Thin Airfoil in Fields of Nonuniform Density, Part 1: Single Density Interface

AIAA Journal ◽  
2003 ◽  
Vol 41 (11) ◽  
pp. 2085-2094 ◽  
Author(s):  
Frank E. Marble
Keyword(s):  
Density Interface ◽  
Thin Airfoil

Active Feedback Controller Design for a Thin Airfoil

1993 ◽  
Author(s):  
Hitay Ozbay ◽  
Glen R. Bachmann
Keyword(s):  
Controller Design ◽  
Feedback Controller ◽  
Thin Airfoil ◽  
Active Feedback

Method of calculating flow around extremely thin airfoil with slotted leading-edge slat and flap

2019 ◽  
Author(s):  
Vladimir A. Frolov
Keyword(s):  
Leading Edge ◽  
Thin Airfoil

Forces on Unstaggered Airfoil Cascades in Unsteady In-Phase Motion

1976 ◽  
Vol 98 (3) ◽  
pp. 521-530 ◽  
Author(s):  
N. H. Kemp ◽  
H. Ohashi
Keyword(s):  
Flow Velocity ◽  
Incompressible Flow ◽  
Kutta Condition ◽  
Harmonic Motion ◽  
Thin Airfoil ◽  
Through Flow ◽  
Flow Through ◽  
Unsteady Effects ◽  
Analytical Expressions ◽  
Phase Motion

Incompressible flow through an unstaggered cascade in general, unsteady, in-phase motion is considered. By methods of thin-airfoil theory, using the assumptions of wakes trailing back at the through-flow velocity, and the Kutta condition, exact analytical expressions are derived for loading, lift and moment. As application, harmonic motion is considered for plunging, pitching, and sinusoidal gusts. Numerical values of lift and moment for these three cases are given graphically (tables are available from the authors). The results show strong analogies with isolated unsteady thin-airfoil theory. They should prove useful as simple examples of unsteady effects in cascades, and as check cases for other approximate or purely numerical analyses.

Asymptotic Behavior of Internal Rossby Waves with a Sharp Density Interface

2005 ◽  
Vol 65 (5) ◽  
pp. 1772-1793
Author(s):  
A. Ouahsine ◽  
P. A. Bois
Keyword(s):  
Asymptotic Behavior ◽  
Rossby Waves ◽  
Density Interface

A Physically Consistent Reduced Order Model for Plasma Aeroelastic Control on Compressor Blades

2018 ◽  
Author(s):  
Valentina Motta ◽  
Leonie Malzacher ◽  
Dieter Peitsch ◽  
Giuseppe Quaranta
Keyword(s):  
Suction Side ◽  
Reduced Order Model ◽  
Plasma Actuators ◽  
Pitching Moment ◽  
Compressor Cascade ◽  
Order Model ◽  
Compressor Blades ◽  
Reduced Order ◽  
Thin Airfoil ◽  
Pressure Suction

Plasma actuators may be successfully employed as virtual control surfaces, located at the trailing edge of blades, both on the pressure and on the suction side, to control the aeroelastic response of a compressor cascade. Actuators generate an induced flow against the direction of the freestream. As a result, actuating on the pressure side yields an increase in lift and nose down pitching moment, whereas the opposite is obtained by operating on the suction side. A properly phased alternate pressure/suction side actuation allows to reduce vibration and to delay the flutter onset. This paper presents the development of a linear frequency domain reduced order model for lift and pitching moment of the plasma-equipped cascade. Specifically, an equivalent thin airfoil model is used as a physically consistent basis for the model. Modifications in the geometry of the thin airfoil are generated to account for the effective chord and camber changes induced by the plasma actuators, as well as for the effects of the neighboring blades. The model reproduces and predicts correctly the mean and the unsteady loads, along with the aerodynamic damping on the plasma equipped cascade. The relationship between the parameters of the reduced order model with the flow physics is highlighted.

Errata: Remarks on Thin Airfoil Theory

1977 ◽  
Vol 14 (12) ◽  
pp. 1248-1248
Author(s):  
Rajendra K. Bera
Keyword(s):  
Thin Airfoil
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