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NACA 66 (p51hroot-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51hroot-il)
Reynolds number: 100,000
Max Cl/Cd: 27.08 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51hroot-il-100000-n5.txt
Download as CSV file: xf-p51hroot-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5280   0.08135   0.07605  -0.0853   0.9755   0.0339
 -12.500  -0.5512   0.07405   0.06856  -0.0908   0.9677   0.0338
 -12.250  -0.5690   0.06840   0.06268  -0.0943   0.9607   0.0336
 -12.000  -0.5882   0.06367   0.05769  -0.0959   0.9524   0.0337
 -11.750  -0.6011   0.05980   0.05355  -0.0965   0.9455   0.0336
 -11.500  -0.6196   0.05646   0.04990  -0.0950   0.9361   0.0338
 -11.250  -0.6310   0.05363   0.04677  -0.0931   0.9286   0.0338
 -11.000  -0.6422   0.05115   0.04400  -0.0902   0.9205   0.0339
 -10.750  -0.6519   0.04884   0.04134  -0.0867   0.9141   0.0341
 -10.500  -0.6570   0.04695   0.03916  -0.0833   0.9077   0.0342
 -10.250  -0.6594   0.04485   0.03666  -0.0801   0.9027   0.0344
 -10.000  -0.6562   0.04292   0.03435  -0.0773   0.8985   0.0347
  -9.750  -0.6441   0.04089   0.03219  -0.0762   0.8944   0.0354
  -9.500  -0.6299   0.03945   0.03064  -0.0752   0.8909   0.0364
  -9.250  -0.6142   0.03810   0.02912  -0.0741   0.8877   0.0376
  -9.000  -0.5971   0.03660   0.02736  -0.0730   0.8851   0.0389
  -8.750  -0.5775   0.03503   0.02551  -0.0722   0.8820   0.0397
  -8.500  -0.5548   0.03356   0.02378  -0.0718   0.8788   0.0406
  -8.250  -0.5312   0.03236   0.02230  -0.0715   0.8760   0.0420
  -8.000  -0.5016   0.03093   0.02084  -0.0724   0.8742   0.0437
  -7.750  -0.4738   0.02984   0.01972  -0.0729   0.8723   0.0455
  -7.500  -0.4426   0.02873   0.01854  -0.0739   0.8708   0.0471
  -7.250  -0.4135   0.02777   0.01749  -0.0744   0.8694   0.0488
  -7.000  -0.3895   0.02710   0.01669  -0.0741   0.8677   0.0510
  -6.750  -0.3740   0.02647   0.01614  -0.0728   0.8647   0.0534
  -6.500  -0.3604   0.02605   0.01572  -0.0709   0.8616   0.0558
  -6.250  -0.3472   0.02565   0.01524  -0.0688   0.8585   0.0581
  -6.000  -0.3335   0.02525   0.01474  -0.0667   0.8558   0.0608
  -5.750  -0.3199   0.02476   0.01425  -0.0646   0.8535   0.0645
  -5.500  -0.3033   0.02438   0.01382  -0.0629   0.8518   0.0709
  -5.250  -0.2957   0.02424   0.01371  -0.0600   0.8484   0.0773
  -5.000  -0.2872   0.02407   0.01357  -0.0570   0.8452   0.0889
  -4.750  -0.2795   0.02363   0.01339  -0.0540   0.8423   0.1243
  -4.500  -0.2805   0.02268   0.01315  -0.0496   0.8392   0.2528
  -4.250  -0.2877   0.02160   0.01287  -0.0439   0.8364   0.4072
  -4.000  -0.2580   0.02209   0.01459  -0.0417   0.8358   0.6550
  -3.750  -0.2694   0.02257   0.01504  -0.0349   0.8314   0.6878
  -3.500  -0.2700   0.02334   0.01580  -0.0292   0.8274   0.7240
  -3.250  -0.2565   0.02464   0.01708  -0.0247   0.8247   0.7637
  -3.000  -0.1941   0.02699   0.01933  -0.0273   0.8252   0.7929
  -2.750  -0.1705   0.02735   0.01958  -0.0264   0.8234   0.8019
  -2.500  -0.1418   0.02763   0.01973  -0.0265   0.8221   0.8079
  -2.250  -0.1297   0.02757   0.01957  -0.0240   0.8202   0.8164
  -2.000  -0.0936   0.02773   0.01962  -0.0256   0.8192   0.8196
  -1.750  -0.1329   0.02804   0.01996  -0.0142   0.8116   0.8318
  -1.500  -0.1070   0.02827   0.02011  -0.0142   0.8091   0.8347
  -1.250  -0.0823   0.02841   0.02017  -0.0140   0.8070   0.8384
  -1.000  -0.0619   0.02840   0.02009  -0.0130   0.8049   0.8432
  -0.750  -0.0482   0.02817   0.01979  -0.0109   0.8029   0.8491
  -0.500  -0.0468   0.02855   0.02017  -0.0066   0.7977   0.8534
  -0.250  -0.0425   0.02870   0.02029  -0.0029   0.7929   0.8592
   0.000  -0.0353   0.02847   0.02001   0.0003   0.7895   0.8648
   0.250  -0.0057   0.02848   0.01998  -0.0005   0.7876   0.8667
   0.500   0.0273   0.02852   0.01998  -0.0018   0.7862   0.8684
