scholarly journals Unsteady Aerodynamic Interaction between Two Bodies at Hypersonic Speed

2010 ◽  
Vol 53 (180) ◽  
pp. 114-121 ◽  
Author(s):  
Hiroshi OZAWA ◽  
Keiichi KITAMURA ◽  
Katsuhisa HANAI ◽  
Koichi MORI ◽  
Yoshiaki NAKAMURA
Keyword(s):  
Hypersonic Speed ◽  
Unsteady Aerodynamic ◽  
Aerodynamic Interaction ◽  
Two Bodies

Aerodynamic interaction of two bodies in a supersonic flow

2004 ◽  
Vol 49 (5) ◽  
pp. 315-317 ◽  
Author(s):  
I. A. Zhdan ◽  
V. P. Stulov ◽  
P. V. Stulov
Keyword(s):  
Supersonic Flow ◽  
Aerodynamic Interaction ◽  
Two Bodies

scholarly journals Unsteady loads for coaxial rotors in forward flight computed using a vortex particle method

2018 ◽  
Vol 122 (1251) ◽  
pp. 693-714 ◽  
Author(s):  
J. Tan ◽  
Y. Sun ◽  
G. N. Barakos
Keyword(s):  
Flow Model ◽  
Particle Method ◽  
Reversed Flow ◽  
Aerodynamic Loads ◽  
Unsteady Aerodynamic ◽  
Vortex Particle Method ◽  
Coaxial Rotor ◽  
Aerodynamic Interaction ◽  
Coaxial Rotors ◽  
Vortex Particle

ABSTRACTRecent advances in coaxial rotor design have shown benefits of this configuration. Nevertheless, issues related to rotor-head drag, aerodynamic performance, wake interference, and vibration should also be considered. Simulating the unsteady aerodynamic loads for a coaxial rotor, including the aerodynamic interactions between rotors and rotor blades, is an essential part of analysing their vibration characteristics. In this article, an unsteady aerodynamic analysis based on a vortex particle method is presented. In this method, a reversed-flow model for the retreating side of the coaxial rotor is proposed based on an unsteady panel technique. To account for reversed flow, shedding a vortex from the leading edge is used rather than from the trailing edge. Moreover, vortex-blade aerodynamic interactions are accounted for. The model considers the unsteady pressure term induced on a blade by tip vortices of other blades, and thus accounts for the aerodynamic interaction between the rotors and its contribution to the unsteady airloads. Coupling the reversed-flow model and the vortex-blade aerodynamic interaction model with the viscous vortex-particle method is used to simulate the complex wake of the coaxial rotor. The unsteady aerodynamic loads on the X2 coaxial rotor are simulated in forward flight, and compared with the results of PRASADUM (Parallelized Rotorcraft Analysis for Simulation And Design, developed at the University of Maryland) and CFD/CSD computations with the OVERFLOW and the CREATE-AV Helios tools. The results of the present method agree with the results of the CFD/CSD method, and compare to it better than the PRASADUM solutions. Furthermore, the influence of the aerodynamic interaction between the coaxial rotors on the unsteady airloads, frequency, wake structure, induced flow, and force distributions are analysed. Additionally, the results are also compared against computations for a single-rotor case, simulated at similar conditions as the coaxial rotor. It is shown that the effect of tip vortex interaction plays a significant role in unsteady airloads of coaxial rotors at low speeds, while the rotor blade passing effect is obviously strengthened at high-speed.

Aerodynamic Interaction between Two Bodies during Opposite Passing Maneuver

2018 ◽  
Vol 2018.67 (0) ◽  
pp. 325
Author(s):  
Soichiro YAJIMA ◽  
Haziq Ikhwan ZAWAWI ◽  
Ryozo ISHIWATA ◽  
Naoto HAGINO
Keyword(s):  
Aerodynamic Interaction ◽  
Two Bodies

Unsteady Aerodynamic Interactions in a Multistage Compressor

1987 ◽  
Vol 109 (3) ◽  
pp. 420-428 ◽  
Author(s):  
V. R. Capece ◽  
S. Fleeter
Keyword(s):  
Axial Flow ◽  
Unsteady Aerodynamic ◽  
Geometric Conditions ◽  
Forcing Function ◽  
Reduced Frequency ◽  
Aerodynamic Interaction ◽  
Blade Row ◽  
Unsteady Interaction ◽  
Multistage Compressor ◽  
Series Of Experiments

The fundamental flow physics of multistage blade row interactions is experimentally investigated, with unique data obtained which quantify the unsteady harmonic aerodynamic interaction phenomena. In particular, a series of experiments is performed in a three-stage axial flow research compressor over a range of operating and geometric conditions at high reduced frequency values. The multistage unsteady interaction effects of the following on each of the three vane rows are investigated: (1) the steady vane aerodynamic loading, (2) the waveform of the aerodynamic forcing function to each vane row, including both the chordwise and traverse gust components.

Experimental Investigation of Multistage Interaction Gust Aerodynamics

1989 ◽  
Vol 111 (4) ◽  
pp. 409-417 ◽  
Author(s):  
V. R. Capece ◽  
S. Fleeter
Keyword(s):  
Axial Flow ◽  
Unsteady Aerodynamics ◽  
Unique Data ◽  
Aerodynamic Loading ◽  
Unsteady Aerodynamic ◽  
Forcing Function ◽  
Reduced Frequency ◽  
Aerodynamic Interaction ◽  
Blade Row ◽  
Potential Interactions

The fundamental flow physics of multistage blade row interactions are experimentally investigated at realistic reduced frequency values. Unique data are obtained that describe the fundamental unsteady aerodynamic interaction phenomena on the stator vanes of a three-stage axial flow research compressor. In these experiments, the effect on vane row unsteady aerodynamics of the following are investigated and quantified: (1) steady vane aerodynamic loading; (2) aerodynamic forcing function waveform, including both the chordwise and transverse gust components; (3) solidity; (4) potential interactions; and (5) isolated airfoil steady flow separation.

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