Aerodynamic characteristics, database development and flight simulation of the X-34 vehicle

Aerodynamic Characteristics, Database Development, and Flight Simulation of the X-34 Vehicle

Journal of Spacecraft and Rockets ◽

10.2514/2.3706 ◽

2001 ◽

Vol 38 (3) ◽

pp. 334-344 ◽

Cited By ~ 13

Author(s):

Bandu N. Pamadi ◽

Gregory J. Brauckmann ◽

Michael J. Ruth ◽

Henri D. Fuhrmann

Keyword(s):

Aerodynamic Characteristics ◽

Flight Simulation ◽

Database Development

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Helicopter Flight Simulation based on URANS Solver and Virtual Blade Model

Journal of KONES ◽

10.2478/kones-2019-0075 ◽

2019 ◽

Vol 26 (3) ◽

pp. 211-217

Author(s):

Wieńczysław Stalewski ◽

Katarzyna Surmacz

Keyword(s):

Computational Models ◽

Steep Descent ◽

Aerodynamic Characteristics ◽

Flight Simulation ◽

Ansys Fluent ◽

Local Flow ◽

Rotating Blades ◽

Blade Element Theory ◽

Helicopter Flight ◽

Blade Model

Abstract The methodology of simulation of a rotorcraft flight has been developed and applied to simulate several stages of flight of light helicopter. The methodology is based on coupling of several computational models of Computational Fluid Dynamics, Flight Dynamic. The essence of the methodology consists in calculation of aerodynamic forces acting on the flying rotorcraft by solving during the simulation the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. In this approach, the rotorcraft is flying inside the computational 3D mesh modelling the space filled with the air. The flight simulation procedure is completely embedded in the URANS solver ANSYS FLUENT. Flow effects caused by rotating blades of main or tail rotor are modelled by application of the developed Virtual Blade Model (VBM). In this approach, real rotors are replaced by volume discs influencing the flow field similarly as rotating blades. Time-averaged aerodynamic effects of rotating blades are modelled using momentum source terms placed inside the volume-disc zones. The momentum sources are evaluated based on the Blade Element Theory, which associates local flow parameters in the blade sections with databases of 2D-aerodynamic characteristics of these sections. Apart of the VBM module, two additional UDF modules support the simulation of helicopter flight: the module responsible for modelling of all kinematic aspects of the flight and the module gathering the momentary aerodynamic loads and solves 6 DOF-Equations describing a motion of the helicopter seen as solid body. Exemplary simulation of helicopter flight, starting from a hover, through an acceleration and fast flight until a deceleration and steep descent, has been discussed.

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Initial Development Of OC-Based Flight Dynamics Engineering Simulator

Jurnal Teknologi ◽

10.11113/jt.v28.1030 ◽

1998 ◽

pp. 67-72

Author(s):

Shuhaimi Mansor ◽

Amir Fadhil Yaacob

Keyword(s):

Cost Reduction ◽

Aircraft Design ◽

Aerodynamic Characteristics ◽

Database System ◽

Flight Simulation ◽

Pilot Training ◽

Initial Development ◽

Aerodynamic Database ◽

Aircraft Motion ◽

And Training

Flight simulation had played a very important role in aerospace and aviation industries as an engineering tool and training equipment. Computers provided the capability of stimulating an aircraft in flight without actually flying the aircraft, thus providing safety to pilots and also cost reduction in pilot training and aircraft design. Aerodynamic characteristics were modelled mathematically to display the air craft orientation and the aircraft motion during manoeuvres. Implementation of aerodynamic database system enables a flight simulator to stmulate many types of aircraft manoeuvres.

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An investigation of lateral-directional departure behavior based on yawing–rolling coupled wind tunnel tests

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410017723361 ◽

2017 ◽

Vol 232 (16) ◽

pp. 2989-3000

Author(s):

Lin Shen ◽

Da Huang ◽

Genxing Wu

Keyword(s):

Wind Tunnel ◽

Aerodynamic Characteristics ◽

Flight Simulation ◽

Wind Tunnel Tests ◽

Unsteady Aerodynamic ◽

Model Based ◽

Aerodynamic Model ◽

Data Prediction ◽

Text Model ◽

Departure Behavior

The traditional aerodynamic model based on the dynamic derivative tests and the [Formula: see text] model based on the yawing–rolling coupled motion tests are compared with respect to aerodynamic data, prediction of lateral-directional departure, and flight simulation. The study shows that the traditional model cannot fully reveal the unsteady aerodynamic characteristics and predict completely the departure behavior due to yaw–roll coupling. On the other hand, the [Formula: see text] model can reveal the departure behavior of an aircraft at some specific coupling ratios when the angle of attack reaches a critical value or more, using the aerodynamic data obtained from the yawing–rolling coupled wind tunnel tests. The comparison of flight simulation results shows that the lateral-directional departure is closely related to the coupling ratios, and for the investigated aircraft, the departure is mainly caused by the unsteady yawing and rolling moments at the coupling ratios showing unstable features.

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