Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.96 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq010-il-1000000.txt
Download as CSV file: xf-hq010-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/10 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.9114   0.11132   0.10949   0.0107   1.0000   0.0030
 -15.000  -0.9436   0.09926   0.09735   0.0043   1.0000   0.0030
 -14.750  -0.9884   0.08458   0.08254  -0.0040   1.0000   0.0030
 -14.500  -1.0166   0.07336   0.07118  -0.0110   1.0000   0.0029
 -14.250  -1.0364   0.06465   0.06233  -0.0170   1.0000   0.0029
 -14.000  -1.0606   0.05616   0.05366  -0.0227   1.0000   0.0029
 -13.750  -1.0807   0.04962   0.04694  -0.0265   1.0000   0.0029
 -13.500  -1.0946   0.04475   0.04190  -0.0286   1.0000   0.0029
 -13.250  -1.1098   0.04030   0.03728  -0.0297   1.0000   0.0029
 -13.000  -1.1245   0.03645   0.03322  -0.0297   1.0000   0.0029
 -12.750  -1.1339   0.03355   0.03014  -0.0287   1.0000   0.0029
 -12.500  -1.1413   0.03116   0.02757  -0.0268   1.0000   0.0029
 -12.250  -1.1470   0.02916   0.02541  -0.0241   1.0000   0.0029
 -12.000  -1.1518   0.02741   0.02348  -0.0206   1.0000   0.0029
 -11.750  -1.1499   0.02567   0.02155  -0.0178   1.0000   0.0029
 -11.500  -1.1408   0.02421   0.01991  -0.0159   1.0000   0.0029
 -11.250  -1.1293   0.02283   0.01836  -0.0142   1.0000   0.0029
 -11.000  -1.1164   0.02145   0.01680  -0.0125   1.0000   0.0029
 -10.750  -1.1007   0.02029   0.01550  -0.0112   1.0000   0.0029
 -10.500  -1.0836   0.01920   0.01427  -0.0099   1.0000   0.0029
 -10.250  -1.0652   0.01822   0.01316  -0.0088   1.0000   0.0030
 -10.000  -1.0457   0.01731   0.01213  -0.0078   1.0000   0.0030
  -9.750  -1.0253   0.01648   0.01119  -0.0069   1.0000   0.0031
  -9.500  -1.0038   0.01577   0.01038  -0.0061   1.0000   0.0031
  -9.250  -0.9823   0.01499   0.00950  -0.0052   1.0000   0.0033
  -9.000  -0.9608   0.01420   0.00857  -0.0044   1.0000   0.0037
  -8.750  -0.9380   0.01358   0.00791  -0.0037   1.0000   0.0044
  -8.500  -0.9156   0.01293   0.00730  -0.0030   1.0000   0.0076
  -8.250  -0.8910   0.01259   0.00702  -0.0026   1.0000   0.0115
  -8.000  -0.8655   0.01239   0.00682  -0.0023   1.0000   0.0130
  -7.750  -0.8392   0.01230   0.00674  -0.0022   1.0000   0.0137
  -7.500  -0.8151   0.01189   0.00629  -0.0017   1.0000   0.0148
  -7.250  -0.7914   0.01141   0.00576  -0.0010   1.0000   0.0165
  -7.000  -0.7668   0.01110   0.00545  -0.0006   1.0000   0.0179
  -6.750  -0.7421   0.01082   0.00517  -0.0001   1.0000   0.0192
  -6.500  -0.7175   0.01058   0.00491   0.0004   1.0000   0.0204
  -6.250  -0.6925   0.01045   0.00479   0.0009   1.0000   0.0212
  -6.000  -0.6677   0.00992   0.00424   0.0013   0.9984   0.0257
  -5.750  -0.6323   0.00961   0.00394  -0.0006   0.9890   0.0295
  -5.500  -0.5959   0.00924   0.00355  -0.0026   0.9785   0.0361
  -5.250  -0.5598   0.00889   0.00324  -0.0046   0.9655   0.0470
  -5.000  -0.5290   0.00858   0.00298  -0.0053   0.9447   0.0622
  -4.750  -0.5035   0.00835   0.00276  -0.0048   0.9200   0.0786
  -4.500  -0.4793   0.00811   0.00253  -0.0041   0.8976   0.0996
  -4.250  -0.4555   0.00771   0.00225  -0.0034   0.8794   0.1430
  -4.000  -0.4308   0.00738   0.00207  -0.0029   0.8642   0.1977
  -3.750  -0.4048   0.00720   0.00192  -0.0026   0.8499   0.2211
  -3.500  -0.3790   0.00697   0.00176  -0.0022   0.8363   0.2535
  -3.250  -0.3532   0.00669   0.00158  -0.0019   0.8241   0.2958
  -3.000  -0.3287   0.00621   0.00140  -0.0015   0.8135   0.3846
  -2.750  -0.3024   0.00594   0.00128  -0.0013   0.8038   0.4388
  -2.500  -0.2763   0.00566   0.00117  -0.0010   0.7949   0.4920
  -2.250  -0.2501   0.00544   0.00109  -0.0007   0.7860   0.5457
  -2.000  -0.2232   0.00529   0.00104  -0.0005   0.7769   0.5901
  -1.750  -0.1957   0.00521   0.00101  -0.0004   0.7690   0.6167
  -1.500  -0.1680   0.00517   0.00099  -0.0003   0.7613   0.6363
  -1.250  -0.1403   0.00513   0.00098  -0.0002   0.7536   0.6591
  -0.750  -0.0843   0.00511   0.00094  -0.0001   0.7353   0.6806
