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.

scholarly journals Features of flow around transport aircraft model with running propellers by modelled engine failure in wind tunnel

2021 ◽  
Vol 2103 (1) ◽  
pp. 012206
Author(s):  
V I Chernousov ◽  
A A Krutov ◽  
E A Pigusov
Keyword(s):  
Wind Tunnel ◽  
Lift Coefficient ◽  
Aerodynamic Characteristics ◽  
Light Transport ◽  
Transport Aircraft ◽  
Engine Failure ◽  
The One ◽  
Low Speed Wind Tunnel ◽  
Control Surfaces ◽  
Landing Mode

Abstract This paper presents the experiment results of modelling the one engine failure at the landing mode on a model of a light transport airplane in the T-102 TsAGI low speed wind tunnel. The effect of starboard and port engines failure on the aerodynamic characteristics and stability of the model is researched. The model maximum lift coefficient is reduced about ≈8% and there are the same moments in roll and yaw for starboard and port engines failure case. It was found that the failure of any engine has little impact on the efficiency of control surfaces. Approaches of compensation of forces and moments arising in the engine failure case were investigated.

scholarly journals Wind Tunnel Tests of the Tu-154M Aircraft Aerodynamic Characteristics

2019 ◽  
Vol 26 (3) ◽  
pp. 113-120
Author(s):  
Andrzej Krzysiak
Keyword(s):  
Wind Tunnel ◽  
Aerodynamic Characteristics ◽  
Full Scale ◽  
Control Surface ◽  
Rolling Moment ◽  
Wind Tunnel Tests ◽  
Aircraft Model ◽  
University Of Technology ◽  
The Military ◽  
Control Surfaces

Abstract Determination of possible manoeuvres to be performed by the aircraft requires knowledge of its aerodynamic characteristics including, in particular, characteristics of the aircraft at configuration with deflected control surfaces. In this article, the wind tunnel tests results of the model of passenger Tu-154M aircraft manufactured at the scale 1:40 are presented. The model was designed and manufactured by the Military University of Technology based on the Tu-154M aircraft geometry obtained by full-scale object scanning. The model mapped all aircraft control surfaces, along with the gaps between these surfaces and the main wing part. During the tests all the model’s control surface like, flaps, ailerons, spoilers, slots, rudder, elevator and tail plane were deflected at the same deflection angles range as they are used in the full scale aircraft. The aerodynamic characteristics of the tested Tu-154M aircraft model were measured by the 6-component internal balance. Based on the obtained measurements the aircraft model aerodynamic coefficients were calculated. In the article the basic aerodynamic characteristics of the tested Tu-154M aircraft model i.e. lift, drag coefficients as well as pitching, yawing and rolling moment coefficients versus model angles of attack and sideslip angles were presented. The tests were performed in the Institute of Aviation low speed wind tunnels T-1 of the 1.5 m diameter test section at the undisturbed velocity, V∞ = 40 m/s.

Experimental Hydro- and Aerodynamics Research on Arrow

2014 ◽  
Vol 1022 ◽  
pp. 113-117
Author(s):  
Xiao An Long
Keyword(s):  
Wind Tunnel ◽  
Longitudinal Direction ◽  
Aerodynamic Characteristics ◽  
Static Stability ◽  
The State ◽  
Water Tunnel ◽  
Theoretical Knowledge ◽  
Pitching Moment ◽  
Considerable Influence ◽  
Attached Flow

This study aims to investigate the hydro- and aerodynamic characteristics of arrows as understood within the field of archery and to contribute to theoretical knowledge, upon which archery techniques are based. The water tunnel and wind tunnel are used to test different arrows consisting of four famous brands.The results showed that when the angles of attack from -6°to 6°, the arrow remained in the state of attached flow. Arrows that had spiral plastic fletches demonstrated better states of flow than arrows with straight fletches. Within the range of the experimental angles of attack, the coefficients of lift increased, while the coefficients of pitching moment decreased when the angle of attack increased. The arrows showed static stability in the longitudinal direction. Arrow fetches also demonstrated considerable influence on the lift and pitching moment. The rolling of the arrows caused the change of the coefficient of lift. Based on the results, it can be concluded that arrow fetches are the major contributors to the arrows’ flight stability.

