By A.J. Jackson
;De Havilland Tiger Moth[Aircraft Profile 132] КНИГИ ;ВОЕННАЯ ИСТОРИЯ Название:De Havilland Tiger Moth Автор: A.J. Jackson Серия: plane Profile 132 Издательство: Profile guides Ltd Год издания: 1966 Страниц:16 Формат: PDF в rarЯзык: английский Размер: 9.07 Мб Для сайта: Мир книгУчебно-тренировочный биплан De Havilland Tiger Moth разработан в 30-е годы для первичного обучения для Королевских Воздушных силах Великобритании и использовался в этой роли до 1952 года. Широко экспортировался, кое-где используеться и до сих пор ifolder.ru.com zero
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Additional resources for De Havilland Tiger Moth
G. the area of the neutral wing projected on the ground and including the portion inside the fuselage. The wing area is not a constant, because of the use of high-lift devices in take-off and landing operations. However, it is calculated with the control surfaces in the neutral position. The presence of additional aerodynamic surfaces, such as horizontal tail and canards, affects the position of the lift force, the magnitude and the share of lift generated by the aircraft’s subsystems. Two important non-dimensional quantities are the Reynolds number and the Mach number.
The percentage of this drag on the total drag count depends on the type of aircraft and its operational configuration, and varies from 25–30% for a supersonic jet fighter to 70–80% in the case of a VTOL aircraft. For a commercial subsonic jet aircraft the contribution of the fuselage to the zero-lift drag is of the order of 30%. The skin friction drag of modern large aircraft is close to the theoretical value from turbulent flat plate theory at the corresponding Reynolds number. The effect of Reynolds number can be evaluated from a number of semi-empirical relationships.
Describe how the temperature can affect the cruise conditions and the fuel consumption, and find an engineering solution (problem-based learning: additional research is required). 9. Calculate the relationship between the leading-edge and the quarter-chord sweep angle for a wing with a straight leading edge. The taper ratio is l, the tip and root chords are ctip and croot, respectively; the wing span is b, and the wing area is A. 10. 7. 5 km, T 1 ¼ d70 C. 0055 C/m. Stop the calculation at the troposphere.