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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 500,000
Max Cl/Cd: 79.14 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1010-il-500000.txt
Download as CSV file: xf-hq1010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.7559   0.03821   0.03489  -0.0406   1.0000   0.0102
  -9.000  -0.7629   0.03346   0.02972  -0.0386   1.0000   0.0101
  -8.750  -0.7609   0.02951   0.02535  -0.0366   1.0000   0.0101
  -8.500  -0.7508   0.02674   0.02222  -0.0349   1.0000   0.0102
  -8.250  -0.7359   0.02484   0.02003  -0.0333   1.0000   0.0104
  -8.000  -0.7223   0.02245   0.01732  -0.0315   1.0000   0.0106
  -7.750  -0.7107   0.01943   0.01396  -0.0294   1.0000   0.0111
  -7.500  -0.6944   0.01789   0.01227  -0.0276   1.0000   0.0115
  -7.250  -0.6766   0.01704   0.01136  -0.0261   1.0000   0.0122
  -7.000  -0.6599   0.01632   0.01058  -0.0243   1.0000   0.0128
  -6.750  -0.6430   0.01580   0.00998  -0.0225   0.9998   0.0139
  -6.500  -0.6076   0.01482   0.00888  -0.0244   0.9962   0.0149
  -6.250  -0.5747   0.01334   0.00725  -0.0260   0.9918   0.0168
  -6.000  -0.5399   0.01261   0.00649  -0.0278   0.9871   0.0195
  -5.750  -0.5035   0.01189   0.00570  -0.0298   0.9835   0.0238
  -5.500  -0.4685   0.01141   0.00522  -0.0316   0.9787   0.0326
  -5.250  -0.4334   0.01097   0.00478  -0.0333   0.9733   0.0426
  -5.000  -0.3974   0.01049   0.00430  -0.0353   0.9689   0.0538
  -4.750  -0.3667   0.01007   0.00391  -0.0360   0.9595   0.0649
  -4.500  -0.3352   0.00969   0.00355  -0.0369   0.9511   0.0801
  -4.250  -0.3066   0.00919   0.00318  -0.0372   0.9414   0.1134
  -4.000  -0.2816   0.00860   0.00287  -0.0369   0.9297   0.1830
  -3.750  -0.2567   0.00813   0.00262  -0.0365   0.9187   0.2520
  -3.500  -0.2328   0.00756   0.00236  -0.0360   0.9083   0.3434
  -3.250  -0.2094   0.00702   0.00217  -0.0353   0.8986   0.4547
  -3.000  -0.1847   0.00674   0.00209  -0.0346   0.8881   0.5237
  -2.750  -0.1588   0.00661   0.00203  -0.0341   0.8787   0.5683
  -2.500  -0.1325   0.00655   0.00198  -0.0336   0.8699   0.6020
  -2.250  -0.1062   0.00648   0.00195  -0.0331   0.8602   0.6321
  -2.000  -0.0794   0.00646   0.00192  -0.0327   0.8513   0.6545
  -1.750  -0.0524   0.00646   0.00189  -0.0324   0.8429   0.6730
  -1.500  -0.0257   0.00643   0.00190  -0.0320   0.8340   0.6936
  -1.250   0.0012   0.00644   0.00188  -0.0315   0.8253   0.7111
  -1.000   0.0281   0.00644   0.00185  -0.0311   0.8150   0.7242
  -0.750   0.0552   0.00642   0.00183  -0.0308   0.8042   0.7351
  -0.500   0.0824   0.00642   0.00181  -0.0305   0.7943   0.7468
  -0.250   0.1095   0.00643   0.00178  -0.0302   0.7848   0.7589
   0.000   0.1366   0.00643   0.00178  -0.0299   0.7741   0.7705
   0.250   0.1636   0.00641   0.00178  -0.0295   0.7632   0.7820
   0.500   0.1905   0.00641   0.00179  -0.0291   0.7527   0.7935
   0.750   0.2176   0.00642   0.00178  -0.0288   0.7433   0.8039
   1.000   0.2450   0.00642   0.00179  -0.0287   0.7326   0.8140
   1.250   0.2721   0.00641   0.00182  -0.0283   0.7220   0.8234
   1.500   0.2991   0.00641   0.00183  -0.0280   0.7111   0.8334
   1.750   0.3260   0.00642   0.00184  -0.0277   0.6991   0.8443
   2.250   0.3788   0.00643   0.00190  -0.0268   0.6701   0.8684
