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HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)
Reynolds number: 100,000
Max Cl/Cd: 45.46 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hh02-il-100000-n5.txt
Download as CSV file: xf-hh02-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HUGHES HELICOPTERS HH-02 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6039   0.08977   0.08572   0.0160   0.8997   0.0283
  -8.000  -0.6065   0.08359   0.07956   0.0100   0.8948   0.0279
  -7.750  -0.6069   0.07502   0.07096   0.0003   0.8903   0.0273
  -7.500  -0.6051   0.06680   0.06254  -0.0072   0.8857   0.0271
  -7.250  -0.5991   0.06121   0.05672  -0.0109   0.8814   0.0276
  -7.000  -0.5886   0.05550   0.05069  -0.0143   0.8768   0.0282
  -6.750  -0.5774   0.05029   0.04505  -0.0160   0.8726   0.0287
  -6.500  -0.5618   0.04515   0.03940  -0.0175   0.8682   0.0287
  -6.250  -0.5436   0.04074   0.03444  -0.0181   0.8638   0.0290
  -6.000  -0.5248   0.03721   0.03035  -0.0176   0.8599   0.0294
  -5.750  -0.5000   0.03397   0.02654  -0.0180   0.8551   0.0304
  -5.500  -0.4753   0.03179   0.02372  -0.0176   0.8506   0.0326
  -5.250  -0.4528   0.02958   0.02121  -0.0170   0.8467   0.0342
  -5.000  -0.4249   0.02775   0.01914  -0.0174   0.8417   0.0356
  -4.750  -0.3989   0.02627   0.01744  -0.0170   0.8371   0.0372
  -4.500  -0.3745   0.02518   0.01613  -0.0161   0.8334   0.0401
  -4.250  -0.3453   0.02417   0.01484  -0.0162   0.8282   0.0432
  -4.000  -0.3198   0.02272   0.01341  -0.0158   0.8235   0.0459
  -3.750  -0.2955   0.02188   0.01251  -0.0149   0.8197   0.0496
  -3.500  -0.2679   0.02121   0.01170  -0.0148   0.8148   0.0551
  -3.250  -0.2416   0.02032   0.01083  -0.0146   0.8098   0.0607
  -3.000  -0.2166   0.01976   0.01017  -0.0138   0.8057   0.0695
  -2.750  -0.1902   0.01914   0.00954  -0.0134   0.8013   0.0833
  -2.500  -0.1625   0.01839   0.00900  -0.0137   0.7958   0.1201
  -2.250  -0.1382   0.01732   0.00853  -0.0133   0.7916   0.2525
  -2.000  -0.1149   0.01640   0.00849  -0.0125   0.7874   0.4699
  -1.750  -0.0874   0.01621   0.00850  -0.0122   0.7813   0.5685
  -1.500  -0.0644   0.01602   0.00847  -0.0106   0.7769   0.6489
  -1.250  -0.0399   0.01579   0.00831  -0.0094   0.7724   0.7050
  -1.000  -0.0112   0.01556   0.00811  -0.0094   0.7661   0.7395
  -0.750   0.0153   0.01513   0.00786  -0.0083   0.7617   0.7900
  -0.500   0.0792   0.01483   0.00778  -0.0149   0.7576   0.9997
  -0.250   0.1086   0.01491   0.00770  -0.0155   0.7506   1.0000
   0.000   0.1333   0.01490   0.00753  -0.0146   0.7459   1.0000
   0.250   0.1621   0.01496   0.00747  -0.0149   0.7377   1.0000
   0.500   0.1859   0.01485   0.00723  -0.0136   0.7310   1.0000
   0.750   0.2134   0.01482   0.00710  -0.0134   0.7210   1.0000
   1.000   0.2363   0.01466   0.00682  -0.0117   0.7145   1.0000
   1.250   0.2651   0.01469   0.00680  -0.0119   0.7041   1.0000
   1.500   0.2911   0.01465   0.00668  -0.0112   0.6964   1.0000
   1.750   0.3177   0.01462   0.00660  -0.0107   0.6876   1.0000
   2.000   0.3450   0.01462   0.00657  -0.0104   0.6781   1.0000
   2.250   0.3697   0.01451   0.00640  -0.0092   0.6703   1.0000
   2.500   0.3978   0.01454   0.00643  -0.0091   0.6587   1.0000
   2.750   0.4248   0.01453   0.00640  -0.0087   0.6471   1.0000
   3.000   0.4511   0.01449   0.00636  -0.0080   0.6352   1.0000
