Ram Air Turbine (RAT) is used as an emergency power source to feed vital apparatuses required for aircrafts in case of main systems failure. The purpose of this paper is to explain the function of RAT as a wind harvesting technology for aircraft and its advantages as auxiliary power generator during landing process. This survey allows a more axiomatic understanding on the use of different RAT approaches in aircraft construction. The survey in this paper also provides a sight to simultaneously use RAT for emergency case and power harvesting as future energy.

The present paper aims to study the possibility of dispensing an auxiliary power unit (APU) in an aircraft powered by fossil fuels to reduce air pollution. It particularly seeks to evaluate the amount of power generated by the ram air turbine (RAT) using the novel counter-rotating technique while characterizing its optimum axial distance. The ram air turbine (RAT), which is already equipped in aircrafts, was enhanced to generate the amount of energy produced by the APU. The approach was implemented by a CRRAT system. Six airfoil profiles were tested based on 2D models and the best airfoil was chosen for implantation on the RAT and CRRAT systems. The performance of the conventional single-rotor RAT and CRRAT were analyzed using FLUENT software based on 3D models. The adopted numerical scheme was the Navier–Stokes equation with k–ω SST turbulence modeling. The dynamic mesh and user-defined function (UDF) were used to revolve the rotor turbine via wind. The results indicated that the FX63-137 airfoil profile showed a higher performance in terms of the lift-to-drag ratio compared to the other airfoils. The optimum axial distance between the two rotors was 0.087 m of the rotor diameter and the efficiency of the new CRRAT increased to almost 45% compared to the single-rotor RAT.

Comparison of six airfoils; FX 63-137, FX76-100, S835, S809, NACA63415, and NACA63215, have been performed using commercial software, FLUENT and XFOIL, in order to choose the best maximum lift to drag ratio in the region of 4×10^∧6 Reynolds number, and also to specify their aerodynamic coefficients in Blade Element Momentum theory (BEM). These airfoils are candidates for the use as blade turbines and another application of flying object operating at high Reynolds number. In this study, the two-dimensional model of airfoils was established through Gambit software. The range of angles of attack is from -150 to 150. Comparisons of the numerical results generally show good agreements. Numerical results of FX 63-137 were also validated with experimental data. A good agreement of lift and drag coefficient from numerical simulations of FLUENT and experimental data was obtained at 10^∧6 Reynolds number.

Aerial crop spraying, also known as crop dusting, is made for aerial application of pesticides or fertilizer. An agricultural aircraft which is converted from an aircraft has been built to combine with the aerial crop spraying for the purpose. In recent years, many studies on the aerial crop spraying were conducted because aerial application is the most economical, large and rapid treatment for the crops. The main objective of this research is to study the airflow of aerial crop spraying system using Computational Fluid Dynamics. This paper is focus on the effect of aircraft speed and nozzle orientation on the distribution of spray droplet at a certain height. Successful and accurate of CFD simulation will improve the quality of spray during the real situation and reduce the spray drift. The spray characteristics and efficiency are determined from the calculated results of CFD. Turbulence Model (k-ɛ Model) is used for the airflow in the fluid domain to achieve a more accurate simulation. Furthermore, spray simulation is done by setting the Flat-fan Atomizer Model of Discrete Phase Model (DPM) at the nozzle exit. The interaction of spray from each flat-fan atomizer can also be observed from the simulation. The evaluation of this study is validation and grid dependency study using field data from industry.

In an operation, belly landing is mostly applied as recovery method especially on research Unmanned Aerial Vehicle (UAV) such as Aludra SR-10. This type of landing method may encounter tough landing on hard soil and gravel which create high impact load on the aircraft. The impact may cause structural or system damage which costly to be repaired. Nowadays, Parachute Recovery System (PRS) recently used in numerous different tasks such as landing purpose to replace belly landing technique. Parachute use in this system to slow down flying or falling UAV to a safe landing by opening the canopy to increase aerodynamic drag. This paper was described the Computational Fluid Dynamic (CFD) analysis on ALUDRA SR-10 model with two different conditions i.e. the UAV equipped with and without parachute in order to identify the changes of aerodynamic characteristics. This simulation studies using solid models of aircraft and hemisphere parachute and was carried out by using ANSYS 16.0 Fluent under steady and turbulent flow and was modelled using the k-epsilon (k-ε) turbulence model. This simulation was limited to determine the drag force and drag coefficient. The obtained result showed that implementation of parachute increase 0.25 drag coefficient of the aircraft that is from 0.93 to 1.18. Subsequent to the reduction of descent rate caused by the parachute, the drag force of the aircraft increase by 0.76N. These increasing of drag force of the aircraft will produce lower terminal velocity which is expected to reduce the impact force on the aircraft during landing.

The present study considered the performance analysis of a new proposed design of a vehicle's wind turbine energy installation system. A test is conducted on the energy conversion and storage system that have been built to evaluate its performance and the capability. The result shows that the power that is generated by the system is directly proportional to the speed of the alternator. The time taken for charging a battery is also recorded and it is found that it takes about 2 to 3 hours to fill the 12-volt battery depending on the size and capacity of the battery used. The power generated for the system is 20.4 watt and 120.5 watt at 60 km/h and 120 km/h respectively. From the analysis that has been done, the energy from a turbine has the potential to generate power to car system. The wind energy is possible to integrate with other existing and renewable energy.