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HQ 0/7 AIRFOIL (hq07-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 0/7 AIRFOIL (hq07-il)
Reynolds number: 200,000
Max Cl/Cd: 43.14 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq07-il-200000.txt
Download as CSV file: xf-hq07-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/7 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5805   0.09103   0.08791   0.0073   1.0000   0.0367
  -9.000  -0.5822   0.08619   0.08310   0.0056   1.0000   0.0374
  -8.000  -0.7065   0.06777   0.06425  -0.0123   1.0000   0.0350
  -7.750  -0.7013   0.06391   0.06038  -0.0124   1.0000   0.0359
  -7.500  -0.6960   0.06015   0.05655  -0.0128   1.0000   0.0369
  -7.250  -0.6897   0.05619   0.05245  -0.0133   1.0000   0.0381
  -7.000  -0.6816   0.05203   0.04810  -0.0136   1.0000   0.0396
  -6.750  -0.6711   0.04780   0.04358  -0.0137   1.0000   0.0416
  -6.500  -0.6623   0.04394   0.03890  -0.0130   1.0000   0.0472
  -6.250  -0.6402   0.03442   0.02886  -0.0106   1.0000   0.0211
  -6.000  -0.6241   0.02965   0.02361  -0.0095   1.0000   0.0199
  -5.750  -0.6035   0.02585   0.01928  -0.0082   1.0000   0.0196
  -5.500  -0.5800   0.02295   0.01589  -0.0070   1.0000   0.0206
  -5.250  -0.5575   0.02051   0.01315  -0.0062   1.0000   0.0256
  -5.000  -0.5324   0.01889   0.01124  -0.0054   1.0000   0.0302
  -4.750  -0.5082   0.01680   0.00898  -0.0043   1.0000   0.0373
  -4.500  -0.4832   0.01587   0.00794  -0.0036   1.0000   0.0451
  -4.250  -0.4602   0.01451   0.00661  -0.0028   1.0000   0.0523
  -4.000  -0.4360   0.01363   0.00563  -0.0019   1.0000   0.0586
  -3.750  -0.4134   0.01246   0.00450  -0.0010   1.0000   0.0737
  -3.500  -0.3946   0.01059   0.00349   0.0000   1.0000   0.2274
  -3.250  -0.3795   0.00891   0.00310   0.0017   1.0000   0.5024
  -3.000  -0.3611   0.00837   0.00311   0.0039   1.0000   0.6498
  -2.750  -0.3407   0.00817   0.00303   0.0059   1.0000   0.7188
  -2.500  -0.3208   0.00805   0.00302   0.0081   1.0000   0.7691
  -2.250  -0.3012   0.00798   0.00300   0.0103   1.0000   0.8069
  -2.000  -0.2834   0.00790   0.00299   0.0130   1.0000   0.8405
  -1.750  -0.2672   0.00786   0.00299   0.0159   1.0000   0.8738
  -1.500  -0.2493   0.00784   0.00300   0.0183   1.0000   0.9012
  -1.250  -0.2246   0.00786   0.00296   0.0191   1.0000   0.9228
  -1.000  -0.1905   0.00793   0.00299   0.0177   1.0000   0.9449
  -0.750  -0.1455   0.00802   0.00303   0.0141   1.0000   0.9637
  -0.500  -0.0946   0.00810   0.00306   0.0092   1.0000   0.9784
  -0.250  -0.0420   0.00812   0.00304   0.0038   1.0000   0.9893
   0.000  -0.0001   0.00812   0.00303   0.0000   1.0000   1.0000
   0.250   0.0420   0.00812   0.00304  -0.0038   0.9893   1.0000
   0.500   0.0948   0.00810   0.00306  -0.0093   0.9784   1.0000
   0.750   0.1456   0.00802   0.00303  -0.0142   0.9636   1.0000
   1.000   0.1906   0.00793   0.00299  -0.0178   0.9449   1.0000
   1.250   0.2246   0.00786   0.00296  -0.0191   0.9228   1.0000
   1.500   0.2494   0.00784   0.00300  -0.0183   0.9012   1.0000
   1.750   0.2671   0.00786   0.00299  -0.0159   0.8737   1.0000
   2.000   0.2833   0.00790   0.00299  -0.0129   0.8405   1.0000
   2.250   0.3012   0.00798   0.00300  -0.0103   0.8070   1.0000
   2.500   0.3208   0.00805   0.00302  -0.0081   0.7690   1.0000
   2.750   0.3406   0.00817   0.00303  -0.0059   0.7186   1.0000
   3.000   0.3611   0.00837   0.00310  -0.0039   0.6498   1.0000
   3.250   0.3795   0.00891   0.00310  -0.0017   0.5023   1.0000
   3.500   0.3945   0.01059   0.00349   0.0000   0.2265   1.0000
   3.750   0.4134   0.01247   0.00451   0.0010   0.0735   1.0000
   4.000   0.4359   0.01363   0.00563   0.0019   0.0587   1.0000
   4.250   0.4602   0.01451   0.00661   0.0028   0.0524   1.0000
   4.500   0.4832   0.01587   0.00795   0.0036   0.0451   1.0000
   4.750   0.5083   0.01679   0.00897   0.0043   0.0373   1.0000
   5.000   0.5324   0.01889   0.01124   0.0054   0.0303   1.0000
   5.250   0.5576   0.02064   0.01330   0.0063   0.0261   1.0000
   5.500   0.5801   0.02294   0.01588   0.0070   0.0205   1.0000
   5.750   0.6035   0.02586   0.01928   0.0082   0.0196   1.0000
   6.000   0.6242   0.02963   0.02358   0.0095   0.0199   1.0000
   6.250   0.6402   0.03444   0.02889   0.0106   0.0211   1.0000
   7.250   0.6478   0.04697   0.04359   0.0132   0.0397   1.0000
   7.500   0.6465   0.05211   0.04888   0.0123   0.0386   1.0000
   7.750   0.6406   0.05729   0.05418   0.0111   0.0379   1.0000
   8.000   0.6273   0.06239   0.05936   0.0093   0.0377   1.0000
   8.250   0.6053   0.06892   0.06591   0.0038   0.0384   1.0000
   8.500   0.5933   0.07525   0.07221  -0.0005   0.0383   1.0000
   8.750   0.5865   0.08092   0.07785  -0.0035   0.0380   1.0000
   9.000   0.5823   0.08611   0.08301  -0.0057   0.0373   1.0000
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