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HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 AIRFOIL (hq259-il)
Reynolds number: 100,000
Max Cl/Cd: 56.75 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259-il-100000-n5.txt
Download as CSV file: xf-hq259-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3993   0.09042   0.08559  -0.0339   1.0000   0.0255
  -8.250  -0.4009   0.08670   0.08194  -0.0353   1.0000   0.0256
  -8.000  -0.4035   0.08323   0.07855  -0.0363   1.0000   0.0252
  -7.750  -0.4092   0.07984   0.07526  -0.0370   1.0000   0.0247
  -7.500  -0.4176   0.07663   0.07216  -0.0374   1.0000   0.0237
  -7.250  -0.4242   0.07250   0.06812  -0.0400   1.0000   0.0234
  -7.000  -0.4306   0.06832   0.06397  -0.0422   1.0000   0.0226
  -6.750  -0.4371   0.06421   0.05985  -0.0433   1.0000   0.0217
  -6.500  -0.4417   0.06028   0.05587  -0.0437   1.0000   0.0216
  -6.250  -0.4438   0.05579   0.05124  -0.0442   1.0000   0.0209
  -6.000  -0.4355   0.04961   0.04473  -0.0464   0.9984   0.0196
  -5.750  -0.4053   0.04277   0.03728  -0.0513   0.9924   0.0186
  -5.500  -0.3755   0.03778   0.03173  -0.0547   0.9870   0.0184
  -5.250  -0.3457   0.03349   0.02687  -0.0572   0.9820   0.0185
  -5.000  -0.3152   0.02974   0.02257  -0.0591   0.9770   0.0189
  -4.750  -0.2816   0.02684   0.01918  -0.0611   0.9734   0.0197
  -4.500  -0.2515   0.02489   0.01687  -0.0620   0.9679   0.0215
  -4.250  -0.2182   0.02343   0.01500  -0.0632   0.9633   0.0258
  -4.000  -0.1828   0.02158   0.01277  -0.0643   0.9601   0.0281
  -3.750  -0.1542   0.01983   0.01093  -0.0646   0.9545   0.0310
  -3.500  -0.1219   0.01869   0.00969  -0.0655   0.9498   0.0374
  -3.250  -0.0863   0.01779   0.00873  -0.0673   0.9463   0.0557
  -3.000  -0.0580   0.01713   0.00807  -0.0677   0.9395   0.0817
  -2.750  -0.0241   0.01632   0.00735  -0.0692   0.9350   0.1169
  -2.500   0.0066   0.01528   0.00674  -0.0704   0.9298   0.2374
  -2.250   0.0308   0.01409   0.00680  -0.0701   0.9236   0.5606
  -2.000   0.0615   0.01393   0.00681  -0.0700   0.9192   0.6671
  -1.750   0.0850   0.01390   0.00681  -0.0686   0.9112   0.7244
  -1.500   0.1103   0.01379   0.00681  -0.0668   0.9062   0.7960
  -1.250   0.1302   0.01367   0.00670  -0.0643   0.8979   0.8424
  -1.000   0.1627   0.01353   0.00646  -0.0648   0.8929   0.8645
  -0.750   0.1914   0.01344   0.00630  -0.0648   0.8849   0.8848
  -0.500   0.2286   0.01330   0.00607  -0.0665   0.8796   0.9071
  -0.250   0.2675   0.01321   0.00590  -0.0687   0.8721   0.9357
   0.000   0.3131   0.01307   0.00567  -0.0723   0.8664   0.9770
   0.250   0.3439   0.01308   0.00559  -0.0732   0.8571   1.0000
   0.500   0.3749   0.01308   0.00549  -0.0739   0.8495   1.0000
   0.750   0.4030   0.01312   0.00547  -0.0741   0.8401   1.0000
   1.000   0.4307   0.01317   0.00546  -0.0741   0.8302   1.0000
   1.250   0.4591   0.01316   0.00539  -0.0740   0.8184   1.0000
   1.500   0.4868   0.01312   0.00532  -0.0736   0.8047   1.0000
   1.750   0.5141   0.01310   0.00526  -0.0733   0.7906   1.0000
