Suchergebnisse

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 ...

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. ; В данной статье выполнено моделирование методами вычислительной аэродинамики (панельно-выхревой метод) обтекания расчетных моделей надувного (комбинированного) крыла с разными положениями и числом В воздушного винта. Получены аэродинамические характеристики, осуществлен анализ изменения несущих свойства и критериев статичной продольной устойчивости. Проведена оценка статичной продольной устойчивости при установлении горизонтального оперения на разной высоте относительно крыла. ; Виконано моделювання методами обчислювальної аеродинаміки (панельно-вихровий метод) обтікання розрахункових моделей надувного (комбінованого) крила з різними положеннями та числом В повітряного гвинта. Отримані аеродинамічні характеристики, здійснено аналіз зміни несучих властивостей та критеріїв статичної поздовжньої стійкості. Проведено оцінку статичної поздовжньої стійкості при встановленні горизонтального оперення на різній висоті відносно крила.

A review of the literature shows that emergency ground conditions for aircraft occur with sufficient frequency to require emergency escape devices. The nature of these emergencies allows for a reasonable possibility of escape if care is taken in selection and design of escape provisions. For normal low-wing aircraft, the inflatable escape slide provides for reliable support during descent. Extensive experimental data are given for design of overwing emergency exits and similar installations. These data show some significant relations to body dimensions and agility of the subject. Standard methods are necessary for comparing escape exit tests in the future, if optimum design of exits and devices for minimum weight and space requirements is to be achieved.