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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 500,000
Max Cl/Cd: 85.61 at α=-1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc21010-il-500000-n5.txt
Download as CSV file: xf-sc21010-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.8409   0.08011   0.07703  -0.0528   0.9999   0.0145
 -16.750  -0.8881   0.06657   0.06327  -0.0616   0.9999   0.0144
 -16.500  -0.9158   0.05758   0.05409  -0.0679   0.9999   0.0144
 -16.250  -0.9350   0.05085   0.04720  -0.0726   0.9999   0.0144
 -16.000  -0.9499   0.04559   0.04178  -0.0758   0.9999   0.0144
 -15.750  -0.9634   0.04152   0.03757  -0.0773   0.9999   0.0145
 -15.500  -0.9789   0.03840   0.03433  -0.0768   0.9999   0.0145
 -15.250  -0.9993   0.03607   0.03192  -0.0741   0.9999   0.0146
 -15.000  -1.0052   0.03360   0.02930  -0.0740   0.9999   0.0147
 -14.750  -0.9817   0.03069   0.02616  -0.0796   0.9977   0.0149
 -14.500  -0.9543   0.02840   0.02364  -0.0843   0.9958   0.0151
 -14.250  -0.9260   0.02654   0.02158  -0.0880   0.9945   0.0153
 -14.000  -0.8984   0.02479   0.01970  -0.0911   0.9930   0.0157
 -13.750  -0.8703   0.02356   0.01837  -0.0934   0.9913   0.0160
 -13.500  -0.8408   0.02258   0.01730  -0.0956   0.9898   0.0164
 -13.250  -0.8103   0.02169   0.01632  -0.0977   0.9883   0.0169
 -13.000  -0.7791   0.02079   0.01531  -0.0999   0.9871   0.0174
 -12.750  -0.7473   0.01987   0.01427  -0.1021   0.9860   0.0179
 -12.500  -0.7151   0.01899   0.01327  -0.1042   0.9851   0.0183
 -12.250  -0.6826   0.01820   0.01236  -0.1063   0.9843   0.0188
 -12.000  -0.6493   0.01730   0.01138  -0.1087   0.9836   0.0193
 -11.750  -0.6180   0.01663   0.01067  -0.1104   0.9821   0.0200
 -11.500  -0.5873   0.01607   0.01007  -0.1118   0.9800   0.0206
 -11.250  -0.5551   0.01552   0.00946  -0.1135   0.9784   0.0215
 -11.000  -0.5223   0.01501   0.00888  -0.1152   0.9770   0.0224
 -10.750  -0.4888   0.01448   0.00829  -0.1171   0.9759   0.0234
 -10.500  -0.4548   0.01396   0.00775  -0.1191   0.9749   0.0246
 -10.250  -0.4209   0.01354   0.00729  -0.1209   0.9739   0.0259
 -10.000  -0.3870   0.01313   0.00684  -0.1227   0.9730   0.0272
  -9.750  -0.3527   0.01269   0.00636  -0.1246   0.9721   0.0286
  -9.500  -0.3184   0.01229   0.00595  -0.1265   0.9712   0.0304
  -9.250  -0.2877   0.01199   0.00563  -0.1274   0.9686   0.0324
  -9.000  -0.2563   0.01168   0.00529  -0.1286   0.9661   0.0345
  -8.750  -0.2236   0.01134   0.00495  -0.1300   0.9642   0.0371
  -8.500  -0.1907   0.01106   0.00465  -0.1314   0.9624   0.0397
  -8.250  -0.1575   0.01076   0.00435  -0.1328   0.9608   0.0432
  -8.000  -0.1242   0.01049   0.00409  -0.1343   0.9593   0.0476
  -7.750  -0.0906   0.01021   0.00384  -0.1358   0.9580   0.0538
  -7.500  -0.0588   0.00998   0.00363  -0.1369   0.9556   0.0616
  -7.250  -0.0283   0.00976   0.00345  -0.1377   0.9521   0.0716
  -7.000   0.0036   0.00951   0.00327  -0.1388   0.9492   0.0870
  -6.750   0.0360   0.00927   0.00309  -0.1400   0.9465   0.1050
  -6.500   0.0687   0.00903   0.00292  -0.1412   0.9443   0.1264
  -6.000   0.1333   0.00846   0.00264  -0.1437   0.9385   0.2023
  -5.750   0.1660   0.00813   0.00252  -0.1451   0.9355   0.2610
  -5.500   0.1990   0.00782   0.00243  -0.1465   0.9327   0.3249
  -5.250   0.2318   0.00758   0.00237  -0.1478   0.9301   0.3815
  -5.000   0.2638   0.00743   0.00232  -0.1488   0.9277   0.4221
  -4.750   0.2939   0.00735   0.00234  -0.1493   0.9237   0.4493
  -4.500   0.3243   0.00727   0.00235  -0.1498   0.9199   0.4779
  -4.250   0.3546   0.00722   0.00235  -0.1503   0.9165   0.4974
  -4.000   0.3852   0.00718   0.00234  -0.1508   0.9135   0.5145
  -3.750   0.4151   0.00714   0.00238  -0.1512   0.9096   0.5342
  -3.500   0.4446   0.00712   0.00242  -0.1514   0.9046   0.5543
  -3.250   0.4742   0.00707   0.00238  -0.1515   0.8975   0.5699
  -3.000   0.5022   0.00703   0.00235  -0.1512   0.8834   0.5803
  -2.750   0.5298   0.00702   0.00231  -0.1507   0.8646   0.5900
  -2.500   0.5577   0.00702   0.00229  -0.1504   0.8449   0.6012
  -2.250   0.5855   0.00707   0.00229  -0.1501   0.8219   0.6114