A Modular Wing-Tail Airplane Configuration for the Educational Wind Tunnel Laboratory

2004 ◽  
Author(s):  
B. Terry Beck
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Calibration Procedure ◽  
Aerodynamic Characteristics ◽  
Wind Tunnels ◽  
Small Scale ◽  
Pitching Moment ◽  
Gravity Effects ◽  
Basic Parameters ◽  
Rapid Prototyping System

An innovative modular airplane configuration has been developed for use in small-scale educational wind tunnels. The “airplane” consists of an interchangeable wing and horizontal tail configuration that mounts on a conventional wind tunnel electronic balance (“sting”) to facilitate measurements of normal force, axial force and longitudinal pitching moment. From these basic parameters, the total lift, total drag, and resultant airplane pitching moment can be deduced, along with the location of the aerodynamic center of the total airplane. Using known wing planform and airfoil shapes facilitates comparison of the total airplane aerodynamic characteristics with those predicted from the known characteristics of the separate wing and horizontal tail. In particular, the aerodynamic center of the simplified airplane configuration can be determined, along with the effect that downwash on the tail has on longitudinal stability of the airplane. Included in the paper is a description of the calibration procedure for the modular “sting” mount. This procedure accounts for an offset “line of action” for aerodynamic forces, as well as offset center of gravity effects. In conjunction with this same test setup, an available Rapid Prototyping system has been used to manufacture the test sections (separate wing and tail) for use in the wind tunnel, and in particular, in the modular wing-tail assembly. This provides tremendous flexibility in the types of wing-tail assemblies that can be investigated experimentally using the same module. The relatively inexpensive prototyping procedure also provides the capability for students to design and test their own configurations. Furthermore, the precision manufacturing capability of the Rapid Prototyping system guarantees reliable reproduction of virtually any desired aerodynamic planform and airfoil shape.

scholarly journals Analysis of the propellers-airframe interaction of the light transport aircraft

2021 ◽  
Vol 24 (5) ◽  
pp. 76-88
Author(s):  
Yu. S. Mikhailov
Keyword(s):  
Wind Tunnel ◽  
Experimental Studies ◽  
Aerodynamic Characteristics ◽  
High Energy ◽  
Light Transport ◽  
Transport Aircraft ◽  
High Energy Level ◽  
Combined Use ◽  
Wind Tunnel Balance ◽  
Propeller Blades

In the design of multi-engine aircraft, one of the important issues is the interaction between the propellers and airframe configuration components, especially in take-off and go-around procedure modes. Modern propeller-driven aircraft concepts in the pulling configuration are characterized by a high disk loading and an increased number of propeller blades used to increase cruising speed and reduce excessive noise. The first problem arising due to high disk loading is the direct impact of forces by operating propellers (thrust, normal force) on fixed-wing stability, especially at angles of attack different from a zero value. The second one involves a high-energy level of the propeller slipstream, having a significant indirect impact on the aircraft’s aerodynamics, stability and controllability. This impact is primarily associated with the interaction of propellers slipstream with other aircraft’s configuration elements. The complexity of taking into account the slipstream-wing interaction and other airframe components stipulated the application of experimental methods to study the problems of propellers – airframe interaction while designing propeller-driven aircraft configurations. This article presents an analysis of the experimental studies results of the operating propellers- airframe interaction for a light twin-engine transport aircraft. The aerodynamic aircraft’s configuration is executed using the conventional pattern of a high-wing and the carrier-on deck type empennage. The high-lift wing device is a fixed-vane doubleslotted flap. The wind-tunnel tests of the model in the cruising, takeoff and landing configurations were carried out in TsAGI lowspeed wind-tunnel T-102. Measurement of forces and moments, acting on the model, was performed by means of an external sixcomponent wind-tunnel balance. Measurement of forces and moments, acting on the propeller, was conducted using strain gauge weighers installed inside the engine nacelles of power plant simulators. The simultaneous combined use of external and internal balances allowed researchers to determine the direct and indirect contribution of operating propellers to the model longitudinal aerodynamic characteristics under variation of loading factor B ranging from 0 to 2.

scholarly journals PENELITIAN DAN PENGUJIAN KARAKTERISTIK AERODINAMIKA BOM LATIH PERCOBAAN BLP-500 DAN BLP 25

2010 ◽  
Vol 2 (1) ◽  
Author(s):  
Agus Aribowo ◽  
Sulistyo Atmadi ◽  
Yus Kadarusman Markis
Keyword(s):  
Wind Tunnel ◽  
Analytical Calculation ◽  
Aerodynamic Characteristics ◽  
Static Stability ◽  
Supersonic Wind Tunnel ◽  
Centre Of Gravity ◽  
The Stability