  -0.500  -0.0561   0.00512   0.00092  -0.0001   0.7254   0.6901
  -0.250  -0.0282   0.00512   0.00091   0.0000   0.7160   0.6988
   0.000   0.0000   0.00511   0.00091   0.0000   0.7073   0.7073
   0.250   0.0282   0.00512   0.00091   0.0000   0.6988   0.7161
   0.500   0.0562   0.00512   0.00092   0.0001   0.6901   0.7253
   0.750   0.0843   0.00511   0.00094   0.0001   0.6806   0.7353
   1.250   0.1403   0.00513   0.00098   0.0002   0.6590   0.7537
   1.500   0.1680   0.00517   0.00099   0.0003   0.6362   0.7613
   1.750   0.1957   0.00521   0.00101   0.0004   0.6166   0.7690
   2.000   0.2232   0.00528   0.00104   0.0005   0.5903   0.7769
   2.250   0.2501   0.00544   0.00109   0.0007   0.5463   0.7860
   2.500   0.2763   0.00566   0.00117   0.0010   0.4917   0.7948
   2.750   0.3025   0.00594   0.00128   0.0013   0.4386   0.8038
   3.000   0.3287   0.00621   0.00140   0.0015   0.3841   0.8136
   3.250   0.3532   0.00669   0.00158   0.0019   0.2958   0.8240
   3.500   0.3790   0.00697   0.00176   0.0022   0.2534   0.8364
   3.750   0.4049   0.00720   0.00192   0.0026   0.2213   0.8499
   4.000   0.4309   0.00737   0.00207   0.0029   0.1980   0.8643
   4.250   0.4554   0.00772   0.00225   0.0034   0.1413   0.8794
   4.500   0.4794   0.00811   0.00253   0.0041   0.0996   0.8976
   4.750   0.5035   0.00835   0.00276   0.0048   0.0785   0.9199
   5.000   0.5290   0.00858   0.00298   0.0053   0.0622   0.9447
   5.250   0.5598   0.00889   0.00324   0.0046   0.0467   0.9655
   5.500   0.5958   0.00924   0.00355   0.0026   0.0363   0.9786
   5.750   0.6323   0.00961   0.00394   0.0006   0.0295   0.9891
   6.000   0.6676   0.00993   0.00423  -0.0013   0.0251   0.9984
   6.250   0.6927   0.01042   0.00475  -0.0009   0.0212   1.0000
   6.500   0.7175   0.01057   0.00489  -0.0004   0.0203   1.0000
   6.750   0.7422   0.01081   0.00515   0.0001   0.0192   1.0000
   7.000   0.7669   0.01108   0.00543   0.0006   0.0177   1.0000
   7.250   0.7913   0.01142   0.00576   0.0010   0.0164   1.0000
   7.500   0.8150   0.01190   0.00629   0.0017   0.0146   1.0000
   7.750   0.8394   0.01228   0.00671   0.0022   0.0137   1.0000
   8.000   0.8653   0.01241   0.00685   0.0024   0.0130   1.0000
   8.250   0.8912   0.01256   0.00697   0.0026   0.0112   1.0000
   8.500   0.9155   0.01293   0.00730   0.0030   0.0076   1.0000
   8.750   0.9380   0.01358   0.00790   0.0037   0.0044   1.0000
   9.000   0.9607   0.01420   0.00857   0.0044   0.0037   1.0000
   9.500   1.0038   0.01574   0.01035   0.0061   0.0032   1.0000
   9.750   1.0251   0.01648   0.01119   0.0069   0.0031   1.0000
  10.000   1.0456   0.01730   0.01212   0.0078   0.0030   1.0000
  10.250   1.0650   0.01821   0.01315   0.0089   0.0030   1.0000
  10.500   1.0835   0.01919   0.01425   0.0100   0.0030   1.0000
  10.750   1.1008   0.02025   0.01545   0.0112   0.0029   1.0000
  11.000   1.1162   0.02144   0.01680   0.0126   0.0029   1.0000
  11.250   1.1299   0.02273   0.01824   0.0141   0.0029   1.0000
  11.500   1.1402   0.02425   0.01995   0.0160   0.0029   1.0000
  11.750   1.1489   0.02574   0.02162   0.0179   0.0029   1.0000
  12.000   1.1503   0.02749   0.02357   0.0208   0.0029   1.0000
  12.250   1.1472   0.02912   0.02536   0.0241   0.0029   1.0000
  12.500   1.1417   0.03110   0.02751   0.0268   0.0029   1.0000
  12.750   1.1347   0.03346   0.03005   0.0287   0.0029   1.0000
  13.000   1.1203   0.03686   0.03366   0.0298   0.0029   1.0000
  13.250   1.1137   0.03985   0.03680   0.0298   0.0029   1.0000
  13.500   1.0967   0.04448   0.04162   0.0287   0.0029   1.0000
  13.750   1.0802   0.04969   0.04702   0.0265   0.0029   1.0000
  14.000   1.0647   0.05551   0.05299   0.0231   0.0029   1.0000
  14.250   1.0355   0.06488   0.06257   0.0168   0.0029   1.0000
  14.500   1.0153   0.07375   0.07158   0.0107   0.0029   1.0000
  14.750   0.9860   0.08523   0.08321   0.0035   0.0030   1.0000
  15.000   0.9528   0.09728   0.09537  -0.0033   0.0030   1.0000
<< Back to HQ 0/10 AIRFOIL (hq010-il)

Polar data table (+)

Polar graphs


<< Back to HQ 0/10 AIRFOIL (hq010-il)