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HQ 0/7 AIRFOIL (hq07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/7 AIRFOIL (hq07-il)
Reynolds number: 1,000,000
Max Cl/Cd: 56.22 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq07-il-1000000-n5.txt
Download as CSV file: xf-hq07-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/7 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6829   0.08366   0.08212   0.0053   1.0000   0.0033
  -9.000  -0.6920   0.07712   0.07566   0.0006   1.0000   0.0032
  -8.750  -0.7057   0.06971   0.06826  -0.0072   1.0000   0.0033
  -8.500  -0.7215   0.06459   0.06308  -0.0096   1.0000   0.0033
  -8.250  -0.7291   0.05881   0.05719  -0.0115   1.0000   0.0033
  -8.000  -0.7341   0.05274   0.05096  -0.0125   1.0000   0.0032
  -7.750  -0.7358   0.04648   0.04447  -0.0127   1.0000   0.0031
  -7.500  -0.7338   0.04008   0.03777  -0.0121   1.0000   0.0030
  -7.250  -0.7284   0.03343   0.03073  -0.0108   1.0000   0.0028
  -7.000  -0.7208   0.02644   0.02319  -0.0088   1.0000   0.0026
  -6.750  -0.7071   0.02118   0.01737  -0.0070   1.0000   0.0025
  -6.500  -0.6885   0.01753   0.01325  -0.0055   1.0000   0.0023
  -6.250  -0.6675   0.01485   0.01014  -0.0042   1.0000   0.0022
  -6.000  -0.6449   0.01310   0.00813  -0.0031   1.0000   0.0021
  -5.750  -0.6214   0.01186   0.00669  -0.0023   1.0000   0.0020
  -5.500  -0.5972   0.01096   0.00564  -0.0016   1.0000   0.0020
  -5.250  -0.5723   0.01028   0.00484  -0.0010   1.0000   0.0019
  -5.000  -0.5470   0.00974   0.00419  -0.0005   1.0000   0.0019
  -4.750  -0.5215   0.00929   0.00365  -0.0001   1.0000   0.0019
  -4.500  -0.4958   0.00892   0.00321   0.0004   1.0000   0.0019
  -4.250  -0.4645   0.00860   0.00282  -0.0005   0.9907   0.0019
  -4.000  -0.4306   0.00833   0.00248  -0.0019   0.9762   0.0020
  -3.750  -0.3962   0.00810   0.00214  -0.0033   0.9596   0.0024
  -3.500  -0.3661   0.00792   0.00193  -0.0038   0.9352   0.0036
  -3.250  -0.3407   0.00777   0.00174  -0.0032   0.9041   0.0096
  -3.000  -0.3154   0.00767   0.00159  -0.0026   0.8778   0.0167
  -2.750  -0.2903   0.00736   0.00140  -0.0021   0.8556   0.0581
  -2.250  -0.2381   0.00695   0.00111  -0.0015   0.8175   0.1269
  -2.000  -0.2117   0.00669   0.00094  -0.0014   0.8017   0.1819
  -1.750  -0.1853   0.00643   0.00083  -0.0012   0.7864   0.2387
  -1.500  -0.1604   0.00581   0.00068  -0.0010   0.7734   0.3797
  -1.250  -0.1353   0.00525   0.00058  -0.0008   0.7622   0.5174
  -1.000  -0.1091   0.00501   0.00054  -0.0005   0.7496   0.5923
  -0.750  -0.0823   0.00491   0.00053  -0.0003   0.7349   0.6364
  -0.500  -0.0549   0.00490   0.00051  -0.0002   0.7181   0.6529
  -0.250  -0.0275   0.00491   0.00049  -0.0001   0.7002   0.6684
   0.000   0.0001   0.00491   0.00049   0.0000   0.6839   0.6840
   0.250   0.0276   0.00491   0.00049   0.0001   0.6684   0.7002
   0.500   0.0550   0.00490   0.00051   0.0002   0.6529   0.7181
   0.750   0.0824   0.00491   0.00053   0.0003   0.6364   0.7349
   1.000   0.1093   0.00501   0.00054   0.0005   0.5927   0.7496
   1.250   0.1354   0.00526   0.00058   0.0008   0.5153   0.7623
   1.500   0.1604   0.00583   0.00068   0.0010   0.3760   0.7734
   1.750   0.1854   0.00644   0.00083   0.0012   0.2352   0.7862
   2.000   0.2119   0.00669   0.00094   0.0013   0.1813   0.8016
   2.250   0.2382   0.00695   0.00111   0.0015   0.1259   0.8174
   2.750   0.2905   0.00735   0.00140   0.0021   0.0589   0.8557
   3.000   0.3155   0.00767   0.00160   0.0025   0.0160   0.8778
   3.250   0.3409   0.00777   0.00175   0.0031   0.0096   0.9042
   3.500   0.3664   0.00791   0.00193   0.0037   0.0038   0.9351
   3.750   0.3964   0.00810   0.00214   0.0033   0.0024   0.9593
   4.000   0.4306   0.00833   0.00247   0.0018   0.0020   0.9760
   4.250   0.4648   0.00861   0.00282   0.0004   0.0019   0.9906
   4.500   0.4956   0.00892   0.00321  -0.0003   0.0019   1.0000
   4.750   0.5214   0.00930   0.00366   0.0001   0.0019   1.0000
   5.000   0.5470   0.00973   0.00418   0.0005   0.0019   1.0000
   5.250   0.5724   0.01028   0.00484   0.0010   0.0019   1.0000
   5.500   0.5974   0.01096   0.00564   0.0015   0.0020   1.0000
   5.750   0.6217   0.01187   0.00670   0.0022   0.0020   1.0000
   6.000   0.6452   0.01314   0.00817   0.0031   0.0021   1.0000
   6.250   0.6678   0.01494   0.01023   0.0041   0.0022   1.0000
   6.500   0.6891   0.01751   0.01323   0.0053   0.0023   1.0000
   6.750   0.7077   0.02123   0.01742   0.0068   0.0025   1.0000
   7.000   0.7207   0.02687   0.02366   0.0088   0.0027   1.0000
   7.250   0.7291   0.03353   0.03084   0.0106   0.0028   1.0000
   7.500   0.7337   0.04046   0.03817   0.0119   0.0030   1.0000
   7.750   0.7370   0.04648   0.04447   0.0125   0.0031   1.0000
   8.000   0.7356   0.05269   0.05091   0.0123   0.0032   1.0000
   8.250   0.7299   0.05895   0.05733   0.0112   0.0033   1.0000
   8.500   0.7213   0.06491   0.06341   0.0092   0.0033   1.0000
   8.750   0.7041   0.07027   0.06883   0.0064   0.0033   1.0000
   9.000   0.6921   0.07751   0.07604  -0.0012   0.0032   1.0000
   9.250   0.6845   0.08373   0.08220  -0.0056   0.0033   1.0000
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