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NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.43 at α=-2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc21006-il-1000000.txt
Download as CSV file: xf-sc21006-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-1006 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4322   0.10731   0.10576  -0.0192   0.9999   0.0092
 -12.750  -0.4345   0.10374   0.10220  -0.0191   0.9999   0.0092
 -12.500  -0.4455   0.09722   0.09570  -0.0201   0.9998   0.0094
 -12.250  -0.4464   0.09215   0.09064  -0.0219   0.9995   0.0097
 -12.000  -0.4439   0.08779   0.08628  -0.0236   0.9990   0.0098
 -11.750  -0.4413   0.08332   0.08182  -0.0256   0.9984   0.0099
 -11.500  -0.4374   0.07928   0.07777  -0.0274   0.9977   0.0102
 -11.250  -0.4350   0.07463   0.07313  -0.0297   0.9970   0.0103
 -11.000  -0.4332   0.06980   0.06831  -0.0323   0.9962   0.0105
 -10.750  -0.4319   0.06466   0.06317  -0.0353   0.9953   0.0107
 -10.500  -0.4312   0.05944   0.05796  -0.0388   0.9941   0.0110
 -10.250  -0.4343   0.05406   0.05259  -0.0424   0.9905   0.0111
  -9.750  -0.4371   0.03036   0.02777  -0.0934   0.9875   0.0094
  -9.500  -0.3963   0.02275   0.01943  -0.1020   0.9874   0.0094
  -9.250  -0.3586   0.01861   0.01476  -0.1067   0.9874   0.0095
  -9.000  -0.3218   0.01525   0.01096  -0.1103   0.9876   0.0097
  -8.750  -0.2887   0.01385   0.00940  -0.1123   0.9875   0.0105
  -8.500  -0.2557   0.01275   0.00816  -0.1140   0.9874   0.0110
  -8.250  -0.2232   0.01199   0.00729  -0.1154   0.9871   0.0118
  -8.000  -0.1907   0.01134   0.00656  -0.1168   0.9869   0.0127
  -7.750  -0.1581   0.01075   0.00589  -0.1182   0.9867   0.0134
  -7.500  -0.1254   0.01026   0.00532  -0.1195   0.9865   0.0139
  -7.250  -0.0929   0.00985   0.00484  -0.1209   0.9863   0.0145
  -7.000  -0.0576   0.00903   0.00390  -0.1229   0.9865   0.0179
  -6.750  -0.0252   0.00879   0.00363  -0.1241   0.9862   0.0208
  -6.500   0.0078   0.00850   0.00328  -0.1255   0.9859   0.0261
  -6.250   0.0407   0.00826   0.00306  -0.1268   0.9857   0.0383
  -6.000   0.0743   0.00789   0.00291  -0.1285   0.9856   0.0945
  -5.750   0.1075   0.00757   0.00282  -0.1301   0.9856   0.1594
  -5.500   0.1416   0.00717   0.00276  -0.1320   0.9858   0.2675
  -5.250   0.1747   0.00693   0.00274  -0.1335   0.9857   0.3417
  -5.000   0.2073   0.00676   0.00274  -0.1349   0.9856   0.4059
  -4.750   0.2397   0.00665   0.00275  -0.1361   0.9854   0.4494
  -4.500   0.2723   0.00652   0.00280  -0.1374   0.9852   0.5115
  -4.250   0.3047   0.00645   0.00283  -0.1385   0.9848   0.5494
  -4.000   0.3380   0.00638   0.00284  -0.1398   0.9844   0.5774
  -3.750   0.3750   0.00624   0.00279  -0.1419   0.9836   0.6058
  -3.500   0.4052   0.00605   0.00267  -0.1423   0.9789   0.6299
  -3.250   0.4495   0.00563   0.00235  -0.1457   0.9756   0.6576
  -3.000   0.4972   0.00505   0.00186  -0.1496   0.9702   0.6849
  -2.750   0.5254   0.00478   0.00162  -0.1491   0.9575   0.7015
  -2.500   0.5502   0.00466   0.00153  -0.1479   0.9406   0.7151
  -2.250   0.5761   0.00461   0.00148  -0.1470   0.9197   0.7274
  -2.000   0.6026   0.00462   0.00148  -0.1464   0.8950   0.7377
  -1.750   0.6179   0.00566   0.00159  -0.1431   0.6756   0.7470
  -1.500   0.6338   0.00740   0.00208  -0.1410   0.3735   0.7566
  -1.250   0.6550   0.00861   0.00247  -0.1400   0.1596   0.7659
  -1.000   0.6794   0.00933   0.00278  -0.1394   0.0545   0.7748
  -0.750   0.7059   0.00970   0.00304  -0.1391   0.0292   0.7841
  -0.500   0.7324   0.01004   0.00342  -0.1386   0.0216   0.7919
  -0.250   0.7592   0.01031   0.00372  -0.1383   0.0183   0.7997
   0.000   0.7840   0.01108   0.00461  -0.1374   0.0144   0.8079
   0.250   0.8105   0.01139   0.00497  -0.1369   0.0139   0.8157
   0.500   0.8365   0.01182   0.00546  -0.1364   0.0133   0.8235
   0.750   0.8621   0.01231   0.00602  -0.1357   0.0125   0.8303
   1.000   0.8876   0.01285   0.00662  -0.1351   0.0117   0.8380
   1.250   0.9127   0.01343   0.00728  -0.1344   0.0109   0.8445
   1.500   0.9375   0.01422   0.00814  -0.1335   0.0103   0.8518
   1.750   0.9599   0.01588   0.00993  -0.1322   0.0095   0.8585
   2.000   0.9828   0.01873   0.01306  -0.1307   0.0092   0.8660
   2.250   1.0074   0.01980   0.01432  -0.1297   0.0090   0.8738
   2.500   1.0322   0.02077   0.01548  -0.1288   0.0087   0.8817
   2.750   1.0557   0.02237   0.01733  -0.1276   0.0084   0.8893
   3.000   1.0768   0.02533   0.02069  -0.1255   0.0079   0.8966
   7.750   1.0119   0.14049   0.13932  -0.1227   0.0080   1.0001
   8.000   1.0107   0.14618   0.14500  -0.1255   0.0074   1.0001
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