Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.59 at α=-0.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ste87391-il-1000000-n5.txt
Download as CSV file: xf-ste87391-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 87(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.5205   0.10562   0.10314  -0.1077   0.9334   0.0071
 -17.250  -0.5460   0.09673   0.09414  -0.1126   0.9326   0.0071
 -17.000  -0.5657   0.08921   0.08652  -0.1169   0.9316   0.0071
 -16.750  -0.5836   0.08218   0.07938  -0.1211   0.9305   0.0072
 -16.500  -0.6006   0.07554   0.07265  -0.1253   0.9292   0.0072
 -16.250  -0.6172   0.06924   0.06625  -0.1293   0.9278   0.0072
 -16.000  -0.6334   0.06307   0.05997  -0.1333   0.9263   0.0073
 -15.750  -0.6470   0.05730   0.05409  -0.1372   0.9248   0.0073
 -15.500  -0.6583   0.05172   0.04839  -0.1412   0.9232   0.0073
 -15.250  -0.6655   0.04662   0.04317  -0.1451   0.9217   0.0074
 -15.000  -0.6686   0.04205   0.03847  -0.1489   0.9201   0.0075
 -14.750  -0.6693   0.03788   0.03418  -0.1527   0.9186   0.0076
 -14.500  -0.6647   0.03473   0.03092  -0.1557   0.9171   0.0077
 -14.250  -0.6590   0.03202   0.02810  -0.1580   0.9156   0.0078
 -14.000  -0.6518   0.02978   0.02576  -0.1597   0.9140   0.0080
 -13.750  -0.6428   0.02790   0.02379  -0.1609   0.9126   0.0081
 -13.500  -0.6322   0.02630   0.02209  -0.1618   0.9112   0.0082
 -13.250  -0.6201   0.02490   0.02059  -0.1624   0.9099   0.0084
 -13.000  -0.6068   0.02365   0.01924  -0.1628   0.9086   0.0085
 -12.750  -0.5918   0.02253   0.01802  -0.1632   0.9074   0.0086
 -12.500  -0.5750   0.02156   0.01696  -0.1636   0.9062   0.0086
 -12.250  -0.5575   0.02067   0.01600  -0.1639   0.9053   0.0087
 -12.000  -0.5458   0.01940   0.01463  -0.1641   0.9041   0.0089
 -11.750  -0.5271   0.01842   0.01359  -0.1646   0.9030   0.0091
 -11.500  -0.5057   0.01773   0.01284  -0.1649   0.9020   0.0093
 -11.250  -0.4828   0.01718   0.01224  -0.1652   0.9009   0.0095
 -11.000  -0.4589   0.01672   0.01174  -0.1655   0.9001   0.0098
 -10.750  -0.4346   0.01627   0.01125  -0.1658   0.8993   0.0100
 -10.500  -0.4101   0.01581   0.01075  -0.1660   0.8985   0.0103
 -10.250  -0.3856   0.01532   0.01021  -0.1662   0.8978   0.0106
 -10.000  -0.3608   0.01484   0.00968  -0.1665   0.8970   0.0108
  -9.750  -0.3356   0.01439   0.00917  -0.1667   0.8964   0.0111
  -9.500  -0.3100   0.01397   0.00869  -0.1670   0.8957   0.0114
  -9.250  -0.2839   0.01358   0.00825  -0.1673   0.8951   0.0116
  -9.000  -0.2575   0.01323   0.00785  -0.1676   0.8945   0.0118
  -8.750  -0.2304   0.01295   0.00754  -0.1679   0.8939   0.0120
  -8.500  -0.2041   0.01250   0.00704  -0.1683   0.8933   0.0123
  -8.250  -0.1776   0.01202   0.00650  -0.1687   0.8925   0.0128
  -8.000  -0.1515   0.01168   0.00613  -0.1689   0.8918   0.0131
  -7.750  -0.1255   0.01140   0.00583  -0.1689   0.8911   0.0135
  -7.500  -0.0993   0.01115   0.00556  -0.1690   0.8905   0.0138
  -7.250  -0.0730   0.01091   0.00530  -0.1691   0.8898   0.0142
  -7.000  -0.0466   0.01070   0.00507  -0.1691   0.8890   0.0146
  -6.750  -0.0200   0.01050   0.00485  -0.1692   0.8881   0.0151
  -6.500   0.0068   0.01032   0.00465  -0.1693   0.8872   0.0155
