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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.01 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3512-il-1000000.txt
Download as CSV file: xf-hq3512-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3229   0.09330   0.09174  -0.0514   0.9974   0.0127
  -9.750  -0.4880   0.02950   0.02696  -0.1102   0.9615   0.0077
  -9.500  -0.4848   0.02502   0.02199  -0.1112   0.9461   0.0077
  -9.250  -0.4734   0.02254   0.01914  -0.1105   0.9344   0.0077
  -9.000  -0.4560   0.02094   0.01727  -0.1099   0.9254   0.0078
  -8.750  -0.4367   0.01973   0.01584  -0.1093   0.9166   0.0079
  -8.500  -0.4247   0.01666   0.01231  -0.1081   0.9077   0.0082
  -8.250  -0.4040   0.01532   0.01077  -0.1075   0.9005   0.0085
  -8.000  -0.3809   0.01446   0.00979  -0.1071   0.8941   0.0088
  -7.750  -0.3567   0.01377   0.00899  -0.1067   0.8874   0.0090
  -7.500  -0.3320   0.01314   0.00824  -0.1063   0.8816   0.0092
  -7.250  -0.3071   0.01252   0.00753  -0.1060   0.8753   0.0095
  -7.000  -0.2817   0.01198   0.00687  -0.1057   0.8694   0.0097
  -6.750  -0.2561   0.01145   0.00626  -0.1054   0.8636   0.0100
  -6.500  -0.2302   0.01096   0.00568  -0.1051   0.8575   0.0103
  -6.250  -0.2039   0.01058   0.00521  -0.1049   0.8520   0.0106
  -6.000  -0.1772   0.01022   0.00479  -0.1048   0.8460   0.0110
  -5.750  -0.1515   0.00962   0.00408  -0.1045   0.8403   0.0121
  -5.500  -0.1245   0.00930   0.00372  -0.1044   0.8346   0.0131
  -5.250  -0.0973   0.00903   0.00340  -0.1043   0.8287   0.0142
  -5.000  -0.0701   0.00873   0.00306  -0.1041   0.8233   0.0171
  -4.750  -0.0426   0.00848   0.00285  -0.1041   0.8173   0.0257
  -4.500  -0.0149   0.00837   0.00273  -0.1041   0.8115   0.0326
  -4.250   0.0128   0.00819   0.00256  -0.1041   0.8058   0.0376
  -4.000   0.0407   0.00809   0.00244  -0.1041   0.7996   0.0413
  -3.750   0.0685   0.00798   0.00228  -0.1041   0.7940   0.0454
  -3.500   0.0964   0.00782   0.00214  -0.1041   0.7874   0.0512
  -3.250   0.1241   0.00774   0.00199  -0.1040   0.7804   0.0556
  -3.000   0.1518   0.00756   0.00185  -0.1040   0.7719   0.0667
  -2.750   0.1792   0.00739   0.00171  -0.1039   0.7640   0.0883
  -2.500   0.2065   0.00712   0.00157  -0.1039   0.7557   0.1355
  -2.250   0.2332   0.00671   0.00144  -0.1040   0.7488   0.2343
  -2.000   0.2594   0.00613   0.00131  -0.1041   0.7415   0.3865
  -1.750   0.2863   0.00585   0.00126  -0.1041   0.7351   0.4819
  -1.500   0.3140   0.00573   0.00124  -0.1041   0.7278   0.5314
  -1.250   0.3417   0.00570   0.00124  -0.1040   0.7211   0.5632
  -1.000   0.3699   0.00566   0.00124  -0.1040   0.7139   0.5891
  -0.750   0.3976   0.00568   0.00125  -0.1039   0.7067   0.6100
  -0.500   0.4258   0.00568   0.00126  -0.1039   0.6987   0.6280
  -0.250   0.4535   0.00572   0.00128  -0.1038   0.6913   0.6441
   0.000   0.4814   0.00574   0.00132  -0.1038   0.6833   0.6628
   0.250   0.5091   0.00578   0.00135  -0.1037   0.6755   0.6771
   0.500   0.5368   0.00582   0.00138  -0.1036   0.6669   0.6867
   0.750   0.5647   0.00586   0.00141  -0.1036   0.6590   0.6946
   1.000   0.5924   0.00591   0.00144  -0.1035   0.6505   0.7011
   1.250   0.6204   0.00595   0.00147  -0.1035   0.6416   0.7073
   1.500   0.6477   0.00601   0.00151  -0.1034   0.6315   0.7136
   2.000   0.7023   0.00614   0.00160  -0.1031   0.6078   0.7262
   2.250   0.7294   0.00623   0.00166  -0.1030   0.5943   0.7332
   2.500   0.7558   0.00634   0.00173  -0.1027   0.5779   0.7397
   2.750   0.7820   0.00647   0.00181  -0.1024   0.5588   0.7471
   3.000   0.8077   0.00662   0.00191  -0.1020   0.5363   0.7543
   3.250   0.8326   0.00683   0.00203  -0.1015   0.5090   0.7624
   3.500   0.8566   0.00709   0.00218  -0.1008   0.4775   0.7704