   3.250   0.4775   0.01445   0.00630  -0.0074   0.6220   1.0000
   3.500   0.5042   0.01445   0.00628  -0.0068   0.6066   1.0000
   3.750   0.5312   0.01447   0.00629  -0.0064   0.5889   1.0000
   4.000   0.5580   0.01450   0.00632  -0.0059   0.5695   1.0000
   4.250   0.5849   0.01456   0.00635  -0.0054   0.5479   1.0000
   4.500   0.6121   0.01468   0.00643  -0.0051   0.5226   1.0000
   4.750   0.6394   0.01485   0.00655  -0.0049   0.4934   1.0000
   5.000   0.6666   0.01510   0.00672  -0.0048   0.4605   1.0000
   5.250   0.6940   0.01544   0.00696  -0.0048   0.4238   1.0000
   5.500   0.7211   0.01590   0.00726  -0.0049   0.3874   1.0000
   5.750   0.7482   0.01646   0.00768  -0.0052   0.3546   1.0000
   6.000   0.7751   0.01706   0.00818  -0.0055   0.3251   1.0000
   6.250   0.8018   0.01768   0.00873  -0.0059   0.2990   1.0000
   6.500   0.8282   0.01832   0.00933  -0.0062   0.2750   1.0000
   6.750   0.8542   0.01899   0.00998  -0.0065   0.2525   1.0000
   7.000   0.8800   0.01966   0.01065  -0.0067   0.2308   1.0000
   7.250   0.9053   0.02038   0.01135  -0.0070   0.2098   1.0000
   7.500   0.9299   0.02114   0.01209  -0.0072   0.1907   1.0000
   7.750   0.9542   0.02191   0.01292  -0.0074   0.1729   1.0000
   8.000   0.9778   0.02275   0.01378  -0.0074   0.1570   1.0000
   8.250   1.0006   0.02365   0.01471  -0.0075   0.1416   1.0000
   8.500   1.0227   0.02461   0.01570  -0.0075   0.1269   1.0000
   8.750   1.0438   0.02563   0.01680  -0.0074   0.1140   1.0000
   9.000   1.0639   0.02674   0.01795  -0.0073   0.1026   1.0000
   9.250   1.0825   0.02798   0.01919  -0.0071   0.0929   1.0000
   9.500   1.1009   0.02917   0.02051  -0.0069   0.0833   1.0000
   9.750   1.1177   0.03053   0.02197  -0.0065   0.0755   1.0000
  10.000   1.1315   0.03206   0.02351  -0.0063   0.0687   1.0000
  10.250   1.1463   0.03349   0.02516  -0.0058   0.0620   1.0000
  10.500   1.1558   0.03526   0.02694  -0.0054   0.0569   1.0000
  10.750   1.1656   0.03688   0.02878  -0.0045   0.0518   1.0000
  11.000   1.1713   0.03868   0.03067  -0.0036   0.0479   1.0000
  11.250   1.1751   0.04081   0.03287  -0.0027   0.0445   1.0000
  11.500   1.1804   0.04291   0.03519  -0.0020   0.0408   1.0000
  11.750   1.1829   0.04522   0.03760  -0.0016   0.0380   1.0000
  12.000   1.1820   0.04797   0.04037  -0.0014   0.0358   1.0000
  12.250   1.1836   0.05073   0.04343  -0.0011   0.0335   1.0000
  12.500   1.1827   0.05379   0.04672  -0.0012   0.0316   1.0000
  12.750   1.1802   0.05705   0.05013  -0.0016   0.0300   1.0000
  13.000   1.1761   0.06056   0.05375  -0.0024   0.0288   1.0000
  13.250   1.1700   0.06444   0.05770  -0.0033   0.0278   1.0000
  13.500   1.1621   0.06899   0.06250  -0.0047   0.0269   1.0000
  13.750   1.1520   0.07404   0.06781  -0.0066   0.0261   1.0000
  14.000   1.1400   0.07963   0.07363  -0.0091   0.0254   1.0000
  14.250   1.1263   0.08586   0.08007  -0.0122   0.0250   1.0000
  14.500   1.1105   0.09286   0.08728  -0.0159   0.0247   1.0000
  14.750   1.0921   0.10080   0.09542  -0.0203   0.0246   1.0000
  15.000   1.0703   0.10996   0.10477  -0.0256   0.0248   1.0000
  15.250   1.0442   0.12072   0.11571  -0.0318   0.0253   1.0000
  15.500   1.0141   0.13314   0.12823  -0.0389   0.0261   1.0000
  15.750   0.9806   0.14758   0.14275  -0.0468   0.0269   1.0000
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