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HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/8 AIRFOIL (hq108-il)
Reynolds number: 50,000
Max Cl/Cd: 33.27 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq108-il-50000-n5.txt
Download as CSV file: xf-hq108-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5570   0.09541   0.08861  -0.0119   1.0000   0.0415
  -8.750  -0.5614   0.08967   0.08297  -0.0162   1.0000   0.0398
  -8.250  -0.5787   0.07744   0.07074  -0.0275   1.0000   0.0369
  -8.000  -0.5795   0.07306   0.06634  -0.0291   1.0000   0.0365
  -7.750  -0.5798   0.06865   0.06186  -0.0306   1.0000   0.0361
  -7.500  -0.5787   0.06431   0.05739  -0.0320   1.0000   0.0358
  -7.250  -0.5761   0.05976   0.05265  -0.0330   1.0000   0.0355
  -7.000  -0.5705   0.05539   0.04802  -0.0337   1.0000   0.0352
  -6.750  -0.5622   0.05103   0.04333  -0.0339   1.0000   0.0351
  -6.500  -0.5509   0.04691   0.03880  -0.0338   1.0000   0.0351
  -6.250  -0.5368   0.04296   0.03437  -0.0334   1.0000   0.0354
  -6.000  -0.5200   0.03930   0.03016  -0.0327   1.0000   0.0359
  -5.750  -0.5006   0.03602   0.02630  -0.0317   1.0000   0.0367
  -5.500  -0.4816   0.03327   0.02332  -0.0310   1.0000   0.0401
  -5.250  -0.4605   0.03125   0.02101  -0.0301   1.0000   0.0457
  -5.000  -0.4366   0.02890   0.01815  -0.0288   1.0000   0.0491
  -4.750  -0.4143   0.02669   0.01585  -0.0274   1.0000   0.0532
  -4.500  -0.3917   0.02513   0.01402  -0.0259   1.0000   0.0624
  -4.250  -0.3712   0.02365   0.01243  -0.0246   1.0000   0.0778
  -4.000  -0.3511   0.02218   0.01098  -0.0232   1.0000   0.0989
  -3.750  -0.3305   0.02067   0.00960  -0.0222   1.0000   0.1342
  -3.500  -0.3126   0.01887   0.00843  -0.0213   1.0000   0.2284
  -3.250  -0.3023   0.01697   0.00808  -0.0183   1.0000   0.5048
  -3.000  -0.2907   0.01663   0.00814  -0.0137   1.0000   0.6621
  -2.750  -0.2784   0.01651   0.00809  -0.0091   1.0000   0.7478
  -2.500  -0.2660   0.01640   0.00800  -0.0044   1.0000   0.8223
  -2.250  -0.2379   0.01631   0.00772  -0.0024   1.0000   0.8923
  -2.000  -0.1774   0.01630   0.00731  -0.0078   1.0000   0.9458
  -1.750  -0.1113   0.01617   0.00677  -0.0155   1.0000   0.9803
  -1.500  -0.0770   0.01597   0.00634  -0.0181   1.0000   1.0000
  -1.250  -0.0787   0.01582   0.00605  -0.0143   1.0000   1.0000
  -1.000  -0.0730   0.01578   0.00585  -0.0117   1.0000   1.0000
  -0.750  -0.0605   0.01581   0.00572  -0.0101   1.0000   1.0000
  -0.500  -0.0447   0.01591   0.00566  -0.0090   1.0000   1.0000
  -0.250  -0.0272   0.01606   0.00566  -0.0081   1.0000   1.0000
   0.000   0.0014   0.01630   0.00578  -0.0094   0.9950   1.0000
   0.250   0.0422   0.01662   0.00597  -0.0129   0.9846   1.0000
   0.500   0.0821   0.01692   0.00620  -0.0161   0.9735   1.0000
   0.750   0.1214   0.01721   0.00645  -0.0191   0.9619   1.0000
   1.000   0.1607   0.01748   0.00673  -0.0219   0.9500   1.0000
   1.250   0.2001   0.01774   0.00701  -0.0247   0.9378   1.0000
   1.500   0.2399   0.01798   0.00731  -0.0275   0.9256   1.0000
   1.750   0.2804   0.01821   0.00763  -0.0303   0.9133   1.0000
   2.000   0.3206   0.01837   0.00796  -0.0327   0.8983   1.0000
   2.250   0.3638   0.01837   0.00811  -0.0350   0.8792   1.0000
   2.500   0.3989   0.01835   0.00824  -0.0357   0.8561   1.0000
   2.750   0.4324   0.01835   0.00847  -0.0360   0.8349   1.0000
   3.000   0.4616   0.01842   0.00870  -0.0355   0.8133   1.0000
   3.250   0.4891   0.01848   0.00894  -0.0347   0.7899   1.0000
   3.500   0.5158   0.01850   0.00916  -0.0336   0.7641   1.0000
   3.750   0.5413   0.01852   0.00935  -0.0321   0.7340   1.0000
   4.000   0.5655   0.01850   0.00950  -0.0302   0.6969   1.0000
   4.250   0.5887   0.01849   0.00969  -0.0279   0.6486   1.0000
   4.500   0.6099   0.01858   0.00979  -0.0253   0.5824   1.0000
   4.750   0.6294   0.01892   0.00989  -0.0225   0.4926   1.0000
   5.000   0.6470   0.01978   0.01028  -0.0202   0.3920   1.0000
   5.250   0.6639   0.02103   0.01108  -0.0185   0.2994   1.0000
   5.500   0.6809   0.02256   0.01221  -0.0172   0.2199   1.0000
   5.750   0.6990   0.02421   0.01355  -0.0160   0.1559   1.0000
   6.000   0.7176   0.02597   0.01506  -0.0150   0.1110   1.0000
   6.250   0.7371   0.02783   0.01698  -0.0139   0.0832   1.0000
   6.500   0.7574   0.02992   0.01903  -0.0128   0.0667   1.0000
   6.750   0.7798   0.03217   0.02144  -0.0116   0.0553   1.0000
   7.000   0.8018   0.03431   0.02388  -0.0107   0.0448   1.0000
   7.250   0.8239   0.03744   0.02726  -0.0096   0.0406   1.0000
   7.500   0.8438   0.04028   0.03064  -0.0085   0.0357   1.0000
   7.750   0.8593   0.04275   0.03332  -0.0077   0.0317   1.0000
   8.000   0.8717   0.04664   0.03755  -0.0066   0.0300   1.0000
   8.250   0.8811   0.05068   0.04218  -0.0053   0.0294   1.0000
   8.500   0.8854   0.05494   0.04695  -0.0041   0.0291   1.0000
   8.750   0.8845   0.05934   0.05179  -0.0030   0.0288   1.0000
   9.000   0.8788   0.06378   0.05659  -0.0023   0.0288   1.0000
   9.250   0.8692   0.06812   0.06118  -0.0019   0.0288   1.0000
   9.500   0.8551   0.07222   0.06545  -0.0016   0.0290   1.0000
   9.750   0.8394   0.07679   0.07014  -0.0028   0.0291   1.0000
  10.000   0.8240   0.08209   0.07553  -0.0056   0.0293   1.0000
  10.250   0.8096   0.08824   0.08173  -0.0097   0.0296   1.0000
  10.500   0.7982   0.09494   0.08844  -0.0143   0.0298   1.0000
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