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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 200,000
Max Cl/Cd: 74.65 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1712-il-200000-n5.txt
Download as CSV file: xf-hs1712-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-712 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3432   0.09232   0.08858  -0.0592   0.9806   0.0222
  -8.750  -0.3488   0.08706   0.08334  -0.0621   0.9754   0.0222
  -8.250  -0.3870   0.03582   0.03062  -0.1117   0.9604   0.0227
  -8.000  -0.3553   0.03383   0.02839  -0.1147   0.9591   0.0233
  -7.750  -0.3281   0.03133   0.02548  -0.1167   0.9566   0.0245
  -7.500  -0.3033   0.02849   0.02204  -0.1180   0.9530   0.0258
  -7.250  -0.2733   0.02770   0.02117  -0.1192   0.9503   0.0266
  -7.000  -0.2410   0.02638   0.01959  -0.1209   0.9483   0.0276
  -6.750  -0.2069   0.02476   0.01754  -0.1229   0.9469   0.0290
  -6.500  -0.1717   0.02400   0.01669  -0.1249   0.9454   0.0302
  -6.250  -0.1346   0.02311   0.01553  -0.1272   0.9442   0.0325
  -6.000  -0.1140   0.02252   0.01486  -0.1260   0.9375   0.0339
  -5.750  -0.0816   0.02176   0.01394  -0.1271   0.9347   0.0359
  -5.500  -0.0474   0.02098   0.01305  -0.1287   0.9327   0.0380
  -5.250  -0.0119   0.02029   0.01220  -0.1305   0.9311   0.0411
  -5.000   0.0242   0.01952   0.01150  -0.1326   0.9298   0.0438
  -4.750   0.0486   0.01907   0.01104  -0.1320   0.9239   0.0462
  -4.500   0.0790   0.01866   0.01063  -0.1327   0.9198   0.0495
  -4.250   0.1133   0.01824   0.01021  -0.1342   0.9171   0.0533
  -4.000   0.1492   0.01781   0.00975  -0.1359   0.9152   0.0576
  -3.750   0.1860   0.01737   0.00928  -0.1379   0.9136   0.0627
  -3.500   0.2061   0.01725   0.00915  -0.1363   0.9049   0.0670
  -3.250   0.2399   0.01684   0.00877  -0.1375   0.9011   0.0743
  -3.000   0.2764   0.01636   0.00832  -0.1393   0.8984   0.0842
  -2.750   0.3013   0.01613   0.00815  -0.1387   0.8902   0.0953
  -2.500   0.3333   0.01577   0.00786  -0.1395   0.8853   0.1145
  -2.250   0.3690   0.01539   0.00754  -0.1411   0.8821   0.1365
  -2.000   0.3946   0.01527   0.00748  -0.1406   0.8735   0.1553
  -1.750   0.4282   0.01498   0.00722  -0.1417   0.8676   0.1754
  -1.500   0.4623   0.01470   0.00696  -0.1429   0.8609   0.1926
  -1.250   0.4959   0.01441   0.00668  -0.1440   0.8517   0.2095
  -1.000   0.5341   0.01406   0.00635  -0.1461   0.8432   0.2302
  -0.750   0.5763   0.01365   0.00599  -0.1492   0.8347   0.2550
  -0.500   0.6160   0.01328   0.00568  -0.1517   0.8230   0.2869
  -0.250   0.6568   0.01279   0.00542  -0.1546   0.8079   0.3660
   0.000   0.6952   0.01176   0.00533  -0.1570   0.7935   0.7097
   0.250   0.7114   0.01122   0.00511  -0.1532   0.7770   0.9196
   0.500   0.7346   0.01112   0.00493  -0.1519   0.7433   1.0000
   0.750   0.7697   0.01119   0.00472  -0.1533   0.7230   1.0000
   1.000   0.7996   0.01139   0.00470  -0.1536   0.7050   1.0000
   1.250   0.8273   0.01160   0.00478  -0.1535   0.6878   1.0000
   1.500   0.8545   0.01182   0.00488  -0.1534   0.6708   1.0000
   1.750   0.8812   0.01205   0.00500  -0.1531   0.6532   1.0000
   2.000   0.9072   0.01229   0.00513  -0.1527   0.6347   1.0000
   2.250   0.9323   0.01254   0.00527  -0.1521   0.6151   1.0000
   2.500   0.9563   0.01281   0.00542  -0.1513   0.5927   1.0000
   2.750   0.9793   0.01312   0.00559  -0.1502   0.5682   1.0000
   3.000   1.0020   0.01343   0.00579  -0.1492   0.5422   1.0000
   3.250   1.0221   0.01384   0.00600  -0.1476   0.5079   1.0000
