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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 100,000
Max Cl/Cd: 66.89 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gm15sm-il-100000-n5.txt
Download as CSV file: xf-gm15sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GM15 (smoothed)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3488   0.10592   0.10099  -0.0307   1.0000   0.0482
  -8.000  -0.3533   0.10418   0.09934  -0.0308   1.0000   0.0484
  -7.750  -0.3592   0.10239   0.09765  -0.0302   1.0000   0.0485
  -7.500  -0.3634   0.10032   0.09567  -0.0299   1.0000   0.0486
  -7.250  -0.3647   0.09780   0.09323  -0.0304   1.0000   0.0487
  -7.000  -0.3642   0.09513   0.09061  -0.0312   1.0000   0.0487
  -6.750  -0.3635   0.09077   0.08632  -0.0282   1.0000   0.0494
  -6.500  -0.3618   0.08779   0.08338  -0.0269   1.0000   0.0498
  -6.250  -0.3598   0.08500   0.08064  -0.0265   1.0000   0.0501
  -5.750  -0.3514   0.07761   0.07326  -0.0269   1.0000   0.0341
  -5.500  -0.3466   0.07454   0.07022  -0.0274   1.0000   0.0322
  -5.250  -0.3339   0.07040   0.06608  -0.0311   0.9993   0.0303
  -4.750  -0.2351   0.05150   0.04683  -0.0623   0.9896   0.0248
  -4.500  -0.1795   0.04123   0.03618  -0.0779   0.9867   0.0243
  -4.250  -0.1210   0.03220   0.02619  -0.0916   0.9846   0.0247
  -4.000  -0.0802   0.02809   0.02152  -0.0973   0.9810   0.0274
  -3.750  -0.0400   0.02521   0.01803  -0.1012   0.9775   0.0292
  -3.500   0.0003   0.02272   0.01494  -0.1042   0.9747   0.0305
  -3.250   0.0350   0.02097   0.01277  -0.1057   0.9697   0.0324
  -3.000   0.0719   0.01969   0.01113  -0.1074   0.9653   0.0357
  -2.750   0.1104   0.01859   0.00995  -0.1098   0.9618   0.0436
  -2.500   0.1433   0.01767   0.00882  -0.1108   0.9552   0.0511
  -2.250   0.1812   0.01690   0.00801  -0.1129   0.9505   0.0722
  -2.000   0.2175   0.01609   0.00743  -0.1147   0.9451   0.1321
  -1.750   0.2526   0.01582   0.00728  -0.1163   0.9384   0.2040
  -1.500   0.2896   0.01572   0.00717  -0.1180   0.9326   0.2568
  -1.250   0.3233   0.01560   0.00703  -0.1191   0.9247   0.2889
  -1.000   0.3587   0.01544   0.00683  -0.1204   0.9176   0.3154
  -0.750   0.3940   0.01527   0.00662  -0.1217   0.9097   0.3407
  -0.500   0.4262   0.01510   0.00643  -0.1223   0.9002   0.3640
  -0.250   0.4634   0.01486   0.00620  -0.1239   0.8929   0.3897
   0.000   0.4942   0.01468   0.00604  -0.1242   0.8815   0.4150
   0.250   0.5249   0.01448   0.00589  -0.1244   0.8696   0.4440
   0.500   0.5560   0.01425   0.00575  -0.1247   0.8572   0.4794
   0.750   0.5869   0.01395   0.00561  -0.1250   0.8443   0.5292
   1.000   0.6157   0.01319   0.00548  -0.1247   0.8309   0.7100
   1.500   0.6813   0.01284   0.00513  -0.1257   0.7994   1.0000
   1.750   0.7126   0.01283   0.00502  -0.1259   0.7821   1.0000
   2.000   0.7423   0.01287   0.00499  -0.1258   0.7628   1.0000
   2.250   0.7726   0.01293   0.00499  -0.1258   0.7434   1.0000
   2.500   0.8015   0.01305   0.00503  -0.1256   0.7231   1.0000
