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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 500,000
Max Cl/Cd: 100.79 at α=-0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc21010-il-500000.txt
Download as CSV file: xf-sc21010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-1010 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6108   0.06122   0.05858  -0.0617   0.9999   0.0234
 -14.500  -0.7025   0.06691   0.06409  -0.0627   0.9999   0.0228
 -14.250  -0.7397   0.05774   0.05479  -0.0688   0.9999   0.0226
 -14.000  -0.7712   0.05204   0.04899  -0.0708   0.9999   0.0225
 -13.750  -0.8031   0.04879   0.04569  -0.0688   0.9999   0.0224
 -13.500  -0.8329   0.04586   0.04269  -0.0666   0.9999   0.0223
 -13.250  -0.8508   0.04119   0.03776  -0.0693   0.9999   0.0223
 -13.000  -0.8511   0.03650   0.03267  -0.0723   0.9997   0.0224
 -12.750  -0.8242   0.03207   0.02772  -0.0784   0.9979   0.0228
 -12.500  -0.7932   0.02914   0.02438  -0.0829   0.9965   0.0231
 -12.250  -0.7642   0.02545   0.02039  -0.0868   0.9955   0.0238
 -12.000  -0.7315   0.02431   0.01919  -0.0894   0.9946   0.0244
 -11.750  -0.6981   0.02332   0.01809  -0.0919   0.9937   0.0252
 -11.500  -0.6665   0.02219   0.01682  -0.0939   0.9921   0.0260
 -11.250  -0.6338   0.02094   0.01541  -0.0960   0.9906   0.0267
 -11.000  -0.6003   0.01993   0.01422  -0.0981   0.9893   0.0275
 -10.750  -0.5667   0.01870   0.01283  -0.1003   0.9882   0.0283
 -10.500  -0.5331   0.01749   0.01160  -0.1025   0.9873   0.0295
 -10.250  -0.4986   0.01688   0.01096  -0.1046   0.9863   0.0307
 -10.000  -0.4637   0.01638   0.01039  -0.1067   0.9854   0.0324
  -9.750  -0.4283   0.01598   0.00991  -0.1087   0.9846   0.0337
  -9.500  -0.3921   0.01484   0.00875  -0.1115   0.9841   0.0359
  -9.250  -0.3560   0.01438   0.00829  -0.1138   0.9836   0.0382
  -9.000  -0.3244   0.01401   0.00786  -0.1149   0.9813   0.0402
  -8.750  -0.2897   0.01331   0.00716  -0.1171   0.9797   0.0436
  -8.500  -0.2556   0.01299   0.00684  -0.1188   0.9780   0.0470
  -8.250  -0.2195   0.01254   0.00635  -0.1210   0.9768   0.0507
  -8.000  -0.1832   0.01216   0.00600  -0.1233   0.9756   0.0558
  -7.750  -0.1463   0.01178   0.00561  -0.1256   0.9746   0.0624
  -7.500  -0.1093   0.01146   0.00531  -0.1278   0.9737   0.0712
  -7.250  -0.0713   0.01102   0.00498  -0.1305   0.9731   0.0905
  -7.000  -0.0334   0.01063   0.00472  -0.1331   0.9725   0.1210
  -6.750   0.0048   0.01020   0.00449  -0.1358   0.9720   0.1675
  -6.500   0.0439   0.00968   0.00427  -0.1389   0.9717   0.2461
  -6.250   0.0834   0.00919   0.00412  -0.1421   0.9714   0.3396
  -6.000   0.1219   0.00890   0.00403  -0.1447   0.9710   0.4053
  -5.750   0.1501   0.00880   0.00404  -0.1449   0.9666   0.4434
  -5.500   0.1847   0.00868   0.00401  -0.1465   0.9648   0.4770
  -5.250   0.2198   0.00858   0.00396  -0.1481   0.9633   0.5050
  -5.000   0.2548   0.00848   0.00393  -0.1497   0.9619   0.5286
  -4.750   0.2900   0.00839   0.00389  -0.1512   0.9605   0.5477
  -4.500   0.3250   0.00831   0.00385  -0.1527   0.9593   0.5678
  -4.250   0.3599   0.00823   0.00382  -0.1541   0.9580   0.5827
  -4.000   0.3896   0.00823   0.00387  -0.1545   0.9546   0.5962
  -3.750   0.4192   0.00821   0.00390  -0.1547   0.9505   0.6114
  -3.500   0.4515   0.00813   0.00387  -0.1555   0.9474   0.6267
  -3.250   0.4856   0.00792   0.00370  -0.1564   0.9435   0.6402
