0.3940   1.0000
   5.500   0.6484   0.01587   0.00826  -0.0063   0.3311   1.0000
   5.750   0.6601   0.01672   0.00872  -0.0039   0.2626   1.0000
   6.000   0.6722   0.01768   0.00933  -0.0017   0.1994   1.0000
   6.250   0.6848   0.01867   0.01002   0.0003   0.1475   1.0000
   6.500   0.6984   0.01966   0.01078   0.0022   0.1099   1.0000
   6.750   0.7125   0.02066   0.01161   0.0041   0.0835   1.0000
   7.000   0.7269   0.02168   0.01265   0.0061   0.0676   1.0000
   7.250   0.7404   0.02280   0.01373   0.0081   0.0567   1.0000
   7.500   0.7550   0.02383   0.01478   0.0098   0.0479   1.0000
   7.750   0.7687   0.02501   0.01605   0.0118   0.0430   1.0000
   8.000   0.7831   0.02618   0.01730   0.0136   0.0390   1.0000
   8.250   0.7949   0.02761   0.01870   0.0154   0.0349   1.0000
   8.500   0.8112   0.02878   0.02007   0.0170   0.0313   1.0000
   8.750   0.8262   0.03027   0.02167   0.0185   0.0290   1.0000
   9.000   0.8399   0.03172   0.02322   0.0200   0.0268   1.0000
   9.250   0.8529   0.03381   0.02538   0.0214   0.0247   1.0000
   9.500   0.8671   0.03537   0.02722   0.0229   0.0227   1.0000
   9.750   0.8795   0.03735   0.02944   0.0244   0.0215   1.0000
  10.000   0.8895   0.03956   0.03188   0.0259   0.0206   1.0000
  10.250   0.8952   0.04177   0.03432   0.0278   0.0199   1.0000
  10.500   0.8972   0.04405   0.03681   0.0299   0.0194   1.0000
  10.750   0.8962   0.04648   0.03944   0.0319   0.0190   1.0000
  11.000   0.8925   0.04912   0.04229   0.0334   0.0187   1.0000
  11.250   0.8857   0.05214   0.04550   0.0345   0.0184   1.0000
  11.500   0.8763   0.05555   0.04912   0.0350   0.0183   1.0000
  11.750   0.8648   0.05925   0.05305   0.0348   0.0183   1.0000
  12.000   0.8497   0.06371   0.05769   0.0337   0.0180   1.0000
  12.250   0.8345   0.06838   0.06256   0.0320   0.0180   1.0000
  12.500   0.8167   0.07384   0.06822   0.0292   0.0180   1.0000
  12.750   0.7906   0.08140   0.07606   0.0244   0.0185   1.0000
  13.000   0.7522   0.09309   0.08802   0.0162   0.0192   1.0000
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