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GIII BL145 AIRFOIL (giiif-il)

GIII BL145 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils


Airfoil giiif-il
Details Dat file Parser  
(giiif-il) GIII BL145 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 BL145 AIRFOIL
       26.       26.

 0.0000000 0.0000000
 0.0048526 0.0075152
 0.0073191 0.0092235
 0.0122653 0.0119605
 0.0246656 0.0170438
 0.0495235 0.0242813
 0.0744150 0.0298096
 0.0993257 0.0343582
 0.1491857 0.0414861
 0.1990887 0.0464250
 0.2490245 0.0496845
 0.2989856 0.0516644
 0.3489653 0.0526848
 0.3989596 0.0529654
 0.4489671 0.0525763
 0.4989971 0.0510377
 0.5490518 0.0482395
 0.5991248 0.0445117
 0.6492096 0.0401741
 0.6993100 0.0350469
 0.7494216 0.0293499
 0.7995359 0.0235129
 0.8496499 0.0176859
 0.8997643 0.0118489
 0.9498786 0.0060119
 0.9999928 0.0001849

 0.0000000 0.0000000
 0.0051084 -.0055298
 0.0076330 -.0067803
 0.0126708 -.0087114
 0.0252342 -.0119450
 0.0503016 -.0153833
 0.0753366 -.0171722
 0.1003620 -.0184713
 0.1504026 -.0205498
 0.2004382 -.0223783
 0.2504712 -.0240669
 0.3005026 -.0256755
 0.3505339 -.0272841
 0.4005647 -.0288628
 0.4505886 -.0300916
 0.5005924 -.0302907
 0.5505788 -.0296103
 0.6005480 -.0280501
 0.6505019 -.0257103
 0.7004419 -.0226607
 0.7503710 -.0190513
 0.8002968 -.0152821
 0.8502225 -.0115028
 0.9001484 -.0077335
 0.9500741 -.0039542
 1.0000000 -.0001849
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Lednicer format dat file
Selig format dat file

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Polars for GIII BL145 AIRFOIL (giiif-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   giiif-il50,000932.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiif-il50,000532.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   giiif-il100,000946.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiif-il100,000544.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   giiif-il200,000961.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   giiif-il200,000555.9 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   giiif-il500,000978.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   giiif-il500,000562.3 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   giiif-il1,000,000983.9 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   giiif-il1,000,000572.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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