Influence of the air propeller on aerodynamic characteristics of the inflatable wing
Journal Title: Механіка гіроскопічних систем - Year 2018, Vol 0, Issue 36
Abstract
The aerodynamic characteristics of the inflatable wing depending on the position and number B of the air propeller and the arrangement of the aircraft wing and horizontal tail, depending on the height of the horizontal tail location relative to the wing are considered in the paper. The simulation is performed by the computational aerodynamics methods (panel-vortex method) of the calculated models flow of the inflatable (combined) wing with different positions and number B of the air propeller. The aerodynamic characteristics are obtained and the analysis of the bearing properties changes and the static longitudinal stability criteria are carried out. An estimation of static longitudinal stability during the installation of a horizontal tail at different heights relative to the wing is made. The bearing properties of the layout for different values of Хгв and Yго practically are not changed. When the location of the screw Хгв changes, the lifting factor increases by 2-3% for every 0,25 basses of the screw from the front edge of the wing. The pitch momentum factor also varies by 2-3%, since it directly depends on the lift factor. The general nature of the change mz(cya, В) depending on the angle of attack of the wing is practically the same for different positions and values of B. The derivative mzCya at small angles of attack acquires a positive value, that is a violation of the condition of static longitudinal stability and such a wing is unstable on the pitch. In the simulation of the wings from the horizontal tail, the derivative mzCya is negative at all the angles of the attack, so this layout is statically stable. The most suitable it is the placement of a plumbing over a wing at the height of Yго= bсах or more, since in this case a balancing speed decreases only by 1.32 times. The location of the horizontal tail in the wing plane is acceptable, but not desirable, as it increases the balancing factor of the lifting force by 2.8 times, which means that it will reduce the balancing velocity by 1.7 times. The disadvantage of such layout is that during a flight with large values of the number B in the event of a sudden propeller failure such an aircraft can stall.
Authors and Affiliations
B. А. Gevko, D. М. Zinchenko
Keywords
Related Articles
- EP ID EP510675
- DOI -
- Views 64
- Downloads 0
3D-models design concept of complex technical objects using knowledge-based technology
<p>3D-models design of complex technical objects (CTO) is performed using information technology (IT). Such technology includes continuous acquisition and life cycle support (CALS) being tools set for its creation. 3D-mo...
Analysis of influence design parameters ejector pipe at the detonation specifications engine
The engines that use a detonation cycle have greater thermal efficiency than engines with constant-pressure combustion cycle. The mechanisms of ejector augmentation are evident in secondary air entrainment. The impulse c...
Влияние температурно-деформационных параметров ТМКО на изменение структуры аустенита и механических свойств микролегированных сталей
В процессе ТМКО микролегированных сталей в широком диапазоне варьировали параметры чистовой прокатки и охлаждения, изменяя степени горячего обжатия при моделировании плоской горячей деформации на стане. Оценивая кривые т...
Adaptive winglet
Winglet are intended to improve the efficiency of fixed-wing aircraft by reducing inductive drag. Such devices increase the effective aspect ratio of a wing without materially increasing the wingspan. Winglets provide fu...
Aerodynamic design of adaptive airplane wing of hybrid construction
This article seeks to design a light aircraft wing of short take-off and landing, which deforms during the flight. The authors first conduct an analysis of the impact of deformation on the wing’s aerodynamic characterist...