   1.000   0.0334   0.02880   0.02025   0.0057   0.7748   0.8776
   1.250   0.0534   0.02865   0.02009   0.0066   0.7720   0.8818
   1.500   0.0873   0.02869   0.02012   0.0052   0.7702   0.8833
   2.000   0.1119   0.02910   0.02057   0.0093   0.7588   0.8905
   2.250   0.1394   0.02907   0.02056   0.0090   0.7559   0.8937
   2.500   0.1686   0.02897   0.02048   0.0085   0.7538   0.8969
   2.750   0.1720   0.02933   0.02088   0.0119   0.7449   0.9013
   3.000   0.2008   0.02937   0.02097   0.0113   0.7411   0.9037
   3.250   0.2342   0.02930   0.02096   0.0101   0.7386   0.9059
   3.750   0.2668   0.02953   0.02131   0.0130   0.7254   0.9152
   4.000   0.3053   0.02934   0.02121   0.0111   0.7225   0.9170
   4.250   0.3205   0.02946   0.02142   0.0127   0.7120   0.9217
   4.500   0.3599   0.02887   0.02092   0.0112   0.7072   0.9238
   4.750   0.3723   0.02881   0.02095   0.0135   0.6963   0.9299
   5.000   0.4131   0.02816   0.02043   0.0118   0.6911   0.9315
   5.250   0.4308   0.02836   0.02075   0.0127   0.6800   0.9362
   5.500   0.4737   0.02729   0.01985   0.0112   0.6742   0.9382
   5.750   0.4928   0.02671   0.01939   0.0130   0.6589   0.9446
   6.000   0.5082   0.02658   0.01939   0.0144   0.6318   0.9505
   6.250   0.5232   0.02623   0.01914   0.0163   0.5952   0.9584
   6.500   0.5925   0.02188   0.01366   0.0162   0.4059   0.9553
   6.750   0.5972   0.02328   0.01436   0.0184   0.2887   0.9624
   7.000   0.6039   0.02498   0.01523   0.0198   0.1538   0.9694
   7.250   0.6216   0.02631   0.01604   0.0198   0.0781   0.9746
   7.750   0.6681   0.02823   0.01786   0.0186   0.0519   0.9854
   8.000   0.6913   0.02922   0.01891   0.0178   0.0482   0.9914
   8.250   0.7102   0.03016   0.01994   0.0177   0.0460   1.0000
   8.500   0.7074   0.03060   0.02040   0.0219   0.0448   1.0000
   8.750   0.7113   0.03130   0.02111   0.0247   0.0437   1.0000
   9.000   0.7187   0.03225   0.02205   0.0268   0.0427   1.0000
   9.250   0.7308   0.03316   0.02302   0.0283   0.0419   1.0000
   9.500   0.7455   0.03409   0.02401   0.0294   0.0409   1.0000
   9.750   0.7623   0.03504   0.02502   0.0304   0.0394   1.0000
  10.000   0.7804   0.03602   0.02602   0.0311   0.0380   1.0000
  10.250   0.8016   0.03708   0.02708   0.0315   0.0370   1.0000
  10.500   0.8270   0.03820   0.02818   0.0315   0.0363   1.0000
  10.750   0.8539   0.03946   0.02953   0.0314   0.0352   1.0000
  11.000   0.8778   0.04079   0.03105   0.0316   0.0343   1.0000
  11.250   0.8995   0.04227   0.03273   0.0318   0.0331   1.0000
  11.500   0.9220   0.04398   0.03462   0.0320   0.0325   1.0000
  11.750   0.9413   0.04584   0.03668   0.0323   0.0320   1.0000
  12.000   0.9572   0.04778   0.03878   0.0329   0.0314   1.0000
  12.250   0.9698   0.04974   0.04090   0.0337   0.0308   1.0000
  12.500   0.9841   0.05193   0.04315   0.0340   0.0301   1.0000
  12.750   0.9849   0.05438   0.04589   0.0357   0.0298   1.0000
  13.000   0.9796   0.05705   0.04891   0.0376   0.0295   1.0000
  13.250   0.9711   0.06002   0.05221   0.0395   0.0292   1.0000
  13.500   0.9626   0.06314   0.05560   0.0409   0.0291   1.0000
  13.750   0.9500   0.06669   0.05945   0.0422   0.0290   1.0000
  14.000   0.9358   0.07049   0.06350   0.0430   0.0289   1.0000
  14.250   0.9177   0.07481   0.06808   0.0435   0.0289   1.0000
  14.500   0.9000   0.07932   0.07282   0.0433   0.0290   1.0000
  14.750   0.8782   0.08459   0.07833   0.0423   0.0290   1.0000
  15.000   0.8555   0.09046   0.08441   0.0405   0.0291   1.0000
  15.250   0.8346   0.09678   0.09090   0.0378   0.0293   1.0000
  15.500   0.8078   0.10479   0.09909   0.0336   0.0294   1.0000
  15.750   0.7810   0.11401   0.10845   0.0281   0.0296   1.0000
  16.000   0.7625   0.12265   0.11718   0.0229   0.0299   1.0000
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