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1998/1999 Trap Wing Data Archive

Model Description

The model is a large chord, semi-span, three element configuration, mountedon a body pod. The objective was to create a "simple" 3-element high-liftconfiguration from which to gather experimental data to provide to theCFD community for the development/validation of high-lift CFD codes. The wing is untwisted and has no dihedral. The choice of large chord (MAC=39.6")and relatively low aspect ratio (AR=4.56) were driven by the high unitReynolds numbers and the need for boundary layer thicknesses that couldbe measured with pneumatic instrumentation. The table below summarizesmodel geometry.Two flap configurations were developed for the Trap Wingmodel.  One flap, referred to as the "fullspan flap", is a single-slottedflap, sealed to the side of body, that extends from wing root to wing tip. The other flap, referred to as the "partspan flap", has a span equal toroughly 1/2 of the span of the model, and is centered about the midspanof the wing. Both flap configurations were tested with a slat that is sealedto the side of body and extends from wing root to wing tip.

Summary of Model Geometry

Model semi-span, b/2 (in)
85.1
MAC (in)
39.6
Model reference area Sref/2,(ft2)
22.028
Aspect Ratio AR
4.56
Leading Edge Sweep, Lle(deg)
33.9
Quarter -Chord Sweep, Lc/4(deg)
30
Taper Ratio
0.4
Flap Chord Ratio
0.3
Wing Root t/c (side of body)
 0.121
Wing Tip t/c
0.10
Slat Chord (normal to l.e., in)
5.0
Body pod length (in)
118.72
Body Pod Width (in)
27.961
Body Pod Height (in)
5.95
Slat Bracket Location (2y/b)
 0.13, 0.33, 0.47,
0.64, 0.77, 0.94
Flap Bracket Location (2y/b)
0.13, 0.37, 
0.61, 0.80

The model, originally designed and tested in the late 1980’s as a simpleswept wing, was highly modified for the NASA AST/IWD program. The wingspar and body pod were retained from the original model, the slat was retainedfrom more recent testing of the same model, and all other components ofthe main element and flap were new.

The leading edge is constant chord, full-span slat, sealing to the side-of-bodyat all deflections. Six brackets attached the slat to the wing. The trailingflap is single-slotted, with constant flap chord ratio (cf/c=0.3)across the span. The flap was tested as both a full-span and part-spanconfiguration. For the full-span testing, the flap was sealed to the side-of-body.The part-span flap covers 0.26 < h < 0.75.Sectional cuts through the positioned geometry for the full-span flapslanding configuration are shown below.

Cuts through baseline full-span landing flaps configuration at h =0.17,0.50, and 0.85.

Photos of the Trap Wing model installedin the Ames 12' PWT:

 Fullspan flap configuration



 

Partspan flap configuration


Traverser hardware mounted to partspan flap configuration:


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Page Curator and NASA Official Responsible for Content
Judith A. Hannon  

Last Updated
August 5, 2011

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