Abrupt Wing Stall

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Abrupt Wing Stall. W.H. Mason Kevin Waclawicz, Michael Henry Virginia Tech 540-231-6740, whmason@vt.edu 11 July 2002. Aerodynamics of Abrupt Wing Stall General Description. Normal Shock. We tackled two different tasks: - a 2-D model problem

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### Abrupt Wing Stall

W.H. Mason

Kevin Waclawicz, Michael Henry

Virginia Tech

540-231-6740, whmason@vt.edu

11 July 2002

Aerodynamics of Abrupt Wing Stall

General Description

Normal Shock

- a 2-D model problem

- detailed examination of NAVAIR computed porous door solutions

The goal: to discover physical basis for abrupt wing stall phenomena

We obtained improved understanding of an extremely complex flowfield

Crossflow

Pattern?

Oblique

Shock

6 deg

• Investigation of “F/A18-E/F like” foil (NACA 65A series, 5.7%)
• Comparison with “F/A18-C/D-like” airfoil (NACA 65A series, 3.5%)
• Post-processing of porous door configuration CFD files.
• Comparison of the porous door and baseline configuration

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Approach : 2-D Model Problem

Question: Can a 2-D calculation show the sudden forward movement in the shock observed in 3-D?

• Use FLOMG from NASA Langley to compute flowfields

- both Johnson-King and Baldwin Lomax Turbulence models used

• Compare E/F and C/D airfoils at critical span station

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Shock Movement with increasing lift

• 2D movement is aft, essentially attaches to hinge line

• E/F and C/D are similar, but E/F happens “sooner” because it’s thicker

• 2D shows no hint of forward shock movement, trends the same for each turbulence model

2D airfoil

3D wing

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Classify off-the-surface and crossflow velocity singular points as well as examine mathematical predictions made in singular point mathematics using CFD.Approach: Computational Flo Viz
• Navy provided CFD Solutions
• 6, 7, 8 & 10 degree AOA grid and solution files
• Wind-Up-Turn
• Mach 0.80, 15K feet
• File sizes, each solution is:
• ~6 million grid points into 46 zones
• Grid: 117 MB
• Solution: 195 MB
• Tecplot files are an additional 1.2 GB for each solution

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7 deg AOA, M = 0.8

Survey all aspects of flowfieldEmphasize cross-flow topology

Location of Crossflow Stations

Topology nomenclature

Nodal Point

Focus

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Significant Accomplishments

Two MS Theses provide details of the two tasks:

Kevin Waclawicz, July 2001, MS, “The Investigation of Crossflow Velocity and Off-the-Surface Streamtrace Topology for a Moderately Swept Wing at Transonic Mach Numbers,”

Michael Henry, August 2001, MS, “Two-Dimensional Shock Sensitivity Analysis for Transonic Airfoils with Leading-Edge and Trailing-Edge Device Deflections, ”

These theses and final presentations are available on the web, after being held for one year

http://www.aoe.vt.edu/aoe/faculty/Mason_f/MRthesis.html

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Cross Flow Velocity TracesM = 0.8, AOA = 10o, Wind-Up-Turn, Altitude 15k feet

Chine and snag locations dominate crossflow topology,

No sudden breaks occur with examination of all the CFD solutions provided

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Off-the-Surface Velocity TracesM = 0.8, AOA = 10o, Wind-Up-Turn, Altitude 15k feet

Approximately on the surface

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Off-the-Surface Velocity TracesM = 0.8, AOA = 10o, Wind-Up-Turn, Altitude 15k feet

Approximately 0.25 feet off the surface

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Off-the-Surface Velocity TracesM = 0.8, AOA = 10o, Wind-Up-Turn, Altitude 15k feet

Approximately 0.5 feet off the surface

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Off-the-Surface Velocity TracesM = 0.8, AOA = 10o, Wind-Up-Turn, Altitude 15k feet

Approximately 0.75 feet off the surface

Note that spiral moves aft and behind the surface as you move further above the wing

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Two-dimensional shock moves in the opposite direction as that of the Three-dimensional wing

Separation phenomenon which pushes the shock forward on the 3-D wing is not present on the 2-D airfoil

Without 3-D effects the separation bubble is confined to the region aft of the hinge line at low AOA’s

The NACA 65A005.7 airfoil does not exhibit any tendency to abrupt shock movement, forward or rearward

In the 2-D case a deflected trailing edge minimizes the adverse effect of the separation region on the inviscid flow, thus preventing the shock from being pushed forward

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Verified that a line of separation in the crossflow is an indication that separation may be present on the surface of the wing

Flow topology for this wing is more sensitive to shock location as opposed to angle of attack

Increasing the angle of attack increases the area of separation and distance in which it occurs off the wing

Verified that a line of separation present in the off-the-surface planes is an indication of separation

Showed that the lines of separation may also indicate the location of the separated region