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Fluid Dynamics of High Angle of Attack pp 313–338Cite as

Some Challenges in High-Alpha Vehicle Dynamics

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Summary

The evolution of aerospace vehicles towards ever-increasing maneuverability and agility, including flight at high angles of attack and vehicle motions of large amplitudes and high angular rates, has led to the need for prediction of vehicle aerodynamics that are dominated by unsteady separated flow effects. The existing data base is reviewed to determine to what degree the following critical issues are understood. 1. Cause and effect of asymmetric forebody flow separation with associated vortices. 2. Effect of asymmetry and breakdown of leading edge vortices, 3. Effect of vehicle motion on dynamic airfoil stall. The challenge is to extend the present knowledge to include the coupling existing between novel aerodynamic controls and the vehicle dynamics of agile aircraft operating at high angles of attack

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Abbreviations

b:

wing span

c:

reference length, wing chord or diameter (d) for circular cylinder and body alone

d:

cylinder diameter

f:

frequency

k:

dimensionless roll rate, k = ωb/2U∞,

1:

sectional lift, coefficient cl = l /q∞c

ℓ:

rolling moment: coefficient Cℓ = ℓ /q∞S b

mp :

sectional pitching moment, coefficient cm = mp/q∞c2

M:

free stream Mach number

n:

yawing moment, coefficient Cn = n/q∞ Sb

p:

roll rate

P:

static pressure, coefficient Cp = (p-p∞)/q∞

q:

dynamic pressure, q∞ = p∞U∞ 2/2

Re:

Reynolds number, Re = U∞c/v∞

S:

reference area, = πd2/4 for body alone, = projected wing area for aircraft

t:

time

UW :

wall velocity

U∞ :

freestream velocity

x:

axial distance from leading edge or body apex

Y:

side force, coefficient CY = Y/q∞S

z:

translatory coordinate

α:

angle of attack

ā:

effective angular amplitude

β:

angle of sideslip

Δ:

increment or amplitude

θ:

purturbation in pitch

θA :

apex half angle

θLE :

complimentary angle to the leading edge sweep, θLE = n/2-A

Λ:

leading edge sweep angle

ξ:

dimensionless x-coordinate, ξ= x/c

ρ:

air density

σ:

inclination of roll axis

φ:

roll angle

φ:

dimensionless roll rate, φ= φb/2U∞

ψ:

coning angle

v:

kinematic viscosity

ω, ϖ:

angular frequency, ω = 2nf, ϖ = ωC/U∞

A:

apex

CG:

enter of gravity or rotation center

LE:

leading edge

LIM:

limit cycle

s:

separation

v:

vortex

w:

wake

W:

wall

o:

initial or time-average value

∞:

freestream condition

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Author information

Authors and Affiliations

  1. Lockheed Missiles & Space Company, Inc., Sunnyvale, California, USA

    L. E. Ericsson (Engineering Consultant)

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  1. L. E. Ericsson
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Editor information

Editors and Affiliations

  1. Dept. of Aeronautics Faculty of Engineering, The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku Tokyo 113, Japan

    R. Kawamura  & Y. Aihara  & 

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© 1993 Springer-Verlag Berlin Heidelberg

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Ericsson, L.E. (1993). Some Challenges in High-Alpha Vehicle Dynamics. In: Kawamura, R., Aihara, Y. (eds) Fluid Dynamics of High Angle of Attack. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-52460-8_22

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  • DOI: https://doi.org/10.1007/978-3-642-52460-8_22

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-52462-2

  • Online ISBN: 978-3-642-52460-8

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