Research and aerodynamic testing of BLP-500 and BLP-25 have been conducted in both subsonic and supersonic wind tunnel. Aerodynamic characteristics such as Cl, Cd, and Cm for these types of bomb we obtained. By knowing the aerodynamic characteristics, the stability and trajectory of the bomb can be determined. Both analytical calculation and real tests in the wind tunnel were performed and compared. The results showed that for its static stability, the location of the centre of gravity of BLP-500 and BLP-25 to be less than 115.1 cm and 31.9 cm respectively.

scholarly journals Konsistensi dan Akurasi Data Hasil Pengukuran pada Pengujian Aerodinamika Model Pesawat Jenis Penumpang Sipil (AirLiner) di Wind Tunnel BBTA3-BPPT

2019 ◽  
Vol 2 (1) ◽  
Author(s):  
Novan Risnawan ◽  
F. Andree Yohanes ◽  
Sunarno Sunarno ◽  
Alief Sadlie Kasman
Keyword(s):  
Wind Tunnel ◽  
Design Process ◽  
National Laboratory ◽  
Aircraft Design ◽  
Aerodynamic Characteristics ◽  
Data Consistency ◽  
Aircraft Model ◽  
Measurement Results ◽  
Passenger Aircraft ◽  
Test Result

AbstractAerodynamic testing of an aircraft model in wind tunnel is important step in an aircraft design process. National Laboratory of Aerodynamic, Aeroelastic and Aeroacoustics Technology (BBTA3) have conducted a testing of a type of civilian passenger aircraft model to obtain aerodynamic characteristics data in ILST wind tunnel. The test result will be used in design process to predict performance and stability, so that the data must be consistent and accurate. This paper discusses the process of data consistency and accuracy checking by performing short repeatability and long repeatability testing so that the measurement results can be regarded valid and can be used to represent the validity of whole measurement data.Keywords: Consistency of test result data, wind tunnel, aerodynamics.Abstraks Pengujian aerodinamik sebuah model pesawat di terowongan angin merupakan tahap penting dalam proses desain pesawat. Balai Besar Teknologi Aerodinamika, Aeroelastika dan Aeroakustika (BBTA3) telah melakukan pengujian sebuah model pesawat bertipe penumpang sipil (airliner) untuk mendapatkan data karakteristik aerodinamika di terowongan angin ILST. Data hasil pengujian ini akan digunakan di dalam proses disain untuk memprediksi kinerja dan kestabilan pesawat sehingga data tersebut harus konsisten dan akurat. Tulisan ini mendiskusikan proses pengecekan konsistensi dan akurasi data dengan melakukan pengujian keberulangan dekat dan pengujian keberulangan jauh sehingga hasil pengukuran dapat dinyatakan valid dan dapat digunakan untuk mewakili keabsahan seluruh data pengukuran.Kata Kunci : Konsistensi data hasil pengujian, wind tunnel, aerodinamika.

A novel unmanned aircraft with solid-state control surfaces: Analysis and flight demonstration

2012 ◽  
Vol 24 (2) ◽  
pp. 147-167 ◽  
Author(s):  
Onur Bilgen ◽  
Lauren M Butt ◽  
Steven R Day ◽  
Craig A Sossi ◽  
Joseph P Weaver ◽  
...  
Keyword(s):  
Solid State ◽  
Wind Tunnel ◽  
Fiber Composite ◽  
Aerodynamic Characteristics ◽  
Unmanned Aircraft ◽  
Ocean Engineering ◽  
Remotely Piloted Aircraft ◽  
Macro Fiber Composite ◽  
Wing Morphing ◽  
Control Surfaces

This article presents a completely servo-less, piezoelectric controlled, wind tunnel and flight tested, remotely piloted aircraft that has been developed by the 2010 Virginia Tech Wing Morphing Design Team (a senior design project between the Departments of Mechanical Engineering and Aerospace and Ocean Engineering). A type of piezocomposite actuator, the Macro-Fiber Composite, is used for changing the camber of all control surfaces on the aircraft. The aircraft is analyzed theoretically for its aerodynamic characteristics to aid the design of the piezoelectric control surfaces. A vortex lattice analysis complemented the database of aerodynamic derivatives used to analyze control response. Steady-state roll rates were measured in a wind tunnel and were compared to a similar aircraft with servomotor actuated control surfaces. The theoretical analysis and wind tunnel testing demonstrated the stability and control authority of the concept, culminating in the first flight of the completely Macro-Fiber Composite controlled aircraft on 29 April 2010. An electric motor-driven propulsion system is used to generate thrust, and all systems are powered with a single lithium polymer battery. This vehicle became the first completely Macro-Fiber Composite controlled, flight tested aircraft. It is also known to be the first fully solid-state piezoelectric material controlled, nontethered, flight tested fixed-wing aircraft.

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