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GIII BL387 AIRFOIL (giiil-il)

GIII BL387 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils


Airfoil giiil-il
Details Dat file Parser  
(giiil-il) GIII BL387 AIRFOIL
Grumman/Gulfstream GIII transonic airfoils
Max thickness 8.5% at 35.1% chord.
Max camber 1.6% at 25.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 GIII BL387 AIRFOIL
       26.       26.

 0.0000000 0.0000000
 0.0051498 0.0128399
 0.0076795 0.0153803
 0.0127260 0.0193714
 0.0253048 0.0261246
 0.0504035 0.0345817
 0.0754698 0.0402692
 0.1005201 0.0445868
 0.1505914 0.0507025
 0.2006359 0.0545285
 0.2506622 0.0567947
 0.3006741 0.0578110
 0.3506721 0.0576575
 0.4006541 0.0561242
 0.4506267 0.0537811
 0.5005946 0.0510379
 0.5505570 0.0478249
 0.6005128 0.0440419
 0.6504613 0.0396490
 0.7004023 0.0345962
 0.7503398 0.0292535
 0.8002745 0.0236607
 0.8502072 0.0179180
 0.9001382 0.0120053
 0.9500691 0.0060927
 1.0000000 0.0001800

 0.0000000 0.0000000
 0.0048901 -.0094170
 0.0073708 -.0110660
 0.0123469 -.0131141
 0.0248226 -.0151996
 0.0498050 -.0167012
 0.0747899 -.0179928
 0.0997756 -.0192143
 0.1497507 -.0213375
 0.1997268 -.0233708
 0.2497056 -.0251840
 0.2996878 -.0266973
 0.3496750 -.0277907
 0.3996681 -.0283641
 0.4496670 -.0284576
 0.4996719 -.0280311
 0.5496835 -.0270248
 0.5997018 -.0254485
 0.6497278 -.0232123
 0.6997600 -.0204462
 0.7497980 -.0171801
 0.7998375 -.0137841
 0.8498771 -.0103781
 0.8999166 -.0069820
 0.9499561 -.0035860
 0.9999958 -.0001800
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Lednicer format dat file
Selig format dat file

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Polars for GIII BL387 AIRFOIL (giiil-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   giiil-il50,000931.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiil-il50,000531.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   giiil-il100,000945 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiil-il100,000542.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   giiil-il200,000957.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   giiil-il200,000551.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   giiil-il500,000972.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiil-il500,000567.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   giiil-il1,000,000982 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   giiil-il1,000,000582.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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