   3.750   0.8801   0.00741   0.00236  -0.1001   0.4439   0.7793
   4.000   0.9033   0.00771   0.00256  -0.0993   0.4107   0.7886
   4.250   0.9265   0.00803   0.00277  -0.0985   0.3786   0.7987
   4.500   0.9492   0.00837   0.00299  -0.0977   0.3458   0.8102
   5.000   0.9940   0.00898   0.00345  -0.0959   0.2927   0.8404
   5.250   1.0164   0.00916   0.00366  -0.0950   0.2783   0.8664
   5.500   1.0440   0.00922   0.00387  -0.0951   0.2653   1.0000
   5.750   1.0682   0.00950   0.00410  -0.0946   0.2548   1.0000
   6.000   1.0935   0.00970   0.00429  -0.0942   0.2480   1.0000
   6.250   1.1175   0.00997   0.00453  -0.0937   0.2399   1.0000
   6.500   1.1425   0.01016   0.00472  -0.0933   0.2332   1.0000
   6.750   1.1661   0.01043   0.00496  -0.0927   0.2249   1.0000
   7.000   1.1902   0.01066   0.00518  -0.0922   0.2160   1.0000
   7.250   1.2136   0.01092   0.00542  -0.0915   0.2058   1.0000
   7.500   1.2362   0.01122   0.00568  -0.0907   0.1953   1.0000
   7.750   1.2580   0.01155   0.00595  -0.0899   0.1814   1.0000
   8.000   1.2789   0.01192   0.00626  -0.0888   0.1658   1.0000
   8.250   1.2980   0.01237   0.00662  -0.0875   0.1475   1.0000
   8.500   1.3153   0.01290   0.00704  -0.0859   0.1299   1.0000
   8.750   1.3308   0.01342   0.00747  -0.0839   0.1136   1.0000
   9.000   1.3447   0.01396   0.00795  -0.0817   0.0984   1.0000
   9.250   1.3577   0.01457   0.00848  -0.0793   0.0836   1.0000
   9.500   1.3695   0.01526   0.00907  -0.0768   0.0687   1.0000
   9.750   1.3812   0.01598   0.00971  -0.0745   0.0555   1.0000
  10.000   1.3917   0.01678   0.01043  -0.0720   0.0410   1.0000
  10.250   1.3973   0.01791   0.01143  -0.0689   0.0233   1.0000
  10.500   1.4009   0.01921   0.01262  -0.0657   0.0096   1.0000
  10.750   1.4114   0.02011   0.01354  -0.0636   0.0068   1.0000
  11.000   1.4232   0.02096   0.01442  -0.0617   0.0058   1.0000
  11.250   1.4351   0.02182   0.01535  -0.0598   0.0053   1.0000
  11.500   1.4459   0.02277   0.01637  -0.0580   0.0048   1.0000
  11.750   1.4564   0.02377   0.01743  -0.0562   0.0046   1.0000
  12.000   1.4658   0.02487   0.01859  -0.0544   0.0044   1.0000
  12.250   1.4717   0.02627   0.02008  -0.0524   0.0041   1.0000
  12.500   1.4765   0.02782   0.02173  -0.0504   0.0039   1.0000
  12.750   1.4846   0.02912   0.02312  -0.0489   0.0039   1.0000
  13.000   1.4907   0.03064   0.02472  -0.0473   0.0038   1.0000
  13.250   1.4969   0.03221   0.02638  -0.0459   0.0038   1.0000
  13.500   1.5007   0.03402   0.02829  -0.0445   0.0037   1.0000
  13.750   1.5031   0.03605   0.03041  -0.0431   0.0036   1.0000
  14.000   1.5061   0.03807   0.03253  -0.0420   0.0036   1.0000
  14.250   1.5080   0.04028   0.03483  -0.0410   0.0035   1.0000
  14.500   1.5072   0.04287   0.03753  -0.0402   0.0035   1.0000
  14.750   1.5051   0.04572   0.04049  -0.0395   0.0035   1.0000
  15.000   1.5033   0.04867   0.04354  -0.0391   0.0034   1.0000
  15.250   1.4999   0.05194   0.04693  -0.0389   0.0034   1.0000
  15.500   1.4963   0.05541   0.05051  -0.0390   0.0033   1.0000
  15.750   1.4907   0.05927   0.05447  -0.0394   0.0033   1.0000
  16.000   1.4843   0.06343   0.05876  -0.0401   0.0032   1.0000
  16.250   1.4752   0.06820   0.06365  -0.0411   0.0032   1.0000
  16.500   1.4671   0.07300   0.06857  -0.0425   0.0032   1.0000
  16.750   1.4553   0.07862   0.07434  -0.0444   0.0032   1.0000
  17.000   1.4448   0.08425   0.08009  -0.0465   0.0032   1.0000
  17.250   1.4317   0.09054   0.08651  -0.0490   0.0032   1.0000
  17.500   1.4186   0.09699   0.09309  -0.0518   0.0031   1.0000
  17.750   1.4063   0.10350   0.09972  -0.0548   0.0031   1.0000
  18.000   1.3926   0.11039   0.10674  -0.0581   0.0031   1.0000
  18.250   1.3789   0.11738   0.11386  -0.0616   0.0031   1.0000
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