  -3.000   0.5123   0.00774   0.00356  -0.1555   0.9336   0.6503
  -2.750   0.5402   0.00753   0.00336  -0.1547   0.9228   0.6600
  -2.500   0.5682   0.00739   0.00321  -0.1541   0.9126   0.6707
  -2.250   0.5945   0.00730   0.00316  -0.1532   0.8997   0.6797
  -1.750   0.6486   0.00723   0.00307  -0.1518   0.8685   0.6980
  -1.500   0.6761   0.00725   0.00308  -0.1513   0.8516   0.7075
  -1.250   0.7033   0.00727   0.00313  -0.1507   0.8333   0.7151
  -1.000   0.7304   0.00735   0.00314  -0.1501   0.8071   0.7235
  -0.750   0.7559   0.00750   0.00320  -0.1491   0.7648   0.7306
  -0.500   0.7772   0.00809   0.00329  -0.1473   0.6520   0.7389
  -0.250   0.7893   0.00973   0.00388  -0.1442   0.4323   0.7451
   0.000   0.8073   0.01108   0.00442  -0.1426   0.2661   0.7527
   0.250   0.8283   0.01206   0.00488  -0.1414   0.1564   0.7589
   0.500   0.8515   0.01277   0.00530  -0.1405   0.0972   0.7652
   0.750   0.8766   0.01330   0.00569  -0.1399   0.0728   0.7720
   1.000   0.9016   0.01371   0.00608  -0.1391   0.0620   0.7774
   1.250   0.9268   0.01417   0.00650  -0.1385   0.0550   0.7841
   1.500   0.9522   0.01454   0.00688  -0.1378   0.0505   0.7901
   1.750   0.9759   0.01512   0.00747  -0.1368   0.0463   0.7961
   2.000   1.0017   0.01548   0.00786  -0.1363   0.0434   0.8027
   2.250   1.0255   0.01593   0.00833  -0.1353   0.0405   0.8075
   2.500   1.0481   0.01667   0.00909  -0.1342   0.0381   0.8130
   2.750   1.0731   0.01710   0.00958  -0.1334   0.0362   0.8185
   3.000   1.0967   0.01758   0.01009  -0.1324   0.0344   0.8231
   3.250   1.1188   0.01835   0.01085  -0.1313   0.0326   0.8288
   3.500   1.1413   0.01914   0.01171  -0.1301   0.0312   0.8341
   3.750   1.1647   0.01962   0.01226  -0.1291   0.0298   0.8394
   4.000   1.1882   0.02022   0.01290  -0.1281   0.0286   0.8457
   4.250   1.2107   0.02083   0.01354  -0.1270   0.0276   0.8509
   4.500   1.2315   0.02191   0.01464  -0.1256   0.0266   0.8563
   4.750   1.2538   0.02316   0.01599  -0.1245   0.0259   0.8616
   5.000   1.2763   0.02391   0.01686  -0.1234   0.0253   0.8662
   5.250   1.2987   0.02482   0.01788  -0.1222   0.0246   0.8715
   5.750   1.3423   0.02645   0.01970  -0.1199   0.0232   0.8821
   6.000   1.3634   0.02723   0.02054  -0.1187   0.0226   0.8884
   6.250   1.3835   0.02825   0.02162  -0.1173   0.0221   0.8945
   6.500   1.4021   0.03075   0.02428  -0.1160   0.0215   0.9007
   6.750   1.4196   0.03230   0.02608  -0.1141   0.0212   0.9073
   7.000   1.4354   0.03373   0.02777  -0.1120   0.0209   0.9147
   7.250   1.4490   0.03557   0.02989  -0.1096   0.0206   0.9231
   7.750   1.4629   0.04005   0.03503  -0.1028   0.0201   1.0001
   8.000   1.4662   0.04323   0.03856  -0.0995   0.0199   1.0001
   8.250   1.4624   0.04675   0.04244  -0.0954   0.0197   1.0001
   8.500   1.4512   0.05017   0.04620  -0.0903   0.0196   1.0001
   8.750   1.4333   0.05349   0.04980  -0.0847   0.0194   1.0001
   9.000   1.4080   0.05785   0.05446  -0.0793   0.0194   1.0001
   9.250   1.3789   0.06283   0.05975  -0.0749   0.0194   1.0001
   9.500   1.3382   0.06975   0.06701  -0.0718   0.0195   1.0001
   9.750   1.2929   0.07820   0.07577  -0.0714   0.0198   1.0001
  10.000   1.2520   0.08742   0.08523  -0.0742   0.0201   1.0001
  10.250   1.2100   0.09930   0.09734  -0.0815   0.0203   1.0001
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