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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 1,000,000
Max Cl/Cd: 75.63 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq109-il-1000000-n5.txt
Download as CSV file: xf-hq109-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/9 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8455   0.05701   0.05541  -0.0317   1.0000   0.0019
 -11.500  -0.9217   0.03940   0.03732  -0.0428   1.0000   0.0018
 -11.250  -0.9249   0.03758   0.03540  -0.0411   1.0000   0.0019
 -11.000  -0.9227   0.03533   0.03301  -0.0401   1.0000   0.0019
 -10.750  -0.9303   0.03120   0.02852  -0.0386   1.0000   0.0020
 -10.500  -0.9245   0.02847   0.02552  -0.0374   1.0000   0.0020
 -10.250  -0.9144   0.02612   0.02291  -0.0363   1.0000   0.0020
 -10.000  -0.9001   0.02427   0.02084  -0.0354   1.0000   0.0021
  -9.750  -0.8833   0.02273   0.01910  -0.0345   1.0000   0.0022
  -9.500  -0.8664   0.02108   0.01722  -0.0336   1.0000   0.0022
  -9.250  -0.8482   0.01960   0.01554  -0.0326   1.0000   0.0023
  -9.000  -0.8284   0.01840   0.01414  -0.0318   1.0000   0.0024
  -8.750  -0.8079   0.01733   0.01292  -0.0309   1.0000   0.0024
  -8.500  -0.7873   0.01630   0.01174  -0.0300   1.0000   0.0025
  -8.250  -0.7663   0.01540   0.01070  -0.0291   1.0000   0.0026
  -8.000  -0.7436   0.01467   0.00987  -0.0284   0.9996   0.0028
  -7.750  -0.7129   0.01415   0.00927  -0.0294   0.9941   0.0029
  -7.500  -0.6821   0.01346   0.00847  -0.0304   0.9886   0.0030
  -7.250  -0.6507   0.01274   0.00766  -0.0316   0.9824   0.0031
  -7.000  -0.6203   0.01167   0.00644  -0.0326   0.9738   0.0037
  -6.750  -0.5891   0.01119   0.00587  -0.0336   0.9636   0.0041
  -6.500  -0.5590   0.01077   0.00540  -0.0342   0.9505   0.0046
  -6.250  -0.5313   0.01042   0.00496  -0.0343   0.9337   0.0051
  -6.000  -0.5052   0.01012   0.00456  -0.0339   0.9169   0.0055
  -5.750  -0.4795   0.00987   0.00422  -0.0335   0.9024   0.0057
  -5.500  -0.4542   0.00945   0.00369  -0.0330   0.8895   0.0070
  -5.250  -0.4282   0.00919   0.00339  -0.0327   0.8774   0.0084
  -5.000  -0.4017   0.00898   0.00309  -0.0325   0.8668   0.0095
  -4.750  -0.3751   0.00876   0.00280  -0.0322   0.8569   0.0116
  -4.500  -0.3486   0.00853   0.00255  -0.0320   0.8476   0.0163
  -4.250  -0.3218   0.00830   0.00234  -0.0318   0.8383   0.0255
  -4.000  -0.2949   0.00811   0.00214  -0.0317   0.8290   0.0343
  -3.750  -0.2678   0.00796   0.00197  -0.0315   0.8194   0.0420
  -3.500  -0.2406   0.00782   0.00180  -0.0314   0.8091   0.0504
  -3.250  -0.2136   0.00762   0.00164  -0.0313   0.7989   0.0674
  -3.000  -0.1867   0.00739   0.00148  -0.0312   0.7891   0.0954
  -2.750  -0.1600   0.00715   0.00133  -0.0311   0.7790   0.1336
  -2.500  -0.1327   0.00695   0.00120  -0.0310   0.7696   0.1681
  -2.000  -0.0781   0.00662   0.00100  -0.0309   0.7531   0.2296
  -1.750  -0.0521   0.00618   0.00086  -0.0308   0.7417   0.3290
  -1.500  -0.0261   0.00583   0.00076  -0.0307   0.7275   0.4228
  -1.250   0.0010   0.00568   0.00070  -0.0306   0.7143   0.4683
  -1.000   0.0277   0.00545   0.00066  -0.0305   0.7032   0.5376
  -0.750   0.0548   0.00535   0.00065  -0.0303   0.6896   0.5838
  -0.500   0.0821   0.00532   0.00064  -0.0302   0.6742   0.6116
  -0.250   0.1097   0.00530   0.00064  -0.0301   0.6605   0.6336
   0.000   0.1374   0.00531   0.00064  -0.0300   0.6470   0.6500
   0.250   0.1651   0.00532   0.00065  -0.0300   0.6334   0.6643
   0.500   0.1927   0.00536   0.00067  -0.0299   0.6164   0.6772
   0.750   0.2202   0.00541   0.00069  -0.0298   0.5960   0.6901
   1.000   0.2476   0.00547   0.00072  -0.0297   0.5746   0.7039
