Finite‐State Induced‐Flow Model for Rotors in Hover and Forward Flight

1989 ◽  
Vol 34 (4) ◽  
pp. 5-17 ◽  
Author(s):  
David A. Peters ◽  
David Doug Boyd ◽  
Cheng Jian He
2000 ◽  
Vol 45 (4) ◽  
pp. 318-320 ◽  
Author(s):  
Chengjian He ◽  
C. S. Lee ◽  
Weibin Chen

1995 ◽  
Vol 32 (2) ◽  
pp. 323-333 ◽  
Author(s):  
David A. Peters ◽  
Cheng Jian He

1995 ◽  
Vol 32 (2) ◽  
pp. 313-322 ◽  
Author(s):  
David A. Peters ◽  
Swaminathan Karunamoorthy ◽  
Wen-Ming Cao

Author(s):  
Jianzhe Huang

Abstract Unmamned rotorcraft requires automatic control system to adjust transient flight behaviors properly, and real-time computation of aerodynamic forces is also in demand. Finite-state inflow model is one of the most efficient models which can fulfill such a requirement. When a rotorcraft is flying close to ground, a strong downwash impinges on the ground surface and reflected airstream influences the flow field of the main rotor. Such a physical phenomenon makes the aerodynamic computations complex, and previous studies have solved such a problem by simulation ground effect with a ground rotor. But it still requires numerical integration to compute the flow field of main rotor downstream, and the computational efficiency degrades evidently. In this paper, adjoint theorem is proposed to calculate induced velocity in the rotor wake with closed form equations. The hover and forward flight conditions will be examined for different moment of inertia of blade and forward flight speeds.


2015 ◽  
Vol 3 (2/3) ◽  
pp. 72-92 ◽  
Author(s):  
Waqas Khan ◽  
Meyer Nahon

Purpose – The purpose of this paper is to develop a physics-based model for UAV propellers that is capable of predicting all aerodynamic forces and moments in any general forward flight condition such as no flow, pure axial flow and pure side flow etc. Design/methodology/approach – The methodology adopted in this paper is the widely used Blade Element Momentum Theory (BEMT) for propeller model development. The difficulty arising from the variation of induced flow with blade’s angular position is overcome by supplementing the BEMT with the inflow model developed by Pitt and Peters. More so, high angle of attack aerodynamics is embedded in the simulation as it is likely for the blades to stall in general forward flight, for example during extreme aerobatics/maneuvers. Findings – The validity of the model is demonstrated via comparison with experiments as well as with other existing models. It is found that one of the secondary forces is negligible while the other is one order of magnitude less than the primary static thrust, and as such may be neglected depending on the level of accuracy required. On the other hand, both secondary moments must be considered as they are of similar order of magnitude as the primary static torque. Research limitations/implications – The paper does not consider the swirl component of the induced flow under the assumption that it is negligible compared to the axial component. Originality/value – This paper fulfills the identified need of a propeller model for general forward flight conditions, and aims to fill this void in the existing literature pertaining to UAVs.


2017 ◽  
Vol 19 (5) ◽  
pp. 766-783 ◽  
Author(s):  
Khalid Al-Asadi ◽  
Jennifer G. Duan

A Delft3D-FLOW model was used to simulate tidal flow in Davis pond marsh in Louisiana, USA. The study area is a freshwater marsh consisting of one main channel and floodplain. Vegetation-induced flow resistance greatly influences tidal flow dynamics in the marsh. This study evaluated eight approaches to estimate vegetation roughness, including two constant Manning's n values, four empirical relations for calculating n, and two methods for calculating Chezy's C values originally embedded in the Delft3D model. Simulated results of water surface elevation (WSE) were compared with the corresponding field observation at eleven stream gauges in the study area. We concluded that the roughness coefficient for vegetated area varies with time as flow depth changes. Among the selected empirical relations for the vegetation roughness, the ones accounting for the effect of the vegetation frontal area and the degree of submergence have closely matched the measurements.


Neurosurgery ◽  
1991 ◽  
Vol 28 (2) ◽  
pp. 251-259 ◽  
Author(s):  
Eng H. Lo ◽  
Jacob I. Fabrikant ◽  
Richard P. Levy ◽  
Mark H. Phillips ◽  
Kenneth A. Frankel ◽  
...  

Abstract Stereotactic radiosurgery has proven to be an effective method of treating selected inaccessible or inoperable arteriovenous malformations (AVMs) of the brain. Radiation-induced obliteration of successfully-treated AVMs, however, occurs only after some latent period after treatment, depending on size, location, and dose. An experimental compartmental flow model is proposed to describe the hemodynamic alterations in the AVM as a result of the pathophysiological changes after radiosurgery, and to analyze temporal alterations in AVM blood flow rates and pressure gradients before complete obliteration. In representative small (low-flow, 150 ml/min) and large (high-flow, 440 ml/min) AVMs, it is found that increases in pressure gradients across certain vascular structures within the AVM occur during the normal course of radiation-induced flow decrease and AVM obliteration. The magnitude of these pressure alterations, however, may be within the normal physiological variations in cerebrovascular blood pressure. The effects of partial-volume irradiation of the AVM is examined by limiting radiosurgical treatment to varying portions of the flow compartments within the model. It is found that alterations in pressure gradients persist in unirradiated vascular shunts, even after complete obliteration of the treated AVM volume. These pressure alterations may increase the probability of hemorrhage from the untreated shunts of the AVM and cause redistribution of regional cerebral blood flow resulting in increased flow through these untreated shunts.


2021 ◽  
Vol 22 (2) ◽  
pp. 307-324
Author(s):  
L. G. A. Ferreira ◽  
C. C. Pagani Júnior ◽  
E. M. Gennaro ◽  
C. De Marqui Junior

A Helicopter rotor undergoes unsteady aerodynamic loads ruled by the aeroelastic coupling between the elastic blades and the dynamic wake induced by rotary wings. Modeling the dynamic interaction between the structural and aerodynamic fields is a key point to understand aeroelastic phenomena associated with rotor stability, flow induced vibration and noise generation, among others. In this study, we address the Generalized Dynamic Wake Model, which describes the inflow velocity field at the rotor disk as a superposition  of a finite number of induced flow states. It is a mature model that has been validated based on experimental data and numerically investigated from an eigenvalue problem formulation, whose eigenvalues and eigenvectors provide a deeper insight on the dynamic wake behavior. The paper extends the results presented in the literature to date in order to support physical interpretation of inflow states drawn from the finite-state wake model for flight conditions varying from hover to edgewise flight. The discussion of the wake model mathematical formulation is also oriented towards practical engineering applications to fill a gap in the literature.


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