   3.500   1.0414   0.01429   0.00626  -0.1458   0.4734   1.0000
   3.750   1.0601   0.01478   0.00658  -0.1440   0.4418   1.0000
   4.000   1.0789   0.01529   0.00691  -0.1423   0.4136   1.0000
   4.250   1.0985   0.01577   0.00726  -0.1407   0.3897   1.0000
   4.500   1.1178   0.01627   0.00762  -0.1391   0.3698   1.0000
   4.750   1.1370   0.01677   0.00802  -0.1375   0.3560   1.0000
   5.000   1.1565   0.01727   0.00843  -0.1360   0.3456   1.0000
   5.250   1.1774   0.01768   0.00882  -0.1347   0.3364   1.0000
   5.500   1.1970   0.01813   0.00924  -0.1332   0.3277   1.0000
   5.750   1.2185   0.01848   0.00963  -0.1321   0.3194   1.0000
   6.000   1.2389   0.01889   0.01005  -0.1308   0.3106   1.0000
   6.250   1.2601   0.01926   0.01045  -0.1296   0.3012   1.0000
   6.500   1.2792   0.01972   0.01090  -0.1281   0.2907   1.0000
   6.750   1.2991   0.02016   0.01134  -0.1267   0.2801   1.0000
   7.000   1.3181   0.02063   0.01182  -0.1252   0.2713   1.0000
   7.250   1.3374   0.02111   0.01231  -0.1238   0.2621   1.0000
   7.500   1.3558   0.02163   0.01285  -0.1223   0.2524   1.0000
   7.750   1.3731   0.02221   0.01341  -0.1205   0.2411   1.0000
   8.000   1.3913   0.02275   0.01398  -0.1190   0.2308   1.0000
   8.250   1.4078   0.02339   0.01462  -0.1172   0.2200   1.0000
   8.500   1.4238   0.02406   0.01529  -0.1154   0.2081   1.0000
   8.750   1.4400   0.02474   0.01598  -0.1137   0.1970   1.0000
   9.000   1.4550   0.02549   0.01674  -0.1118   0.1863   1.0000
   9.250   1.4691   0.02631   0.01755  -0.1098   0.1755   1.0000
   9.500   1.4839   0.02710   0.01837  -0.1079   0.1653   1.0000
   9.750   1.4973   0.02799   0.01927  -0.1059   0.1556   1.0000
  10.000   1.5095   0.02897   0.02026  -0.1038   0.1455   1.0000
  10.250   1.5220   0.02995   0.02127  -0.1018   0.1356   1.0000
  10.500   1.5329   0.03105   0.02238  -0.0996   0.1262   1.0000
  10.750   1.5428   0.03224   0.02357  -0.0974   0.1180   1.0000
  11.000   1.5537   0.03338   0.02477  -0.0954   0.1107   1.0000
  11.250   1.5631   0.03465   0.02608  -0.0933   0.1054   1.0000
  11.500   1.5726   0.03592   0.02742  -0.0912   0.1007   1.0000
  11.750   1.5801   0.03737   0.02892  -0.0891   0.0968   1.0000
  12.000   1.5895   0.03871   0.03037  -0.0872   0.0932   1.0000
  12.250   1.5969   0.04024   0.03197  -0.0852   0.0898   1.0000
  12.500   1.6033   0.04189   0.03370  -0.0833   0.0869   1.0000
  12.750   1.6107   0.04349   0.03541  -0.0816   0.0840   1.0000
  13.000   1.6161   0.04532   0.03733  -0.0798   0.0813   1.0000
  13.250   1.6198   0.04737   0.03945  -0.0781   0.0789   1.0000
  13.500   1.6228   0.04955   0.04173  -0.0765   0.0769   1.0000
  13.750   1.6233   0.05206   0.04430  -0.0749   0.0748   1.0000
  14.000   1.6212   0.05492   0.04720  -0.0734   0.0729   1.0000
  14.250   1.6247   0.05728   0.04973  -0.0723   0.0707   1.0000
  14.500   1.6252   0.06006   0.05264  -0.0713   0.0687   1.0000
  14.750   1.6218   0.06335   0.05602  -0.0704   0.0669   1.0000
  15.000   1.6266   0.06578   0.05865  -0.0699   0.0644   1.0000
  15.250   1.6280   0.06866   0.06170  -0.0694   0.0619   1.0000
  15.500   1.6279   0.07176   0.06494  -0.0690   0.0597   1.0000
  15.750   1.6271   0.07505   0.06836  -0.0688   0.0575   1.0000
  16.000   1.6231   0.07884   0.07225  -0.0689   0.0558   1.0000
  16.250   1.6192   0.08269   0.07623  -0.0690   0.0540   1.0000
  16.500   1.6138   0.08683   0.08051  -0.0695   0.0522   1.0000
  16.750   1.6056   0.09146   0.08523  -0.0702   0.0507   1.0000
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