  -2.000   0.6125   0.00718   0.00230  -0.1495   0.7860   0.6218
  -1.750   0.6378   0.00745   0.00234  -0.1486   0.7242   0.6319
  -1.500   0.6561   0.00845   0.00259  -0.1464   0.5610   0.6419
  -1.250   0.6768   0.00945   0.00299  -0.1452   0.4249   0.6517
  -1.000   0.6997   0.01026   0.00333  -0.1443   0.3153   0.6605
  -0.750   0.7236   0.01096   0.00365  -0.1437   0.2268   0.6695
  -0.500   0.7483   0.01153   0.00395  -0.1432   0.1604   0.6778
  -0.250   0.7740   0.01199   0.00422  -0.1427   0.1187   0.6865
   0.000   0.8000   0.01237   0.00449  -0.1423   0.0901   0.6938
   0.250   0.8265   0.01269   0.00475  -0.1420   0.0738   0.7010
   0.500   0.8530   0.01301   0.00500  -0.1416   0.0605   0.7075
   0.750   0.8793   0.01332   0.00528  -0.1412   0.0517   0.7135
   1.000   0.9056   0.01364   0.00558  -0.1408   0.0459   0.7199
   1.250   0.9319   0.01393   0.00588  -0.1404   0.0419   0.7260
   1.500   0.9577   0.01427   0.00622  -0.1399   0.0384   0.7329
   1.750   0.9839   0.01456   0.00654  -0.1394   0.0361   0.7397
   2.000   1.0095   0.01489   0.00690  -0.1389   0.0336   0.7457
   2.250   1.0349   0.01528   0.00729  -0.1383   0.0315   0.7517
   2.500   1.0606   0.01560   0.00764  -0.1378   0.0297   0.7568
   2.750   1.0858   0.01596   0.00804  -0.1371   0.0281   0.7617
   3.000   1.1104   0.01640   0.00848  -0.1364   0.0266   0.7673
   3.250   1.1351   0.01682   0.00895  -0.1356   0.0255   0.7728
   3.500   1.1595   0.01722   0.00940  -0.1349   0.0243   0.7784
   3.750   1.1840   0.01763   0.00986  -0.1341   0.0232   0.7849
   4.000   1.2077   0.01809   0.01033  -0.1332   0.0221   0.7904
   4.250   1.2308   0.01863   0.01091  -0.1322   0.0211   0.7959
   4.500   1.2544   0.01911   0.01146  -0.1313   0.0204   0.8011
   4.750   1.2774   0.01962   0.01204  -0.1303   0.0197   0.8053
   5.000   1.3001   0.02015   0.01262  -0.1292   0.0190   0.8099
   5.250   1.3226   0.02069   0.01321  -0.1282   0.0184   0.8148
   5.500   1.3444   0.02131   0.01387  -0.1270   0.0179   0.8192
   5.750   1.3643   0.02211   0.01472  -0.1255   0.0174   0.8240
   6.000   1.3854   0.02277   0.01548  -0.1242   0.0170   0.8296
   6.250   1.4059   0.02347   0.01627  -0.1228   0.0167   0.8345
   6.500   1.4259   0.02417   0.01708  -0.1213   0.0162   0.8391
   6.750   1.4457   0.02487   0.01787  -0.1198   0.0158   0.8440
   7.000   1.4653   0.02556   0.01863  -0.1183   0.0154   0.8487
   7.250   1.4838   0.02627   0.01943  -0.1167   0.0150   0.8531
   7.500   1.5015   0.02703   0.02026  -0.1149   0.0147   0.8579
   7.750   1.5177   0.02789   0.02121  -0.1129   0.0145   0.8628
   8.000   1.5315   0.02886   0.02228  -0.1106   0.0142   0.8679
   8.250   1.5424   0.03010   0.02361  -0.1078   0.0139   0.8738
   8.500   1.5539   0.03109   0.02476  -0.1050   0.0138   0.8799
   8.750   1.5632   0.03216   0.02599  -0.1020   0.0137   0.8872
   9.000   1.5723   0.03334   0.02735  -0.0991   0.0135   0.8950
   9.250   1.5804   0.03461   0.02879  -0.0961   0.0133   0.9039
   9.500   1.5868   0.03596   0.03032  -0.0930   0.0131   0.9154
  10.000   1.5939   0.03893   0.03364  -0.0864   0.0128   1.0001
  10.250   1.5974   0.04074   0.03561  -0.0836   0.0127   1.0001
  10.500   1.5997   0.04270   0.03773  -0.0809   0.0126   1.0001
  10.750   1.6004   0.04482   0.04001  -0.0783   0.0124   1.0001
  11.000   1.6001   0.04708   0.04243  -0.0758   0.0123   1.0001
  11.250   1.5986   0.04952   0.04502  -0.0736   0.0122   1.0001
  11.500   1.5952   0.05223   0.04789  -0.0716   0.0121   1.0001
  11.750   1.5914   0.05510   0.05091  -0.0699   0.0119   1.0001
  12.000   1.5850   0.05841   0.05437  -0.0686   0.0118   1.0001
  12.250   1.5764   0.06216   0.05828  -0.0677   0.0118   1.0001
  12.500   1.5665   0.06633   0.06261  -0.0674   0.0117   1.0001
  12.750   1.5551   0.07099   0.06743  -0.0678   0.0116   1.0001
  13.000   1.5386   0.07687   0.07349  -0.0692   0.0116   1.0001
  13.250   1.5201   0.08379   0.08061  -0.0720   0.0115   1.0001
  13.500   1.4919   0.09352   0.09059  -0.0773   0.0115   1.0001
  13.750   1.4522   0.10717   0.10454  -0.0861   0.0116   1.0001
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