   2.750   0.8299   0.01320   0.00511  -0.1254   0.7025   1.0000
   3.000   0.8574   0.01340   0.00525  -0.1249   0.6818   1.0000
   3.250   0.8843   0.01363   0.00548  -0.1244   0.6610   1.0000
   3.500   0.9106   0.01389   0.00570  -0.1238   0.6404   1.0000
   3.750   0.9363   0.01417   0.00596  -0.1231   0.6198   1.0000
   4.000   0.9618   0.01447   0.00625  -0.1223   0.5997   1.0000
   4.250   0.9866   0.01479   0.00658  -0.1215   0.5789   1.0000
   4.500   1.0113   0.01513   0.00699  -0.1207   0.5586   1.0000
   4.750   1.0355   0.01548   0.00740  -0.1197   0.5373   1.0000
   5.000   1.0596   0.01586   0.00781  -0.1188   0.5164   1.0000
   5.250   1.0831   0.01625   0.00828  -0.1177   0.4940   1.0000
   5.500   1.1040   0.01670   0.00869  -0.1162   0.4594   1.0000
   5.750   1.1194   0.01738   0.00909  -0.1137   0.3916   1.0000
   6.000   1.1342   0.01830   0.00961  -0.1114   0.3144   1.0000
   6.250   1.1497   0.01940   0.01035  -0.1094   0.2410   1.0000
   6.500   1.1587   0.02144   0.01155  -0.1069   0.1131   1.0000
   6.750   1.1689   0.02359   0.01319  -0.1044   0.0554   1.0000
   7.000   1.1831   0.02518   0.01477  -0.1022   0.0425   1.0000
   7.250   1.1995   0.02638   0.01612  -0.1004   0.0353   1.0000
   7.500   1.2109   0.02806   0.01797  -0.0979   0.0316   1.0000
   7.750   1.2237   0.02952   0.01964  -0.0955   0.0297   1.0000
   8.000   1.2357   0.03111   0.02141  -0.0930   0.0280   1.0000
   8.250   1.2482   0.03280   0.02324  -0.0907   0.0262   1.0000
   8.500   1.2608   0.03444   0.02495  -0.0887   0.0237   1.0000
   8.750   1.2723   0.03715   0.02766  -0.0868   0.0215   1.0000
   9.000   1.2905   0.03918   0.02993  -0.0853   0.0207   1.0000
   9.250   1.3092   0.04167   0.03270  -0.0839   0.0199   1.0000
   9.500   1.3265   0.04451   0.03585  -0.0825   0.0192   1.0000
   9.750   1.3394   0.04744   0.03920  -0.0806   0.0185   1.0000
  10.000   1.3469   0.05008   0.04217  -0.0783   0.0174   1.0000
  10.250   1.3501   0.05250   0.04486  -0.0757   0.0164   1.0000
  10.500   1.3487   0.05483   0.04743  -0.0727   0.0156   1.0000
  10.750   1.3445   0.05751   0.05035  -0.0698   0.0151   1.0000
  11.000   1.3376   0.06056   0.05365  -0.0672   0.0148   1.0000
  11.250   1.3280   0.06405   0.05742  -0.0649   0.0147   1.0000
  11.500   1.3161   0.06788   0.06151  -0.0631   0.0145   1.0000
  11.750   1.3024   0.07205   0.06595  -0.0620   0.0145   1.0000
  12.000   1.2870   0.07664   0.07081  -0.0617   0.0145   1.0000
  12.250   1.2702   0.08172   0.07615  -0.0624   0.0145   1.0000
  12.500   1.2523   0.08741   0.08208  -0.0640   0.0145   1.0000
  12.750   1.2332   0.09379   0.08870  -0.0667   0.0146   1.0000
  13.000   1.2126   0.10110   0.09625  -0.0707   0.0148   1.0000
  13.250   1.1905   0.10957   0.10494  -0.0760   0.0149   1.0000
  13.500   1.1662   0.11969   0.11526  -0.0828   0.0153   1.0000
  13.750   1.1357   0.13363   0.12937  -0.0927   0.0159   1.0000
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