  -6.250   0.0339   0.01016   0.00447  -0.1694   0.8863   0.0160
  -6.000   0.0613   0.00998   0.00427  -0.1696   0.8855   0.0166
  -5.750   0.0890   0.00978   0.00406  -0.1698   0.8846   0.0177
  -5.500   0.1170   0.00961   0.00389  -0.1701   0.8837   0.0188
  -5.250   0.1456   0.00946   0.00373  -0.1705   0.8829   0.0201
  -5.000   0.1745   0.00930   0.00357  -0.1710   0.8820   0.0235
  -4.750   0.2032   0.00887   0.00331  -0.1716   0.8811   0.0632
  -4.500   0.2321   0.00837   0.00307  -0.1725   0.8802   0.1277
  -4.250   0.2621   0.00814   0.00296  -0.1733   0.8791   0.1647
  -4.000   0.2911   0.00801   0.00290  -0.1738   0.8777   0.1827
  -3.750   0.3150   0.00794   0.00286  -0.1731   0.8755   0.1935
  -3.500   0.3412   0.00784   0.00280  -0.1729   0.8732   0.2025
  -3.000   0.3998   0.00756   0.00254  -0.1738   0.8680   0.2200
  -2.750   0.4318   0.00737   0.00237  -0.1748   0.8653   0.2340
  -2.500   0.4577   0.00725   0.00231  -0.1746   0.8618   0.2497
  -2.250   0.4815   0.00714   0.00225  -0.1739   0.8572   0.2623
  -2.000   0.5099   0.00698   0.00211  -0.1741   0.8523   0.2750
  -1.750   0.5347   0.00688   0.00204  -0.1735   0.8463   0.2892
  -1.500   0.5590   0.00677   0.00198  -0.1729   0.8394   0.3065
  -1.250   0.5854   0.00666   0.00193  -0.1728   0.8336   0.3300
  -1.000   0.6099   0.00655   0.00189  -0.1722   0.8252   0.3556
  -0.750   0.6351   0.00645   0.00185  -0.1718   0.8149   0.3831
  -0.500   0.6591   0.00634   0.00175  -0.1711   0.7958   0.4138
  -0.250   0.6779   0.00636   0.00169  -0.1693   0.7634   0.4468
   0.000   0.6915   0.00656   0.00181  -0.1664   0.7274   0.4817
   0.250   0.7058   0.00687   0.00204  -0.1638   0.6915   0.5215
   0.500   0.7222   0.00716   0.00230  -0.1618   0.6580   0.5705
   0.750   0.7392   0.00745   0.00263  -0.1600   0.6233   0.6387
   1.000   0.7539   0.00787   0.00301  -0.1575   0.5885   0.6890
   1.250   0.7698   0.00830   0.00333  -0.1553   0.5565   0.7077
   1.500   0.7880   0.00869   0.00360  -0.1536   0.5285   0.7188
   1.750   0.8064   0.00907   0.00387  -0.1519   0.5020   0.7261
   2.000   0.8250   0.00947   0.00414  -0.1503   0.4744   0.7326
   2.250   0.8439   0.00987   0.00441  -0.1488   0.4469   0.7380
   2.500   0.8637   0.01024   0.00467  -0.1475   0.4214   0.7434
   2.750   0.8845   0.01058   0.00492  -0.1463   0.4007   0.7480
   3.000   0.9055   0.01091   0.00516  -0.1453   0.3812   0.7522
   3.250   0.9262   0.01124   0.00544  -0.1441   0.3632   0.7599
   3.500   0.9469   0.01159   0.00574  -0.1429   0.3464   0.7718
   3.750   0.9675   0.01196   0.00604  -0.1417   0.3300   0.7815
   4.000   0.9885   0.01228   0.00631  -0.1407   0.3138   0.7853
   4.250   1.0100   0.01260   0.00657  -0.1397   0.2991   0.7866
   4.500   1.0320   0.01289   0.00682  -0.1389   0.2876   0.7877
   4.750   1.0538   0.01319   0.00709  -0.1381   0.2773   0.7888
   5.250   1.0976   0.01378   0.00762  -0.1364   0.2591   0.7910
   5.500   1.1193   0.01409   0.00790  -0.1356   0.2510   0.7923
   5.750   1.1415   0.01438   0.00818  -0.1349   0.2433   0.7934
   6.000   1.1627   0.01472   0.00849  -0.1340   0.2343   0.7943
   6.250   1.1831   0.01509   0.00882  -0.1329   0.2237   0.7953
   6.500   1.2046   0.01541   0.00913  -0.1321   0.2172   0.7962