   2.000   0.5414   0.01312   0.00526  -0.0729   0.7775   1.0000
   2.250   0.5686   0.01315   0.00528  -0.0726   0.7641   1.0000
   2.500   0.5954   0.01320   0.00537  -0.0722   0.7496   1.0000
   2.750   0.6221   0.01324   0.00542  -0.0717   0.7337   1.0000
   3.000   0.6490   0.01328   0.00545  -0.0712   0.7164   1.0000
   3.250   0.6749   0.01336   0.00555  -0.0706   0.6965   1.0000
   3.500   0.7011   0.01344   0.00563  -0.0699   0.6755   1.0000
   3.750   0.7265   0.01356   0.00581  -0.0692   0.6510   1.0000
   4.000   0.7517   0.01370   0.00595  -0.0684   0.6227   1.0000
   4.250   0.7764   0.01389   0.00611  -0.0675   0.5890   1.0000
   4.500   0.8004   0.01415   0.00629  -0.0665   0.5495   1.0000
   4.750   0.8235   0.01451   0.00653  -0.0654   0.5051   1.0000
   5.000   0.8455   0.01500   0.00692  -0.0642   0.4578   1.0000
   5.250   0.8668   0.01558   0.00735  -0.0631   0.4111   1.0000
   5.500   0.8877   0.01623   0.00786  -0.0619   0.3659   1.0000
   5.750   0.9083   0.01693   0.00843  -0.0608   0.3249   1.0000
   6.000   0.9288   0.01767   0.00906  -0.0598   0.2902   1.0000
   6.250   0.9498   0.01839   0.00976  -0.0588   0.2611   1.0000
   6.500   0.9706   0.01913   0.01050  -0.0578   0.2334   1.0000
   6.750   0.9895   0.01999   0.01120  -0.0567   0.1908   1.0000
   7.000   1.0087   0.02088   0.01206  -0.0557   0.1540   1.0000
   7.250   1.0230   0.02239   0.01294  -0.0544   0.0783   1.0000
   7.500   1.0359   0.02427   0.01440  -0.0526   0.0266   1.0000
   7.750   1.0516   0.02582   0.01599  -0.0509   0.0186   1.0000
   8.000   1.0676   0.02725   0.01764  -0.0492   0.0158   1.0000
   8.250   1.0818   0.02878   0.01938  -0.0474   0.0143   1.0000
   8.500   1.0921   0.03065   0.02147  -0.0452   0.0131   1.0000
   8.750   1.0989   0.03280   0.02386  -0.0427   0.0125   1.0000
   9.000   1.1089   0.03462   0.02586  -0.0405   0.0121   1.0000
   9.250   1.1184   0.03643   0.02790  -0.0384   0.0115   1.0000
   9.500   1.1272   0.03835   0.03005  -0.0362   0.0109   1.0000
   9.750   1.1351   0.04030   0.03223  -0.0342   0.0099   1.0000
  10.000   1.1412   0.04244   0.03470  -0.0322   0.0093   1.0000
  10.250   1.1450   0.04480   0.03730  -0.0303   0.0088   1.0000
  10.500   1.1466   0.04753   0.04030  -0.0284   0.0086   1.0000
  10.750   1.1457   0.05052   0.04358  -0.0267   0.0085   1.0000
  11.000   1.1417   0.05380   0.04713  -0.0252   0.0084   1.0000
  11.250   1.1357   0.05738   0.05100  -0.0242   0.0085   1.0000
  11.500   1.1262   0.06138   0.05528  -0.0238   0.0084   1.0000
  11.750   1.1144   0.06588   0.06005  -0.0240   0.0084   1.0000
  12.000   1.1011   0.07083   0.06525  -0.0252   0.0085   1.0000
  12.250   1.0851   0.07657   0.07124  -0.0273   0.0084   1.0000
  12.500   1.0692   0.08283   0.07772  -0.0304   0.0085   1.0000
  12.750   1.0508   0.09023   0.08533  -0.0347   0.0086   1.0000
  13.000   1.0315   0.09869   0.09398  -0.0401   0.0087   1.0000
  13.250   1.0121   0.10817   0.10362  -0.0464   0.0089   1.0000
  13.500   0.9914   0.11910   0.11468  -0.0535   0.0091   1.0000
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