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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.93 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1010-il-1000000.txt
Download as CSV file: xf-hq1010-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7790   0.05063   0.04875  -0.0427   1.0000   0.0056
 -11.000  -0.8045   0.04440   0.04233  -0.0466   1.0000   0.0056
 -10.750  -0.8697   0.03641   0.03388  -0.0447   1.0000   0.0053
 -10.500  -0.8926   0.03143   0.02847  -0.0416   1.0000   0.0052
 -10.250  -0.8965   0.02775   0.02441  -0.0392   1.0000   0.0051
 -10.000  -0.8901   0.02508   0.02144  -0.0374   1.0000   0.0051
  -9.750  -0.8782   0.02308   0.01920  -0.0359   1.0000   0.0052
  -9.500  -0.8633   0.02144   0.01736  -0.0345   1.0000   0.0053
  -9.250  -0.8464   0.02008   0.01583  -0.0333   1.0000   0.0054
  -9.000  -0.8280   0.01900   0.01462  -0.0321   1.0000   0.0057
  -8.750  -0.8098   0.01786   0.01334  -0.0308   1.0000   0.0059
  -8.500  -0.7905   0.01697   0.01232  -0.0296   1.0000   0.0062
  -8.250  -0.7709   0.01616   0.01140  -0.0283   1.0000   0.0065
  -8.000  -0.7516   0.01542   0.01057  -0.0269   1.0000   0.0067
  -7.750  -0.7317   0.01496   0.01005  -0.0256   1.0000   0.0069
  -7.500  -0.7025   0.01369   0.00863  -0.0265   0.9975   0.0072
  -7.250  -0.6705   0.01240   0.00718  -0.0280   0.9935   0.0078
  -7.000  -0.6384   0.01172   0.00644  -0.0292   0.9888   0.0084
  -6.750  -0.6042   0.01119   0.00585  -0.0309   0.9849   0.0092
  -6.500  -0.5700   0.01079   0.00542  -0.0324   0.9800   0.0102
  -6.250  -0.5377   0.01011   0.00465  -0.0336   0.9723   0.0121
  -6.000  -0.5059   0.00969   0.00421  -0.0346   0.9628   0.0144
  -5.750  -0.4766   0.00925   0.00375  -0.0350   0.9502   0.0194
  -5.500  -0.4498   0.00893   0.00343  -0.0348   0.9352   0.0281
  -5.250  -0.4235   0.00874   0.00319  -0.0344   0.9207   0.0342
  -5.000  -0.3976   0.00854   0.00298  -0.0340   0.9077   0.0413
  -4.750  -0.3716   0.00836   0.00276  -0.0336   0.8960   0.0483
  -4.500  -0.3451   0.00821   0.00257  -0.0333   0.8852   0.0548
  -4.250  -0.3188   0.00799   0.00236  -0.0331   0.8750   0.0676
  -4.000  -0.2927   0.00771   0.00215  -0.0328   0.8656   0.0917
  -3.500  -0.2411   0.00701   0.00176  -0.0323   0.8473   0.1908
  -3.250  -0.2149   0.00671   0.00160  -0.0320   0.8388   0.2396
  -3.000  -0.1889   0.00639   0.00144  -0.0318   0.8297   0.2960
  -2.750  -0.1637   0.00589   0.00127  -0.0316   0.8209   0.3998
  -2.500  -0.1377   0.00559   0.00117  -0.0313   0.8129   0.4716
  -2.250  -0.1107   0.00540   0.00110  -0.0312   0.8045   0.5201
  -2.000  -0.0835   0.00529   0.00105  -0.0310   0.7957   0.5559
  -1.500  -0.0288   0.00514   0.00098  -0.0306   0.7750   0.6164
  -1.250  -0.0011   0.00510   0.00095  -0.0305   0.7655   0.6350
  -1.000   0.0264   0.00509   0.00094  -0.0304   0.7559   0.6566
  -0.750   0.0542   0.00506   0.00093  -0.0303   0.7460   0.6739
  -0.500   0.0821   0.00506   0.00092  -0.0302   0.7359   0.6868
  -0.250   0.1099   0.00507   0.00091  -0.0301   0.7251   0.6976
   0.250   0.1657   0.00507   0.00092  -0.0300   0.7048   0.7196
   0.500   0.1937   0.00509   0.00093  -0.0299   0.6948   0.7304
   0.750   0.2215   0.00512   0.00095  -0.0298   0.6846   0.7411
   1.000   0.2491   0.00513   0.00097  -0.0297   0.6731   0.7521
   1.250   0.2769   0.00515   0.00101  -0.0296   0.6610   0.7629
   1.500   0.3046   0.00520   0.00103  -0.0295   0.6467   0.7725
   1.750   0.3319   0.00525   0.00107  -0.0294   0.6297   0.7813
   2.000   0.3594   0.00530   0.00110  -0.0292   0.6104   0.7901
   2.250   0.3866   0.00539   0.00116  -0.0291   0.5886   0.7998