   1.250   0.2748   0.00555   0.00076  -0.0296   0.5500   0.7176
   1.500   0.3016   0.00570   0.00083  -0.0294   0.5148   0.7285
   2.000   0.3548   0.00611   0.00099  -0.0290   0.4318   0.7474
   2.250   0.3808   0.00639   0.00111  -0.0288   0.3808   0.7569
   2.500   0.4062   0.00678   0.00126  -0.0285   0.3114   0.7670
   2.750   0.4326   0.00701   0.00140  -0.0283   0.2751   0.7779
   3.000   0.4590   0.00721   0.00154  -0.0281   0.2474   0.7890
   3.250   0.4857   0.00738   0.00167  -0.0280   0.2273   0.8005
   3.500   0.5122   0.00755   0.00183  -0.0278   0.2044   0.8123
   3.750   0.5387   0.00771   0.00197  -0.0275   0.1862   0.8250
   4.000   0.5646   0.00792   0.00214  -0.0273   0.1609   0.8389
   4.500   0.6139   0.00856   0.00259  -0.0263   0.0915   0.8736
   4.750   0.6376   0.00883   0.00285  -0.0255   0.0660   0.9016
   5.000   0.6654   0.00902   0.00310  -0.0256   0.0499   0.9546
   5.250   0.7025   0.00933   0.00337  -0.0278   0.0374   1.0000
   5.500   0.7283   0.00963   0.00363  -0.0276   0.0285   1.0000
   5.750   0.7537   0.00998   0.00392  -0.0273   0.0194   1.0000
   6.000   0.7789   0.01035   0.00425  -0.0269   0.0124   1.0000
   6.250   0.8041   0.01073   0.00462  -0.0266   0.0075   1.0000
   6.500   0.8291   0.01112   0.00501  -0.0262   0.0049   1.0000
   6.750   0.8544   0.01148   0.00540  -0.0258   0.0040   1.0000
   7.000   0.8794   0.01186   0.00582  -0.0254   0.0036   1.0000
   7.250   0.9041   0.01229   0.00629  -0.0250   0.0031   1.0000
   7.500   0.9282   0.01280   0.00686  -0.0245   0.0027   1.0000
   7.750   0.9514   0.01346   0.00761  -0.0238   0.0024   1.0000
   8.000   0.9732   0.01432   0.00860  -0.0229   0.0022   1.0000
   8.250   0.9962   0.01495   0.00934  -0.0222   0.0022   1.0000
   8.500   1.0193   0.01552   0.00997  -0.0216   0.0022   1.0000
   8.750   1.0419   0.01616   0.01069  -0.0210   0.0021   1.0000
   9.000   1.0639   0.01684   0.01145  -0.0203   0.0020   1.0000
   9.250   1.0861   0.01746   0.01216  -0.0196   0.0019   1.0000
   9.500   1.1067   0.01829   0.01309  -0.0187   0.0018   1.0000
   9.750   1.1268   0.01913   0.01404  -0.0178   0.0018   1.0000
  10.000   1.1452   0.02017   0.01521  -0.0167   0.0017   1.0000
  10.250   1.1628   0.02123   0.01640  -0.0155   0.0017   1.0000
  10.500   1.1792   0.02239   0.01772  -0.0142   0.0016   1.0000
  10.750   1.1950   0.02351   0.01898  -0.0128   0.0016   1.0000
  11.000   1.2081   0.02484   0.02047  -0.0112   0.0016   1.0000
  11.250   1.2195   0.02622   0.02201  -0.0095   0.0015   1.0000
  11.500   1.2274   0.02779   0.02375  -0.0073   0.0015   1.0000
  11.750   1.2325   0.02908   0.02517  -0.0047   0.0015   1.0000
  12.000   1.2343   0.03048   0.02671  -0.0019   0.0014   1.0000
  12.250   1.2281   0.03261   0.02903   0.0011   0.0014   1.0000
  12.500   1.2227   0.03486   0.03145   0.0033   0.0014   1.0000
  12.750   1.2233   0.03676   0.03346   0.0045   0.0014   1.0000
  13.000   1.2122   0.04005   0.03694   0.0054   0.0014   1.0000
  13.250   1.2018   0.04366   0.04072   0.0054   0.0014   1.0000
  13.500   1.1976   0.04687   0.04404   0.0047   0.0013   1.0000
  13.750   1.1888   0.05107   0.04838   0.0032   0.0013   1.0000
  14.000   1.1537   0.06008   0.05766  -0.0015   0.0014   1.0000
  14.250   1.1374   0.06729   0.06501  -0.0062   0.0014   1.0000
  14.500   1.1036   0.07938   0.07731  -0.0142   0.0014   1.0000
  14.750   1.0891   0.08795   0.08598  -0.0195   0.0014   1.0000
  15.000   1.0188   0.10967   0.10794  -0.0318   0.0015   1.0000
  15.250   0.9974   0.11993   0.11825  -0.0372   0.0015   1.0000
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