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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 500,000
Max Cl/Cd: 79.61 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq209-il-500000-n5.txt
Download as CSV file: xf-hq209-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4774   0.08384   0.08161  -0.0284   1.0000   0.0043
  -9.000  -0.4798   0.07944   0.07724  -0.0307   1.0000   0.0042
  -8.750  -0.4876   0.07399   0.07184  -0.0338   1.0000   0.0041
  -8.500  -0.4984   0.06848   0.06638  -0.0373   1.0000   0.0041
  -8.250  -0.5140   0.06174   0.05966  -0.0443   1.0000   0.0041
  -8.000  -0.5264   0.05500   0.05283  -0.0480   1.0000   0.0040
  -7.750  -0.5291   0.04657   0.04417  -0.0527   0.9947   0.0040
  -7.500  -0.5309   0.02630   0.02263  -0.0601   0.9795   0.0039
  -7.250  -0.5064   0.02123   0.01683  -0.0618   0.9731   0.0042
  -7.000  -0.4796   0.01886   0.01403  -0.0625   0.9658   0.0045
  -6.750  -0.4497   0.01734   0.01221  -0.0635   0.9599   0.0047
  -6.500  -0.4235   0.01536   0.00992  -0.0638   0.9516   0.0052
  -6.250  -0.3945   0.01445   0.00887  -0.0644   0.9445   0.0056
  -6.000  -0.3671   0.01386   0.00819  -0.0646   0.9355   0.0062
  -5.750  -0.3396   0.01329   0.00752  -0.0646   0.9271   0.0069
  -5.500  -0.3125   0.01274   0.00686  -0.0646   0.9187   0.0077
  -5.250  -0.2864   0.01211   0.00606  -0.0642   0.9101   0.0081
  -5.000  -0.2610   0.01127   0.00507  -0.0638   0.9023   0.0088
  -4.750  -0.2351   0.01070   0.00439  -0.0635   0.8941   0.0098
  -4.500  -0.2086   0.01035   0.00399  -0.0633   0.8869   0.0113
  -4.250  -0.1819   0.01005   0.00360  -0.0630   0.8794   0.0128
  -4.000  -0.1550   0.00971   0.00316  -0.0628   0.8725   0.0146
  -3.750  -0.1282   0.00939   0.00281  -0.0625   0.8654   0.0219
  -3.500  -0.1011   0.00916   0.00257  -0.0624   0.8588   0.0332
  -3.250  -0.0740   0.00896   0.00236  -0.0623   0.8519   0.0439
  -3.000  -0.0470   0.00872   0.00218  -0.0622   0.8452   0.0647
  -2.750  -0.0202   0.00842   0.00199  -0.0621   0.8380   0.1021
  -2.500   0.0067   0.00813   0.00181  -0.0620   0.8308   0.1493
  -2.250   0.0331   0.00775   0.00164  -0.0619   0.8229   0.2276
  -2.000   0.0592   0.00727   0.00148  -0.0619   0.8142   0.3335
  -1.750   0.0852   0.00686   0.00137  -0.0617   0.8055   0.4433
  -1.500   0.1118   0.00663   0.00131  -0.0615   0.7962   0.5146
  -1.250   0.1382   0.00646   0.00129  -0.0612   0.7851   0.5791
  -1.000   0.1649   0.00638   0.00127  -0.0608   0.7724   0.6206
  -0.750   0.1915   0.00633   0.00127  -0.0604   0.7594   0.6573
  -0.500   0.2185   0.00631   0.00125  -0.0601   0.7474   0.6825
  -0.250   0.2454   0.00630   0.00125  -0.0598   0.7349   0.7040
   0.000   0.2724   0.00632   0.00125  -0.0595   0.7213   0.7229
   0.250   0.2996   0.00634   0.00125  -0.0593   0.7068   0.7337
   0.500   0.3267   0.00638   0.00124  -0.0591   0.6908   0.7427
   0.750   0.3540   0.00643   0.00126  -0.0589   0.6764   0.7524
   1.000   0.3811   0.00648   0.00128  -0.0587   0.6627   0.7623
   1.250   0.4081   0.00654   0.00132  -0.0584   0.6466   0.7722
   1.500   0.4349   0.00661   0.00136  -0.0581   0.6298   0.7829
   1.750   0.4616   0.00668   0.00141  -0.0579   0.6112   0.7942
   2.000   0.4879   0.00678   0.00147  -0.0575   0.5886   0.8065
   2.250   0.5138   0.00689   0.00156  -0.0571   0.5632   0.8196
   2.500   0.5391   0.00704   0.00165  -0.0565   0.5327   0.8343
   2.750   0.5638   0.00721   0.00176  -0.0559   0.4971   0.8510
