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NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.11 at α=-0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20710-il-1000000.txt
Download as CSV file: xf-sc20710-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0710 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.9616   0.07910   0.07673  -0.0477   1.0000   0.0141
 -16.000  -1.0135   0.06418   0.06152  -0.0581   1.0000   0.0139
 -15.750  -1.0374   0.05639   0.05354  -0.0633   1.0000   0.0139
 -15.500  -1.0542   0.05073   0.04772  -0.0664   1.0000   0.0140
 -15.250  -1.0667   0.04629   0.04313  -0.0682   1.0000   0.0140
 -15.000  -1.0754   0.04279   0.03950  -0.0691   1.0000   0.0141
 -14.750  -1.0828   0.03978   0.03637  -0.0691   1.0000   0.0142
 -14.500  -1.0887   0.03724   0.03372  -0.0685   1.0000   0.0142
 -14.250  -1.0947   0.03506   0.03142  -0.0672   1.0000   0.0143
 -14.000  -1.1026   0.03323   0.02949  -0.0648   1.0000   0.0144
 -13.750  -1.1163   0.03181   0.02800  -0.0606   1.0000   0.0145
 -13.500  -1.1195   0.03030   0.02638  -0.0582   1.0000   0.0146
 -13.250  -1.1148   0.02888   0.02486  -0.0571   1.0000   0.0148
 -13.000  -1.1049   0.02759   0.02347  -0.0565   1.0000   0.0150
 -12.750  -1.0919   0.02626   0.02203  -0.0564   1.0000   0.0152
 -12.500  -1.0765   0.02498   0.02062  -0.0563   1.0000   0.0153
 -12.250  -1.0562   0.02376   0.01928  -0.0568   0.9998   0.0155
 -12.000  -1.0278   0.02258   0.01796  -0.0587   0.9990   0.0156
 -11.750  -0.9986   0.02156   0.01683  -0.0604   0.9983   0.0158
 -11.500  -0.9688   0.02068   0.01586  -0.0621   0.9975   0.0159
 -11.250  -0.9407   0.01871   0.01372  -0.0643   0.9968   0.0164
 -11.000  -0.9101   0.01762   0.01255  -0.0663   0.9961   0.0168
 -10.750  -0.8785   0.01690   0.01178  -0.0681   0.9955   0.0172
 -10.500  -0.8465   0.01629   0.01113  -0.0698   0.9950   0.0176
 -10.250  -0.8141   0.01572   0.01051  -0.0716   0.9946   0.0181
 -10.000  -0.7814   0.01518   0.00992  -0.0733   0.9942   0.0186
  -9.750  -0.7499   0.01471   0.00940  -0.0747   0.9933   0.0192
  -9.500  -0.7190   0.01433   0.00897  -0.0759   0.9922   0.0196
  -9.250  -0.6862   0.01349   0.00808  -0.0778   0.9914   0.0206
  -9.000  -0.6538   0.01303   0.00761  -0.0794   0.9905   0.0215
  -8.750  -0.6212   0.01268   0.00725  -0.0809   0.9896   0.0225
  -8.500  -0.5884   0.01236   0.00690  -0.0824   0.9888   0.0236
  -8.250  -0.5548   0.01187   0.00639  -0.0841   0.9882   0.0255
  -8.000  -0.5217   0.01158   0.00612  -0.0857   0.9876   0.0275
  -7.750  -0.4888   0.01139   0.00591  -0.0870   0.9869   0.0293
  -7.500  -0.4545   0.01096   0.00550  -0.0889   0.9864   0.0327
  -7.250  -0.4212   0.01077   0.00531  -0.0904   0.9859   0.0351
  -7.000  -0.3870   0.01045   0.00499  -0.0921   0.9855   0.0382
  -6.750  -0.3532   0.01023   0.00480  -0.0937   0.9851   0.0411
  -6.500  -0.3194   0.01007   0.00463  -0.0952   0.9846   0.0431
  -6.250  -0.2846   0.00977   0.00435  -0.0971   0.9843   0.0475
  -6.000  -0.2504   0.00959   0.00418  -0.0987   0.9840   0.0512
  -5.750  -0.2157   0.00935   0.00398  -0.1004   0.9837   0.0574
  -5.500  -0.1863   0.00916   0.00383  -0.1010   0.9818   0.0653
  -5.250  -0.1543   0.00892   0.00366  -0.1022   0.9802   0.0791
  -5.000  -0.1205   0.00865   0.00350  -0.1037   0.9791   0.1016
  -4.750  -0.0855   0.00834   0.00334  -0.1057   0.9784   0.1368
  -4.500  -0.0493   0.00795   0.00318  -0.1080   0.9779   0.1943
  -4.250  -0.0116   0.00745   0.00303  -0.1108   0.9777   0.2839
  -4.000   0.0276   0.00688   0.00287  -0.1140   0.9779   0.4000
  -3.750   0.0680   0.00631   0.00275  -0.1174   0.9782   0.5323
  -3.500   0.1041   0.00613   0.00270  -0.1193   0.9770   0.5797
  -3.250   0.1409   0.00600   0.00261  -0.1211   0.9758   0.6033
  -3.000   0.1785   0.00586   0.00252  -0.1232   0.9748   0.6217
  -2.750   0.2181   0.00567   0.00234  -0.1255   0.9732   0.6347
  -2.500   0.2523   0.00546   0.00215  -0.1265   0.9676   0.6434
  -2.250   0.2844   0.00534   0.00206  -0.1272   0.9623   0.6531
  -2.000   0.3165   0.00528   0.00198  -0.1277   0.9562   0.6632
  -1.750   0.3450   0.00520   0.00193  -0.1275   0.9456   0.6687
