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GIII BL430 AIRFOIL (giiim-il)

GIII BL430 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils


Airfoil giiim-il
Details Dat file Parser  
(giiim-il) GIII BL430 AIRFOIL
Grumman/Gulfstream GIII transonic airfoils
Max thickness 8.5% at 35.2% chord.
Max camber 1.9% at 25.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 GIII BL430 AIRFOIL
       26.       26.

 0.0000000 0.0000000
 0.0053735 0.0147236
 0.0079492 0.0177082
 0.0130616 0.0221385
 0.0257497 0.0295566
 0.0509820 0.0387164
 0.0761319 0.0446283
 0.1012409 0.0489313
 0.1513870 0.0546990
 0.2014682 0.0579085
 0.2515170 0.0598387
 0.3015331 0.0604798
 0.3515171 0.0598617
 0.4014594 0.0575947
 0.4513819 0.0545481
 0.5012920 0.0510119
 0.5511947 0.0471859
 0.6010885 0.0430101
 0.6509704 0.0383646
 0.7008411 0.0332794
 0.7506967 0.0275946
 0.8005497 0.0218099
 0.8504050 0.0161150
 0.9002677 0.0107101
 0.9501339 0.0054450
 1.0000000 0.0001799

 0.0000000 0.0000000
 0.0047219 -.0109597
 0.0071747 -.0128220
 0.0121144 -.0151973
 0.0245622 -.0172531
 0.0495698 -.0169475
 0.0745739 -.0167819
 0.0995661 -.0170859
 0.1495291 -.0185335
 0.1994752 -.0206506
 0.2494261 -.0225779
 0.2993871 -.0241054
 0.3493595 -.0251832
 0.3993426 -.0258413
 0.4493376 -.0260296
 0.4993473 -.0256384
 0.5493692 -.0247675
 0.5994055 -.0233269
 0.6494540 -.0214066
 0.6995108 -.0191566
 0.7495892 -.0160571
 0.7996695 -.0128877
 0.8497498 -.0097082
 0.8998303 -.0065288
 0.9499107 -.0033493
 0.9999909 -.0001799
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Lednicer format dat file
Selig format dat file

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Polars for GIII BL430 AIRFOIL (giiim-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   giiim-il50,000929.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiim-il50,000531.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   giiim-il100,000943.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiim-il100,000541.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   giiim-il200,000956.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   giiim-il200,000552.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   giiim-il500,000970.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiim-il500,000570.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   giiim-il1,000,000985.9 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiim-il1,000,000585.7 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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