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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 100,000
Max Cl/Cd: 42.8 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-100000.txt
Download as CSV file: xf-glennmartin4-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 4                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3846   0.11898   0.11506  -0.0237   1.0000   0.0885
  -8.000  -0.4069   0.11702   0.11320  -0.0242   1.0000   0.0887
  -7.750  -0.4297   0.11513   0.11138  -0.0237   1.0000   0.0888
  -7.500  -0.3945   0.10979   0.10607  -0.0192   1.0000   0.0918
  -7.250  -0.3963   0.10759   0.10393  -0.0170   1.0000   0.0939
  -7.000  -0.4099   0.10551   0.10192  -0.0155   1.0000   0.0955
  -6.750  -0.4300   0.10374   0.10025  -0.0138   1.0000   0.0962
  -6.500  -0.4204   0.09958   0.09600  -0.0237   0.9870   0.1006
  -6.250  -0.4270   0.09350   0.08964  -0.0350   0.9680   0.1040
  -6.000  -0.3933   0.08920   0.08548  -0.0346   0.9606   0.1070
  -5.750  -0.3726   0.08531   0.08152  -0.0376   0.9494   0.1114
  -5.500  -0.3769   0.08051   0.07624  -0.0426   0.9310   0.1188
  -5.250  -0.3471   0.07585   0.07178  -0.0433   0.9242   0.1224
  -5.000  -0.3412   0.07290   0.06830  -0.0449   0.9069   0.1343
  -4.750  -0.3045   0.06802   0.06370  -0.0468   0.9022   0.1411
  -4.500  -0.2901   0.06418   0.05956  -0.0476   0.8890   0.1529
  -4.250  -0.2737   0.06104   0.05616  -0.0472   0.8756   0.1683
  -4.000  -0.2503   0.05758   0.05278  -0.0468   0.8636   0.1771
  -3.750  -0.2327   0.05498   0.04994  -0.0459   0.8511   0.1979
  -3.000  -0.1698   0.04038   0.03294  -0.0378   0.8211   0.1017
  -2.750  -0.1389   0.03754   0.02966  -0.0372   0.8140   0.1015
  -2.500  -0.1146   0.03525   0.02701  -0.0354   0.8029   0.1009
  -2.250  -0.0753   0.03273   0.02400  -0.0359   0.7977   0.1020
  -2.000  -0.0445   0.03078   0.02175  -0.0356   0.7876   0.1053
  -1.750   0.0052   0.02852   0.01934  -0.0386   0.7819   0.1101
  -1.500   0.0478   0.02703   0.01756  -0.0403   0.7729   0.1186
  -1.250   0.1046   0.02502   0.01552  -0.0451   0.7656   0.1319
  -1.000   0.4662   0.01993   0.01334  -0.1127   0.7632   1.0000
  -0.750   0.5153   0.01945   0.01242  -0.1168   0.7407   1.0000
  -0.500   0.5657   0.01910   0.01167  -0.1214   0.7177   1.0000
  -0.250   0.6155   0.01894   0.01109  -0.1260   0.6948   1.0000
   0.000   0.6529   0.01900   0.01083  -0.1281   0.6729   1.0000
   0.250   0.6918   0.01915   0.01064  -0.1306   0.6522   1.0000
   0.500   0.7303   0.01941   0.01057  -0.1331   0.6331   1.0000
   0.750   0.7661   0.01974   0.01060  -0.1351   0.6150   1.0000
   1.000   0.7955   0.02010   0.01074  -0.1358   0.5985   1.0000
   1.250   0.8201   0.02047   0.01092  -0.1354   0.5825   1.0000
   1.500   0.8420   0.02086   0.01116  -0.1345   0.5682   1.0000
   1.750   0.8651   0.02128   0.01143  -0.1339   0.5550   1.0000
   2.000   0.8938   0.02171   0.01170  -0.1345   0.5433   1.0000
   2.250   0.9207   0.02214   0.01196  -0.1346   0.5319   1.0000
   2.500   0.9354   0.02254   0.01235  -0.1323   0.5219   1.0000
   2.750   0.9690   0.02302   0.01262  -0.1339   0.5123   1.0000
   3.000   0.9775   0.02337   0.01300  -0.1302   0.5037   1.0000
   3.250   1.0140   0.02389   0.01334  -0.1325   0.4958   1.0000
   3.500   1.0209   0.02428   0.01382  -0.1285   0.4883   1.0000
   3.750   1.0530   0.02477   0.01417  -0.1299   0.4815   1.0000
   4.000   1.0674   0.02525   0.01469  -0.1275   0.4753   1.0000
   4.250   1.0831   0.02567   0.01511  -0.1253   0.4687   1.0000
   4.500   1.1231   0.02624   0.01555  -0.1285   0.4629   1.0000
   4.750   1.1230   0.02669   0.01614  -0.1230   0.4574   1.0000
   5.000   1.1419   0.02718   0.01664  -0.1216   0.4520   1.0000
   5.250   1.1829   0.02778   0.01711  -0.1250   0.4472   1.0000
   5.500   1.1816   0.02831   0.01780  -0.1194   0.4423   1.0000
   5.750   1.1935   0.02887   0.01844  -0.1166   0.4376   1.0000
   6.000   1.2203   0.02939   0.01894  -0.1170   0.4333   1.0000
   6.250   1.2463   0.03008   0.01965  -0.1173   0.4290   1.0000
   6.500   1.2437   0.03077   0.02051  -0.1116   0.4249   1.0000
   6.750   1.2557   0.03133   0.02114  -0.1089   0.4203   1.0000
   7.000   1.2844   0.03195   0.02175  -0.1097   0.4167   1.0000
   7.250   1.3017   0.03268   0.02252  -0.1083   0.4126   1.0000
   7.500   1.2946   0.03355   0.02360  -0.1019   0.4090   1.0000
   7.750   1.3013   0.03430   0.02447  -0.0984   0.4051   1.0000
   8.000   1.3263   0.03489   0.02507  -0.0985   0.4013   1.0000
   8.250   1.3533   0.03564   0.02583  -0.0991   0.3974   1.0000
   8.500   1.3322   0.03680   0.02725  -0.0903   0.3941   1.0000
   8.750   1.3277   0.03784   0.02844  -0.0849   0.3902   1.0000
   9.000   1.3476   0.03841   0.02906  -0.0840   0.3861   1.0000
   9.250   1.3970   0.03894   0.02953  -0.0889   0.3822   1.0000
   9.500   1.3566   0.04063   0.03151  -0.0772   0.3794   1.0000
   9.750   1.3280   0.04251   0.03361  -0.0682   0.3762   1.0000
  10.000   1.3248   0.04383   0.03507  -0.0638   0.3724   1.0000
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