   6.750   1.2251   0.01577   0.00947  -0.1311   0.2098   0.7971
   7.000   1.2458   0.01613   0.00982  -0.1302   0.2014   0.7980
   7.250   1.2649   0.01657   0.01021  -0.1290   0.1889   0.7991
   7.500   1.2835   0.01704   0.01062  -0.1277   0.1755   0.8003
   7.750   1.3012   0.01755   0.01107  -0.1263   0.1604   0.8015
   8.000   1.3184   0.01810   0.01155  -0.1249   0.1457   0.8026
   8.250   1.3354   0.01866   0.01205  -0.1234   0.1322   0.8036
   8.500   1.3476   0.01952   0.01275  -0.1212   0.1049   0.8048
   8.750   1.3554   0.02066   0.01367  -0.1184   0.0720   0.8059
   9.000   1.3650   0.02169   0.01457  -0.1159   0.0488   0.8071
   9.250   1.3753   0.02271   0.01549  -0.1135   0.0304   0.8083
   9.500   1.3861   0.02372   0.01641  -0.1112   0.0163   0.8094
   9.750   1.3973   0.02469   0.01734  -0.1091   0.0077   0.8105
  10.000   1.4118   0.02545   0.01811  -0.1074   0.0060   0.8116
  10.500   1.4416   0.02691   0.01966  -0.1043   0.0049   0.8139
  10.750   1.4553   0.02773   0.02053  -0.1027   0.0044   0.8152
  11.000   1.4688   0.02855   0.02141  -0.1010   0.0042   0.8167
  11.250   1.4826   0.02938   0.02229  -0.0995   0.0041   0.8182
  11.500   1.4956   0.03026   0.02323  -0.0979   0.0039   0.8198
  11.750   1.5077   0.03122   0.02424  -0.0962   0.0038   0.8213
  12.000   1.5195   0.03222   0.02530  -0.0945   0.0036   0.8228
  12.250   1.5306   0.03329   0.02643  -0.0928   0.0035   0.8243
  12.500   1.5407   0.03443   0.02763  -0.0911   0.0034   0.8259
  12.750   1.5502   0.03564   0.02891  -0.0893   0.0033   0.8273
  13.000   1.5586   0.03697   0.03030  -0.0875   0.0032   0.8290
  13.250   1.5656   0.03843   0.03185  -0.0856   0.0030   0.8307
  13.500   1.5707   0.04011   0.03361  -0.0837   0.0029   0.8326
  13.750   1.5748   0.04190   0.03549  -0.0818   0.0028   0.8347
  14.000   1.5814   0.04351   0.03718  -0.0802   0.0027   0.8369
  14.250   1.5871   0.04524   0.03899  -0.0787   0.0027   0.8391
  14.500   1.5914   0.04718   0.04101  -0.0771   0.0027   0.8413
  14.750   1.5950   0.04921   0.04313  -0.0757   0.0026   0.8437
  15.000   1.5980   0.05138   0.04541  -0.0744   0.0026   0.8464
  15.250   1.5999   0.05372   0.04785  -0.0731   0.0025   0.8494
  15.500   1.5998   0.05633   0.05056  -0.0719   0.0025   0.8526
  15.750   1.5999   0.05899   0.05332  -0.0710   0.0024   0.8561
  16.000   1.5978   0.06199   0.05643  -0.0701   0.0024   0.8599
  16.250   1.5944   0.06524   0.05980  -0.0694   0.0024   0.8644
  16.500   1.5908   0.06862   0.06329  -0.0689   0.0024   0.8692
  16.750   1.5852   0.07232   0.06712  -0.0685   0.0023   0.8743
  17.000   1.5788   0.07621   0.07113  -0.0684   0.0023   0.8806
  17.500   1.5609   0.08497   0.08017  -0.0689   0.0022   0.8982
  17.750   1.5491   0.08979   0.08517  -0.0694   0.0022   0.9185
  18.000   1.5351   0.09470   0.09026  -0.0700   0.0022   0.9981
  18.250   1.5229   0.09995   0.09563  -0.0712   0.0022   0.9981
  18.500   1.5081   0.10575   0.10155  -0.0728   0.0022   0.9981
  18.750   1.4947   0.11144   0.10735  -0.0746   0.0022   0.9981
  19.000   1.4802   0.11738   0.11342  -0.0767   0.0022   0.9981
  19.250   1.4645   0.12361   0.11976  -0.0791   0.0022   0.9981
<< Back to EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)