   2.500   0.4133   0.00549   0.00122  -0.0288   0.5605   0.8095
   2.750   0.4393   0.00568   0.00129  -0.0284   0.5186   0.8197
   3.000   0.4650   0.00590   0.00139  -0.0281   0.4742   0.8308
   3.250   0.4906   0.00613   0.00152  -0.0277   0.4315   0.8429
   3.500   0.5154   0.00643   0.00167  -0.0271   0.3782   0.8565
   3.750   0.5391   0.00680   0.00186  -0.0265   0.3175   0.8725
   4.000   0.5630   0.00707   0.00204  -0.0257   0.2775   0.8940
   4.500   0.6228   0.00740   0.00240  -0.0267   0.2318   0.9704
   4.750   0.6625   0.00771   0.00260  -0.0296   0.2007   1.0000
   5.000   0.6872   0.00803   0.00279  -0.0292   0.1715   1.0000
   5.250   0.7115   0.00842   0.00304  -0.0287   0.1397   1.0000
   5.500   0.7358   0.00882   0.00330  -0.0282   0.1122   1.0000
   5.750   0.7601   0.00923   0.00359  -0.0277   0.0876   1.0000
   6.000   0.7847   0.00960   0.00388  -0.0273   0.0692   1.0000
   6.250   0.8095   0.00996   0.00417  -0.0269   0.0561   1.0000
   6.500   0.8344   0.01030   0.00449  -0.0265   0.0462   1.0000
   6.750   0.8590   0.01068   0.00482  -0.0260   0.0366   1.0000
   7.000   0.8833   0.01109   0.00518  -0.0255   0.0276   1.0000
   7.250   0.9079   0.01146   0.00553  -0.0251   0.0221   1.0000
   7.500   0.9318   0.01192   0.00595  -0.0246   0.0160   1.0000
   7.750   0.9550   0.01245   0.00648  -0.0239   0.0110   1.0000
   8.000   0.9775   0.01309   0.00716  -0.0231   0.0082   1.0000
   8.250   1.0010   0.01357   0.00769  -0.0225   0.0073   1.0000
   8.500   1.0238   0.01412   0.00828  -0.0218   0.0065   1.0000
   8.750   1.0432   0.01509   0.00935  -0.0205   0.0057   1.0000
   9.000   1.0646   0.01577   0.01011  -0.0196   0.0055   1.0000
   9.250   1.0859   0.01641   0.01083  -0.0188   0.0053   1.0000
   9.500   1.1064   0.01713   0.01163  -0.0178   0.0050   1.0000
   9.750   1.1259   0.01791   0.01251  -0.0167   0.0047   1.0000
  10.000   1.1442   0.01880   0.01349  -0.0154   0.0045   1.0000
  10.250   1.1616   0.01971   0.01449  -0.0141   0.0043   1.0000
  10.500   1.1771   0.02075   0.01564  -0.0125   0.0042   1.0000
  10.750   1.1910   0.02187   0.01688  -0.0108   0.0041   1.0000
  11.000   1.2030   0.02307   0.01820  -0.0089   0.0041   1.0000
  11.250   1.2112   0.02445   0.01971  -0.0065   0.0039   1.0000
  11.500   1.2165   0.02563   0.02100  -0.0036   0.0039   1.0000
  11.750   1.2176   0.02708   0.02258  -0.0005   0.0038   1.0000
  12.000   1.2149   0.02897   0.02462   0.0026   0.0037   1.0000
  12.250   1.2088   0.03125   0.02707   0.0053   0.0036   1.0000
  12.500   1.2025   0.03375   0.02977   0.0074   0.0036   1.0000
  12.750   1.2001   0.03606   0.03222   0.0088   0.0037   1.0000
  13.000   1.1832   0.04007   0.03645   0.0099   0.0036   1.0000
  13.250   1.1748   0.04346   0.04001   0.0101   0.0036   1.0000
  13.500   1.1618   0.04772   0.04445   0.0095   0.0036   1.0000
  13.750   1.1504   0.05215   0.04904   0.0082   0.0036   1.0000
  14.000   1.1386   0.05706   0.05409   0.0062   0.0036   1.0000
  14.250   1.1259   0.06257   0.05975   0.0034   0.0036   1.0000
  14.500   1.1178   0.06779   0.06509   0.0004   0.0036   1.0000
  14.750   1.0996   0.07532   0.07278  -0.0042   0.0036   1.0000
  15.000   1.0816   0.08348   0.08108  -0.0093   0.0036   1.0000
  15.250   1.0708   0.09061   0.08832  -0.0137   0.0036   1.0000
  15.500   1.0531   0.09948   0.09731  -0.0191   0.0037   1.0000
  15.750   1.0366   0.10826   0.10620  -0.0243   0.0037   1.0000
  16.000   1.0184   0.11758   0.11561  -0.0297   0.0037   1.0000
  16.250   0.9930   0.12928   0.12744  -0.0362   0.0039   1.0000
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