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GIII BL86 AIRFOIL (modified line 31) (giiid-il)

GIII BL86 AIRFOIL (modified line 31) - Grumman/Gulfstream GIII transonic airfoils


Airfoil giiid-il
Details Dat file Parser  
(giiid-il) GIII BL86 AIRFOIL (modified line 31)
Grumman/Gulfstream GIII transonic airfoils
Max thickness 9.7% at 39.8% chord.
Max camber 1% at 29.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 GIII BL86 AIRFOIL (modified line 31)
       26.       26.

 0.0000000 0.0000000
 0.0046998 0.0080942
 0.0071260 0.0100842
 0.0120046 0.0133551
 0.0242719 0.0196300
 0.0489348 0.0287146
 0.0736829 0.0355023
 0.0984902 0.0406923
 0.1482250 0.0478366
 0.1980593 0.0522947
 0.2479536 0.0551350
 0.2978883 0.0568869
 0.3478537 0.0578098
 0.3978577 0.0576943
 0.4479094 0.0562904
 0.4980022 0.0537782
 0.5481265 0.0504171
 0.5982786 0.0463070
 0.6484618 0.0413581
 0.6986743 0.0356203
 0.7489152 0.0291135
 0.7991684 0.0222772
 0.8494031 0.0159402
 0.8996048 0.0104920
 0.9497957 0.0053334
 0.9999863 0.0001847

 0.0000004 -.0000100
 0.0052638 -.0071147
 0.0078230 -.0087098
 0.0129157 -.0112109
 0.0255821 -.0157012
 0.0507987 -.0215460
 0.0759405 -.0253736
 0.1010415 -.0281027
 0.1511795 -.0318333
 0.2012727 -.0343555
 0.2513407 -.0361987
 0.3013917 -.0375826
 0.3514312 -.0386568
 0.4014618 -.0394914
 0.4514846 -.0401163
 0.5014730 -.0398125
 0.5514255 -.0385400
 0.6013495 -.0364986
 0.6512482 -.0337781
 0.7011248 -.0304584
 0.7509772 -.0264896
 0.8008045 -.0218418
 0.8506171 -.0167945
 0.9004206 -.0115076
 0.9502156 -.0059910
 1.0000000 -.0001847
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Lednicer format dat file
Selig format dat file

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Polars for GIII BL86 AIRFOIL (modified line 31) (giiid-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   giiid-il50,000931 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   giiid-il100,000945.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   giiid-il200,000959.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   giiid-il500,000970.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   giiid-il1,000,000975.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
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