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lrn1007 (lrn1007-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: lrn1007 (lrn1007-il)
Reynolds number: 100,000
Max Cl/Cd: 55.31 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lrn1007-il-100000-n5.txt
Download as CSV file: xf-lrn1007-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: lrn1007                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1155   0.10680   0.10153  -0.0853   0.8964   0.0121
  -8.500  -0.1064   0.10444   0.09918  -0.0870   0.8944   0.0121
  -8.250  -0.0976   0.10234   0.09710  -0.0890   0.8922   0.0122
  -8.000  -0.0864   0.09984   0.09460  -0.0914   0.8904   0.0122
  -7.750  -0.0742   0.09722   0.09196  -0.0938   0.8890   0.0122
  -7.500  -0.0616   0.09492   0.08967  -0.0967   0.8872   0.0122
  -7.250  -0.0491   0.09222   0.08697  -0.0989   0.8852   0.0122
  -7.000  -0.0375   0.08905   0.08385  -0.1010   0.8828   0.0123
  -6.750  -0.0333   0.08338   0.07821  -0.0991   0.8812   0.0128
  -6.500  -0.0232   0.07996   0.07479  -0.0996   0.8793   0.0131
  -6.250  -0.0151   0.07630   0.07115  -0.0992   0.8777   0.0140
  -6.000  -0.0018   0.07364   0.06838  -0.1013   0.8759   0.0145
  -5.750   0.0101   0.07137   0.06612  -0.1033   0.8732   0.0150
  -5.500   0.0232   0.06910   0.06385  -0.1055   0.8704   0.0155
  -5.250   0.0387   0.06672   0.06145  -0.1080   0.8678   0.0161
  -5.000   0.0569   0.06427   0.05898  -0.1109   0.8656   0.0166
  -4.750   0.0772   0.06180   0.05644  -0.1139   0.8638   0.0174
  -4.500   0.0990   0.05935   0.05392  -0.1170   0.8619   0.0183
  -4.250   0.1149   0.05744   0.05198  -0.1186   0.8582   0.0196
  -4.000   0.1366   0.05536   0.04981  -0.1209   0.8553   0.0210
  -3.750   0.1653   0.05351   0.04782  -0.1240   0.8531   0.0227
  -3.500   0.2040   0.05285   0.04685  -0.1278   0.8512   0.0240
  -3.250   0.2387   0.05193   0.04561  -0.1303   0.8495   0.0244
  -3.000   0.2471   0.04815   0.04192  -0.1300   0.8456   0.0253
  -2.750   0.2581   0.04493   0.03877  -0.1300   0.8423   0.0279
  -2.500   0.2842   0.04296   0.03665  -0.1313   0.8397   0.0319
  -2.000   0.3470   0.03898   0.03223  -0.1348   0.8362   0.0426
  -1.750   0.3712   0.04114   0.03382  -0.1330   0.8304   0.0505
  -1.250   0.4240   0.03585   0.02824  -0.1350   0.8250   0.0650
  -0.750   0.4718   0.03235   0.02450  -0.1357   0.8186   0.0977
  -0.250   0.5256   0.02990   0.02161  -0.1364   0.8123   0.1601
   0.250   0.5844   0.02889   0.02017  -0.1344   0.8055   0.0974
   0.750   0.6430   0.02812   0.01900  -0.1321   0.7985   0.0299
   1.250   0.6919   0.02721   0.01793  -0.1302   0.7891   0.0188
   1.500   0.7213   0.02647   0.01715  -0.1298   0.7857   0.0160
   1.750   0.7533   0.02580   0.01634  -0.1299   0.7835   0.0143
   2.000   0.7714   0.02594   0.01632  -0.1285   0.7756   0.0138
   2.250   0.8031   0.02557   0.01569  -0.1288   0.7722   0.0227
   2.500   0.8377   0.02512   0.01503  -0.1294   0.7699   0.0457
   2.750   0.8564   0.02401   0.01540  -0.1285   0.7614   1.0000
   3.000   0.8873   0.02383   0.01507  -0.1286   0.7578   1.0000
   3.250   0.9052   0.02418   0.01539  -0.1272   0.7490   1.0000
   3.750   0.9525   0.02427   0.01549  -0.1258   0.7351   1.0000
   4.000   0.9833   0.02389   0.01516  -0.1259   0.7308   1.0000
   4.250   0.9994   0.02417   0.01549  -0.1242   0.7196   1.0000
   4.500   1.0171   0.02435   0.01573  -0.1228   0.7088   1.0000
   4.750   1.0453   0.02392   0.01536  -0.1224   0.7023   1.0000
   5.000   1.0635   0.02399   0.01552  -0.1210   0.6905   1.0000
   5.250   1.0804   0.02409   0.01574  -0.1193   0.6776   1.0000
   5.500   1.0985   0.02404   0.01581  -0.1176   0.6649   1.0000
   5.750   1.1201   0.02381   0.01576  -0.1162   0.6520   1.0000
   6.000   1.1488   0.02077   0.01029  -0.1093   0.3345   1.0000
   6.250   1.1389   0.02331   0.01163  -0.1043   0.1771   1.0000
   6.500   1.1287   0.02663   0.01360  -0.0997   0.0057   1.0000
   6.750   1.1445   0.02762   0.01481  -0.0980   0.0047   1.0000
   7.000   1.1589   0.02877   0.01626  -0.0960   0.0043   1.0000
   7.250   1.1718   0.03009   0.01789  -0.0940   0.0042   1.0000
   7.500   1.1832   0.03158   0.01968  -0.0918   0.0042   1.0000
   7.750   1.1925   0.03327   0.02166  -0.0894   0.0042   1.0000
   8.000   1.1989   0.03523   0.02391  -0.0869   0.0043   1.0000
   8.250   1.2030   0.03743   0.02635  -0.0842   0.0045   1.0000
   8.500   1.2070   0.03975   0.02888  -0.0815   0.0046   1.0000
   8.750   1.2142   0.04223   0.03154  -0.0790   0.0049   1.0000
   9.750   1.3281   0.07047   0.06320  -0.0695   0.0228   1.0000
  10.000   1.3121   0.07367   0.06674  -0.0654   0.0232   1.0000
  10.250   1.2951   0.07698   0.07039  -0.0621   0.0239   1.0000
  10.500   1.2781   0.08086   0.07454  -0.0596   0.0241   1.0000
  10.750   1.2605   0.08495   0.07889  -0.0578   0.0244   1.0000
  11.000   1.2422   0.08935   0.08352  -0.0567   0.0245   1.0000
  11.250   1.2238   0.09399   0.08837  -0.0563   0.0245   1.0000
  11.500   1.2052   0.09893   0.09349  -0.0566   0.0244   1.0000
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