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GIII BL167 AIRFOIL (giiig-il)

GIII BL167 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils


Airfoil giiig-il
Details Dat file Parser  
(giiig-il) GIII BL167 AIRFOIL
Grumman/Gulfstream GIII transonic airfoils
Max thickness 8.3% at 44.9% chord.
Max camber 1.3% at 29.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 GIII BL167 AIRFOIL
       26.       26.

 0.0000000 0.0000000
 0.0048583 0.0078081
 0.0073261 0.0095829
 0.0122759 0.0123526
 0.0246821 0.0175177
 0.0495500 0.0247988
 0.0744499 0.0303104
 0.0993675 0.0348524
 0.1492390 0.0419271
 0.1991500 0.0468224
 0.2490917 0.0500284
 0.2990564 0.0519647
 0.3490389 0.0529214
 0.3990350 0.0531283
 0.4490439 0.0526255
 0.4990721 0.0510630
 0.5491217 0.0483209
 0.5991893 0.0445892
 0.6492678 0.0402476
 0.6993600 0.0351563
 0.7494626 0.0294952
 0.7995687 0.0236341
 0.8496749 0.0177731
 0.8997810 0.0119120
 0.9498872 0.0060510
 0.9999934 0.0001799

 0.0000000 0.0000000
 0.0051039 -.0057274
 0.0076266 -.0069816
 0.0126614 -.0089003
 0.0252176 -.0120025
 0.0502757 -.0152079
 0.0753106 -.0171338
 0.1003364 -.0185598
 0.1503765 -.0207821
 0.2004109 -.0226845
 0.2504421 -.0244169
 0.3004716 -.0260493
 0.3505007 -.0276618
 0.4005289 -.0292243
 0.4505478 -.0302769
 0.5005489 -.0303499
 0.5505353 -.0296032
 0.6005060 -.0279967
 0.6504631 -.0256405
 0.7004082 -.0226245
 0.7503421 -.0189887
 0.8002736 -.0152229
 0.8502053 -.0114672
 0.9001368 -.0077014
 0.9500684 -.0039357
 1.0000000 -.0001799
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Lednicer format dat file
Selig format dat file

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Polars for GIII BL167 AIRFOIL (giiig-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   giiig-il50,000931.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiig-il50,000532.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   giiig-il100,000946.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   giiig-il100,000544.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   giiig-il200,000965.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiig-il200,000556.1 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   giiig-il500,000978.8 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   giiig-il500,000562.1 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   giiig-il1,000,000983 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   giiig-il1,000,000573 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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