Teaching aircraft flight performance in aeronautical engineering using PC-based flight simulation

1998 ◽  
Author(s):  
James Baughn ◽  
Jason Wolf
Keyword(s):  
Flight Simulation ◽  
Flight Performance ◽  
Aircraft Flight ◽  
Aeronautical Engineering

scholarly journals Application of the Rapid Update Cycle (RUC) to Aircraft Flight Simulation

2008 ◽  
Author(s):  
Yan Zhang ◽  
Seamus McGovern
Keyword(s):  
Computer Simulation ◽  
Theoretical Model ◽  
Wind Speed ◽  
Simulation Model ◽  
Flight Simulation ◽  
Simulation Tool ◽  
Flight Performance ◽  
Aircraft Flight ◽  
True Airspeed ◽  
Environmental Prediction

An aircraft flight simulation model under development aims to provide a computer simulation tool to investigate aircraft flight performance during en route flight and landing under various atmospherical conditions [1]. Within this model, the air pressure and temperature serve as important parameters for deriving the true airspeed (TAS). Also important are the wind speed and direction, which will be direct inputs for the flight simulation model. In this paper, the Rapid Update Cycle (RUC) data, provided hourly by the National Centers for Environmental Prediction (NCEP) and the National Oceanic and Atmospheric Administration (NOAA) are used to derive the atmospherical parameters. We relate the pressure to the geodetic altitude by using the geopotential height from the RUC data and the theoretical model. Then the resultant pressure as a function of the geodetic altitude is used to retrieve other parameters such as the temperature and wind velocity by multi-dimensional interpolation. Airplane flights simulated by the X-Plane® simulator with the input of the RUC data are demonstrated.

scholarly journals Variable cant angle winglets for improvement of aircraft flight performance

Meccanica ◽  
2020 ◽  
Vol 55 (10) ◽  
pp. 1917-1947
Author(s):  
J. E. Guerrero ◽  
M. Sanguineti ◽  
K. Wittkowski
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Drag Reduction ◽  
Fuel Efficiency ◽  
Aerodynamic Performance ◽  
Flight Performance ◽  
Sweep Angle ◽  
Aircraft Flight ◽  
Induced Drag ◽  
Aircraft Performance

Abstract Traditional winglets are designed as fixed devices attached at the tips of the wings. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving aircraft performance and fuel efficiency. However, because winglets are fixed surfaces, they cannot be used to control lift-induced drag reductions or to obtain the largest lift-induced drag reductions at different flight conditions (take-off, climb, cruise, loitering, descent, approach, landing, and so on). In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different flight phases. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle on the performance of a benchmark wing at Mach numbers of 0.3 and 0.8395. The results obtained demonstrate that by adjusting the cant angle, the aerodynamic performance can be improved at different flight conditions.

The effects of changing passenger weight on aircraft flight performance

2019 ◽  
Vol 13 ◽  
pp. 41-62 ◽  
Author(s):  
Damien J. Melis ◽  
Jose M. Silva ◽  
Miguel A. Silvestre ◽  
Richard Yeun
Keyword(s):  
Flight Performance ◽  
Aircraft Flight

Fundamental and Practical Aspects of Crack Growth under Corrosion Fatigue Conditions

1977 ◽  
Vol 191 (1) ◽  
pp. 107-114 ◽  
Author(s):  
J. Schijve
Keyword(s):  
Crack Growth ◽  
Aluminium Alloys ◽  
Relevant Information ◽  
Flight Simulation ◽  
Shear Mode ◽  
Load Spectrum ◽  
Aircraft Flight ◽  
Cracking Modes ◽  
Crack Growth Mechanism ◽  
High Level

The crack growth mechanism is dependent on environment, frequency and temperature as shown by some examples. Two cracking modes are observed in aluminium alloys: the tensile mode and the shear mode. Examples show that inert environments promote the shear mode whereas aggressive environments promote the tensile mode. Information from constant-amplitude tests need not be applicable to service loading conditions as illustrated by an example. Significant environmental effects on crack growths are observed in aircraft flight-simulation tests. Growth delays induced by severe flights occur in all environments. As a consequence the truncation of the load spectrum at the high level end is a difficult question. The problem of producing relevant information in the laboratory is discussed.

scholarly journals Variable Cant Angle Winglets for Improvement of Aircraft Flight Performance

2019 ◽  
Author(s):  
Joel Guerrero ◽  
Kevin Wittkowski ◽  
Marco Sanguineti
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Drag Reduction ◽  
Fuel Efficiency ◽  
Aerodynamic Performance ◽  
Flight Performance ◽  
Sweep Angle ◽  
Aircraft Flight ◽  
Induced Drag ◽  
Aircraft Performance

Traditional winglets are designed as fixed devices attached at the tips of the wings. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving aircraft performance and fuel efficiency. However, because winglets are fixed surfaces, they cannot be used to control lift-induced drag reductions or to obtain the largest lift-induced drag reductions at different flight conditions (take-off, climb, cruise, loitering, descent, approach, landing, and so on). In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different flight phases. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle on the performance of a benchmark wing at Mach numbers of 0.3 and 0.8395. The results obtained demonstrate that by adjusting the cant angle, the aerodynamic performance can be improved at different flight conditions.

scholarly journals Research on Dynamic Modeling and Transition Flight Strategy of VTOL UAV

2019 ◽  
Vol 9 (22) ◽  
pp. 4937
Author(s):  
Chunyang Wang ◽  
Zhou Zhou ◽  
Rui Wang
Keyword(s):  
Flight Simulation ◽  
Flight Performance ◽  
Research Focus ◽  
Transition Mode ◽  
Flight Mode ◽  
Horizontal Flight ◽  
Vtol Uav ◽  
Aerial Vehicle ◽  
Control Quantity ◽  
Transition Flight

A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) can meet both VTOL and horizontal flight performance, but how to achieve a safe and stable transition is a research focus of this type of aircraft. According to the overall configuration characteristics of VTOL UAV, aerodynamic models of lift fan, lift duct and induced wing surface of VTOL UAV were established. Three flight modes of induced VTOL UAV are studied, including hover, transition and horizontal flight. The method of longitudinal flight balance of UAV in transition mode is also studied. Finally, a UAV is taken as an example to conduct the research of transition flight mode balancing and flight simulation with the method presented in this paper. The results show that the proposed method can reasonably give the control quantity and longitudinal attitude of UAV in the whole transition mode, so that the UAV can achieve a steady transition flight.

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