CEAS Aeronautical Journal

, Volume 3, Issue 2, pp 145–164

Multidisciplinary conceptual design for aircraft with circulation control high-lift systems

Authors

    • Institute of Aircraft Design and Lightweight StructuresTechnische Universitaet Braunschweig
  • Wolfgang Heinze
    • Institute of Aircraft Design and Lightweight StructuresTechnische Universitaet Braunschweig
  • Peter Horst
    • Institute of Aircraft Design and Lightweight StructuresTechnische Universitaet Braunschweig
  • Rolf Radespiel
    • Institute of Fluid MechanicsTechnische Universitaet Braunschweig
Original Paper

DOI: 10.1007/s13272-012-0049-5

Cite this article as:
Werner-Spatz, C., Heinze, W., Horst, P. et al. CEAS Aeronaut J (2012) 3: 145. doi:10.1007/s13272-012-0049-5

Abstract

Active high-lift technologies have often proven their potential in aerodynamic analyses and wind tunnel tests, but have so far played only a minute role in civil production aircraft. This is expected to change in the future only if such technologies can be accounted for early in the aircraft design process. In this paper, the adaptation of a conceptual design process is presented, enabling it to consider circulation control as a high-lift technology. It is shown that the main aerodynamic effects of a blown flap in the boundary layer control regime can be satisfactorily modeled with a potential theory method. Some sample results of the design process indicate a potential for significant reductions of required field length in comparison with today’s aircraft, creating the potential to increase the capacity of the air transportation system, without increasing overall aircraft mass or direct operating cost.

Keywords

Aircraft conceptual design Active high-lift Circulation control Multisiciplinary design High-lift aerodynamics

List of symbols

A

Cross-section area of BLC exit slot, in m²

A

Speed of sound, in m/s

B

Width, in m

C D0

3D zero-lift drag coefficient

C Di

3D induced drag coefficient

c dF

2D drag coefficient with flap extended

c dF0

2D drag coefficient without flap extension

C L

3D lift coefficient

c l

2D lift coefficient

C M

3D pitching moment coefficient

\( C_{{{\upmu}}} \)

3D blowing momentum coefficient

\( c_{{{\upmu}}} \)

2D blowing momentum coefficient

c p

Pressure coefficient

F F

Wing reference area, in m²

i

Counter over wing sections

j

Index denoting parameters of the BLC jet

L/D

Relation of lift to drag

\( \dot{m} \)

Mass flow, in kg/s

Ma

Mach number

p

Static pressure, in Pa

\( p_{\text{T}} \)

Total pressure, in Pa

q

Dynamic pressure, in Pa

T

Static temperature, in K

T T

Total temperature, in K

t n

Chord length normal to the wing leading edge, in m

V

Velocity, in m/s

\( \alpha \)

Angle of attack, in degrees

\( \gamma \)

Dimensionless circulation

\( \varphi_{ 2 5} \)

Wing sweep angle at quarter-chord, in degrees

\( \eta \)

Dimensionless span coordinate

\( \kappa \)

Ideal gas coefficient

\( \Uplambda \)

Wing aspect ratio

\( \rho \)

Density, in kg/m³

Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2012