   2.500   0.4047   0.00643   0.00193  -0.0262   0.6527   0.8826
   2.750   0.4302   0.00644   0.00197  -0.0256   0.6336   0.8993
   3.000   0.4561   0.00647   0.00202  -0.0249   0.6106   0.9192
   3.250   0.4855   0.00657   0.00209  -0.0251   0.5774   0.9442
   3.500   0.5211   0.00677   0.00217  -0.0268   0.5337   0.9680
   3.750   0.5595   0.00707   0.00230  -0.0293   0.4802   0.9875
   4.000   0.5908   0.00754   0.00249  -0.0305   0.4127   1.0000
   4.250   0.6121   0.00802   0.00271  -0.0295   0.3510   1.0000
   4.500   0.6345   0.00851   0.00297  -0.0288   0.2997   1.0000
   4.750   0.6583   0.00890   0.00322  -0.0282   0.2686   1.0000
   5.000   0.6828   0.00925   0.00348  -0.0277   0.2432   1.0000
   5.250   0.7070   0.00963   0.00376  -0.0272   0.2125   1.0000
   5.500   0.7311   0.01005   0.00404  -0.0268   0.1800   1.0000
   5.750   0.7549   0.01051   0.00436  -0.0262   0.1439   1.0000
   6.000   0.7779   0.01107   0.00474  -0.0256   0.1117   1.0000
   6.250   0.8012   0.01159   0.00516  -0.0250   0.0885   1.0000
   6.500   0.8247   0.01209   0.00561  -0.0244   0.0705   1.0000
   6.750   0.8483   0.01259   0.00604  -0.0239   0.0557   1.0000
   7.000   0.8717   0.01309   0.00651  -0.0233   0.0443   1.0000
   7.250   0.8948   0.01364   0.00704  -0.0226   0.0349   1.0000
   7.500   0.9168   0.01433   0.00771  -0.0218   0.0264   1.0000
   7.750   0.9370   0.01525   0.00864  -0.0207   0.0190   1.0000
   8.000   0.9599   0.01579   0.00923  -0.0200   0.0153   1.0000
   8.250   0.9779   0.01692   0.01044  -0.0186   0.0125   1.0000
   8.500   0.9987   0.01767   0.01128  -0.0176   0.0113   1.0000
   8.750   1.0186   0.01849   0.01218  -0.0165   0.0104   1.0000
   9.000   1.0369   0.01947   0.01322  -0.0153   0.0097   1.0000
   9.250   1.0504   0.02099   0.01486  -0.0134   0.0091   1.0000
   9.500   1.0607   0.02305   0.01711  -0.0112   0.0086   1.0000
   9.750   1.0776   0.02414   0.01835  -0.0098   0.0084   1.0000
  10.000   1.0920   0.02555   0.01994  -0.0082   0.0081   1.0000
  10.250   1.1045   0.02714   0.02171  -0.0064   0.0078   1.0000
  10.500   1.1140   0.02903   0.02381  -0.0043   0.0076   1.0000
  10.750   1.1193   0.03101   0.02600  -0.0018   0.0076   1.0000
  11.000   1.1202   0.03312   0.02833   0.0012   0.0075   1.0000
  11.250   1.1165   0.03560   0.03105   0.0042   0.0074   1.0000
  11.500   1.1103   0.03828   0.03397   0.0067   0.0075   1.0000
  11.750   1.1012   0.04129   0.03721   0.0087   0.0076   1.0000
  12.000   1.0871   0.04499   0.04116   0.0101   0.0076   1.0000
  12.250   1.0726   0.04898   0.04538   0.0105   0.0077   1.0000
  12.500   1.0562   0.05355   0.05016   0.0098   0.0078   1.0000
  12.750   1.0375   0.05892   0.05574   0.0080   0.0078   1.0000
  13.000   1.0162   0.06537   0.06239   0.0049   0.0079   1.0000
  13.250   0.9970   0.07229   0.06947   0.0006   0.0079   1.0000
  13.500   0.9761   0.08048   0.07783  -0.0048   0.0080   1.0000
  13.750   0.9549   0.08982   0.08731  -0.0113   0.0080   1.0000
  14.000   0.9330   0.10024   0.09787  -0.0182   0.0081   1.0000
  14.250   0.9042   0.11322   0.11096  -0.0262   0.0082   1.0000
  14.500   0.8658   0.12941   0.12720  -0.0351   0.0085   1.0000
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