  -1.500   0.3735   0.00517   0.00188  -0.1273   0.9330   0.6724
  -1.250   0.4019   0.00516   0.00183  -0.1271   0.9172   0.6755
  -1.000   0.4302   0.00519   0.00180  -0.1268   0.8990   0.6794
  -0.750   0.4577   0.00525   0.00184  -0.1264   0.8758   0.6842
  -0.500   0.4848   0.00538   0.00187  -0.1259   0.8427   0.6885
  -0.250   0.5065   0.00599   0.00195  -0.1242   0.7177   0.6930
   0.000   0.5251   0.00711   0.00227  -0.1223   0.5279   0.6972
   0.250   0.5472   0.00801   0.00257  -0.1213   0.3768   0.7007
   0.500   0.5714   0.00871   0.00281  -0.1207   0.2615   0.7034
   0.750   0.5971   0.00925   0.00301  -0.1203   0.1815   0.7057
   1.000   0.6235   0.00970   0.00320  -0.1201   0.1253   0.7078
   1.250   0.6507   0.01003   0.00338  -0.1199   0.0946   0.7097
   1.500   0.6780   0.01029   0.00355  -0.1198   0.0745   0.7120
   1.750   0.7054   0.01054   0.00373  -0.1196   0.0627   0.7141
   2.000   0.7328   0.01076   0.00395  -0.1194   0.0553   0.7162
   2.250   0.7601   0.01103   0.00417  -0.1192   0.0492   0.7183
   2.500   0.7877   0.01123   0.00437  -0.1190   0.0462   0.7204
   2.750   0.8153   0.01144   0.00458  -0.1189   0.0432   0.7228
   3.000   0.8422   0.01178   0.00489  -0.1186   0.0395   0.7250
   3.250   0.8699   0.01196   0.00507  -0.1185   0.0379   0.7270
   3.500   0.8971   0.01216   0.00528  -0.1183   0.0356   0.7291
   3.750   0.9232   0.01256   0.00568  -0.1178   0.0324   0.7310
   4.000   0.9505   0.01274   0.00589  -0.1176   0.0307   0.7330
   4.250   0.9772   0.01301   0.00614  -0.1173   0.0284   0.7351
   4.500   1.0033   0.01340   0.00654  -0.1169   0.0260   0.7372
   4.750   1.0302   0.01365   0.00681  -0.1166   0.0244   0.7394
   5.000   1.0565   0.01399   0.00712  -0.1162   0.0229   0.7414
   5.250   1.0817   0.01451   0.00768  -0.1156   0.0216   0.7433
   5.500   1.1077   0.01482   0.00804  -0.1152   0.0209   0.7456
   5.750   1.1334   0.01519   0.00845  -0.1146   0.0201   0.7476
   6.000   1.1588   0.01557   0.00886  -0.1141   0.0194   0.7498
   6.250   1.1839   0.01601   0.00933  -0.1135   0.0188   0.7522
   6.500   1.2077   0.01666   0.01001  -0.1126   0.0182   0.7545
   6.750   1.2300   0.01756   0.01099  -0.1115   0.0177   0.7566
   7.000   1.2546   0.01806   0.01154  -0.1108   0.0174   0.7584
   7.250   1.2787   0.01856   0.01212  -0.1101   0.0172   0.7607
   7.500   1.3027   0.01907   0.01270  -0.1093   0.0168   0.7627
   7.750   1.3262   0.01962   0.01333  -0.1084   0.0164   0.7647
   8.000   1.3493   0.02022   0.01400  -0.1075   0.0161   0.7669
   8.250   1.3719   0.02087   0.01472  -0.1065   0.0158   0.7691
   8.500   1.3942   0.02154   0.01544  -0.1055   0.0155   0.7713
   8.750   1.4159   0.02226   0.01623  -0.1044   0.0152   0.7733
   9.000   1.4367   0.02307   0.01711  -0.1032   0.0150   0.7754
   9.250   1.4553   0.02415   0.01829  -0.1016   0.0147   0.7775
   9.500   1.4703   0.02576   0.02008  -0.0995   0.0144   0.7794
   9.750   1.4810   0.02805   0.02262  -0.0968   0.0142   0.7814
  10.000   1.4984   0.02904   0.02374  -0.0951   0.0141   0.7837
  10.250   1.5144   0.03013   0.02496  -0.0932   0.0140   0.7861
  10.500   1.5288   0.03136   0.02633  -0.0911   0.0139   0.7883
  10.750   1.5413   0.03268   0.02781  -0.0888   0.0138   0.7902
  11.000   1.5512   0.03412   0.02943  -0.0861   0.0137   0.7924
  11.250   1.5578   0.03572   0.03121  -0.0830   0.0136   0.7945
  11.500   1.5602   0.03734   0.03300  -0.0793   0.0135   0.7967
  11.750   1.5570   0.03889   0.03471  -0.0746   0.0134   0.7991
  12.000   1.5548   0.04064   0.03661  -0.0706   0.0133   0.8014
  12.250   1.5514   0.04259   0.03872  -0.0668   0.0132   0.8036
  12.500   1.5455   0.04487   0.04116  -0.0633   0.0131   0.8055
  12.750   1.5380   0.04740   0.04387  -0.0601   0.0130   0.8076
  13.000   1.5259   0.05059   0.04724  -0.0572   0.0129   0.8095
  13.250   1.5110   0.05436   0.05121  -0.0551   0.0129   0.8112
  13.500   1.4907   0.05919   0.05625  -0.0539   0.0128   0.8129
  13.750   1.4677   0.06512   0.06238  -0.0546   0.0128   0.8145
  14.000   1.4360   0.07375   0.07125  -0.0584   0.0128   0.8158
  14.250   1.3823   0.09036   0.08820  -0.0705   0.0130   0.8164
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