Aerodynamic Characteristics and Store Loads of a 1/24-Scale F-111 Aircraft Model with Three External Store Loadings

1981 ◽  
Author(s):  
C. F. Anderson
Keyword(s):  
Aerodynamic Characteristics ◽  
Aircraft Model

NUMERICAL AND EXPERIMENTAL INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF THE HYPERSONIC AIRCRAFT MODEL OF INTEGRATED CONFIGURATION

2013 ◽  
Vol 44 (1) ◽  
pp. 111-127
Author(s):  
Sergey Mikhailovich Zadonsky ◽  
Alexander Petrovich Kosykh ◽  
Garry Grantovich Nersesov ◽  
Iraida Fedorovna Chelysheva ◽  
Sergey Valer'evich Chernov ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Aerodynamic Characteristics ◽  
Aircraft Model ◽  
Hypersonic Aircraft

scholarly journals Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests

10.14311/530 ◽  
2004 ◽  
Vol 44 (2) ◽  
Author(s):  
A. V. Petrov ◽  
Y. G. Stepanov ◽  
M. V. Shmakov
Keyword(s):  
Wind Tunnel ◽  
Aerodynamic Characteristics ◽  
Static Stability ◽  
Light Transport ◽  
Experimental Investigations ◽  
Small Scale ◽  
Left Hand ◽  
Aircraft Model ◽  
Turboprop Engine ◽  
Control Surfaces

This report presents the results of experimental investigations into the interaction between the propellers (Ps) and the airframe of a twin-engine, twin-boom light transport aircraft with a Π-shaped tail. An analysis was performed of the forces and moments acting on the aircraft with rotating Ps. The main features of the methodology for windtunnel testing of an aircraft model with running Ps in TsAGI’s T-102 wind tunnel are outlined.The effect of 6-blade Ps slipstreams on the longitudinal and lateral aerodynamic characteristics as well as the effectiveness of the control surfaces was studied on the aircraft model in cruise and takeoff/landing configurations. The tests were conducted at flow velocities of V∞ = 20 to 50 m/s in the ranges of angles of attack α =  -6 to 20 deg, sideslip angles of β = -16 to 16 deg and blade loading coefficient of B 0 to 2.8. For the aircraft of unusual layout studied, an increase in blowing intensity is shown to result in decreasing longitudinal static stability and significant asymmetry of the directional stability characteristics associated with the interaction between the Ps slipstreams of the same (left-hand) rotation and the empennage.

Aircraft model for automatic taxi directional control system design

2019 ◽  
Vol 91 (3) ◽  
pp. 477-483
Author(s):  
Mariusz Krawczyk ◽  
Cezary Jerzy Szczepanski ◽  
Albert Zajdel
Keyword(s):  
Control System ◽  
Full Range ◽  
Aerodynamic Characteristics ◽  
Slip Angle ◽  
Control Law ◽  
Control Laws ◽  
Content Type ◽  
Critical Speeds ◽  
Aircraft Model ◽  
Directional Control

Purpose This paper aims to present a concept of an automatic directional control system of remotely piloted aerial system (RPAS) during the taxiing phase. In particular, it shows the initial stages of the control laws synthesis – mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload. Design/methodology/approach The adapted methodology follows the model-based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis. The computer simulations are carried out to analyse the model behaviour. Findings Chosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. Simulations allowed to compute the critical speeds for different taxiway conditions in a 90° turn. Practical implications The results can be used for the taxi directional control law synthesis and simulation of the control system. The computed critical speeds can be treated as safety limits. Originality/value The taxi directional control system has not been introduced to the RPAS yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle has a big value in the process of design and implementation of the future auto taxi systems. Moreover, computed speed safety limits can be used by designers and standard creators.

Aircraft model for the automatic taxi directional control design

2019 ◽  
Vol 91 (2) ◽  
pp. 289-295
Author(s):  
Mariusz Krawczyk ◽  
Cezary Jerzy Szczepanski ◽  
Albert Zajdel
Keyword(s):  
Control System ◽  
Full Range ◽  
Aerodynamic Characteristics ◽  
Slip Angle ◽  
Control Law ◽  
Control Laws ◽  
Content Type ◽  
Critical Speeds ◽  
Aircraft Model ◽  
Directional Control

PurposeThis paper aims to present a concept of an automatic directional control system of remotely piloted aerial system (RPAS) during the taxiing phase. In particular, it shows the initial stages of the control laws synthesis-mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload.Design/methodology/approachThe adapted methodology follows the model-based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis. The computer simulations are carried out to analyse the model behaviour.FindingsChosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxiing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. Simulations allowed to compute the critical speeds for different taxiway conditions in a 90° turn.Practical implicationsThe results can be used for the taxi directional control law synthesis and simulation of the control system. The computed critical speeds can be treated as a safety limits.Originality/valueThe taxi directional control system has not been introduced to the RPAS yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle has a big value in the process of design and implementation of the future auto taxi systems. Moreover, computed speed safety limits can be used by designers and standards creators.

Prediction of aerodynamic characteristics of an aircraft model with and without winglet using fuzzy logic technique

2011 ◽  
Vol 15 (8) ◽  
pp. 595-605 ◽  
Author(s):  
Altab Hossain ◽  
Ataur Rahman ◽  
Jakir Hossen ◽  
A.K.M.P. Iqbal ◽  
M.I. Zahirul
Keyword(s):  
Fuzzy Logic ◽  
Aerodynamic Characteristics ◽  
Aircraft Model ◽  
Fuzzy Logic Technique

scholarly journals Design of a Three Surfaces R/C Aircraft Model

10.14311/314 ◽  
2002 ◽  
Vol 42 (1) ◽  
Author(s):  
D. P. Coiro ◽  
F. Nicolosi
Keyword(s):  
Cost Model ◽  
Low Cost ◽  
Aerodynamic Characteristics ◽  
Flight Behavior ◽  
Material Structure ◽  
Aircraft Model ◽  
Lifting Surfaces ◽  
And Performance ◽  
Under Construction ◽  
High Angles Of Attack

Design of a three lifting surfaces radio-controlled model has been carried out at Dipartimento di Progettazione Aeronautica (DPA) by the authors in the last year. The model is intended to be a UAV prototype and is now under construction. The main goal of this small aircraft's design is to check the influence of the canard surface on the aircraft's aerodynamic characteristics and flight behavior, especially at high angles of attack. The aircraft model is also intended to be a flying platform to test sensors, measurement and acquisition systems for research purposes and a valid and low-cost teaching instrument for flight dynamics and flight maneuvering. The aircraft has been designed to fly with and without canard, and all problems relative to aircraft balance and stability have been carefully analyzed and solved. The innovative configuration and the mixed wooden-composite material structure has been obtained with very simple shapes and all the design is focused on realizing a low-cost model. A complete aerodynamic analysis of the configuration up to high angles of attack and a preliminary aircraft stability and performance prediction will be presented.

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