   3.000   0.5875   0.00741   0.00189  -0.0551   0.4574   0.8732
   3.250   0.6106   0.00767   0.00205  -0.0541   0.4086   0.9114
   3.500   0.6448   0.00822   0.00231  -0.0559   0.3271   1.0000
   3.750   0.6686   0.00873   0.00256  -0.0554   0.2734   1.0000
   4.000   0.6942   0.00904   0.00277  -0.0552   0.2503   1.0000
   4.250   0.7203   0.00930   0.00298  -0.0550   0.2340   1.0000
   4.500   0.7459   0.00960   0.00322  -0.0547   0.2134   1.0000
   4.750   0.7710   0.00995   0.00347  -0.0544   0.1856   1.0000
   5.000   0.7951   0.01043   0.00375  -0.0540   0.1451   1.0000
   5.250   0.8176   0.01110   0.00415  -0.0533   0.0955   1.0000
   5.500   0.8410   0.01167   0.00455  -0.0528   0.0646   1.0000
   6.000   0.8890   0.01261   0.00535  -0.0519   0.0339   1.0000
   6.250   0.9139   0.01297   0.00571  -0.0515   0.0272   1.0000
   6.500   0.9382   0.01339   0.00611  -0.0510   0.0213   1.0000
   6.750   0.9622   0.01385   0.00656  -0.0505   0.0152   1.0000
   7.000   0.9850   0.01444   0.00712  -0.0498   0.0068   1.0000
   7.250   1.0081   0.01499   0.00770  -0.0492   0.0048   1.0000
   7.500   1.0308   0.01557   0.00835  -0.0484   0.0041   1.0000
   7.750   1.0529   0.01622   0.00911  -0.0476   0.0034   1.0000
   8.000   1.0747   0.01688   0.00988  -0.0468   0.0031   1.0000
   8.250   1.0958   0.01764   0.01076  -0.0458   0.0029   1.0000
   8.500   1.1159   0.01847   0.01171  -0.0448   0.0027   1.0000
   8.750   1.1363   0.01924   0.01259  -0.0438   0.0026   1.0000
   9.000   1.1554   0.02010   0.01357  -0.0426   0.0025   1.0000
   9.250   1.1733   0.02108   0.01467  -0.0413   0.0024   1.0000
   9.500   1.1902   0.02209   0.01581  -0.0399   0.0023   1.0000
   9.750   1.2051   0.02327   0.01713  -0.0383   0.0022   1.0000
  10.000   1.2185   0.02453   0.01858  -0.0364   0.0021   1.0000
  10.250   1.2300   0.02587   0.02008  -0.0344   0.0020   1.0000
  10.500   1.2392   0.02719   0.02156  -0.0321   0.0020   1.0000
  10.750   1.2450   0.02860   0.02312  -0.0293   0.0020   1.0000
  11.000   1.2479   0.03024   0.02494  -0.0265   0.0020   1.0000
  11.250   1.2501   0.03198   0.02685  -0.0239   0.0019   1.0000
  11.500   1.2498   0.03399   0.02905  -0.0214   0.0019   1.0000
  11.750   1.2488   0.03615   0.03140  -0.0193   0.0019   1.0000
  12.000   1.2451   0.03869   0.03413  -0.0176   0.0019   1.0000
  12.250   1.2406   0.04146   0.03709  -0.0162   0.0019   1.0000
  12.500   1.2337   0.04468   0.04051  -0.0154   0.0019   1.0000
  12.750   1.2251   0.04833   0.04437  -0.0152   0.0019   1.0000
  13.000   1.2142   0.05260   0.04883  -0.0157   0.0019   1.0000
  13.250   1.2011   0.05755   0.05398  -0.0171   0.0019   1.0000
  13.500   1.1882   0.06297   0.05959  -0.0193   0.0019   1.0000
  13.750   1.1716   0.06958   0.06640  -0.0227   0.0019   1.0000
  14.000   1.1551   0.07692   0.07391  -0.0270   0.0019   1.0000
  14.250   1.1364   0.08542   0.08259  -0.0322   0.0019   1.0000
  14.500   1.1178   0.09461   0.09194  -0.0378   0.0019   1.0000
  14.750   1.0961   0.10503   0.10251  -0.0441   0.0019   1.0000
  15.000   1.0745   0.11563   0.11324  -0.0502   0.0019   1.0000
  15.250   1.0529   0.12654   0.12426  -0.0563   0.0020   1.0000
  15.500   1.0319   0.13768   0.13549  -0.0624   0.0020   1.0000
  15.750   1.0058   0.15114   0.14904  -0.0694   0.0021   1.0000
  16.000   0.9758   0.16700   0.16496  -0.0773   0.0022   1.0000
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