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5 Preliminary Sizing - HAW Hamburg
5 - 7 Fig. 5.4 Maximum lift coefficient of aircraft with different high-lift devices as a function of wing sweep. For take-off configuration the given values have to be reduced by 20 percent (based on data from Raymer 1989) Table 5.2 Statistical values of maximum landing mass over maximum take-off mass mML / mMTO for different types of aircraft (based on Roskam I)
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Project - HAW Hamburg
www.fzt.haw-hamburg.deIn this project, ground handling has been further discussed and differences have been compared in the results. Ground handling is ... SGHA Standard Ground Handling Agreement SWAT Southwest Airlines Air Travel . 8 . 1 Introduction . 1.1 Motivation . LCA are a blooming industry. Due to the economy downturn, many passengers have chosen
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www.fzt.haw-hamburg.deThe vapor compression cycle (VCC) is the principle of Vapor Compression Refrigeration Systems (VCRS) known in aviation as the Vapor Cycle Machines (VCM). Conventional air conditioning systems, heat pumps, and refrigeration systems that are able to cool (or heat, for
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8 High Lift Systems and Maximum Lift Coefficients
www.fzt.haw-hamburg.de8 - 2 Trailing edge high lift systems The plain flap (Fig. 8.1) is simply a pivoted rear section of an airfoil. Typically the flap depth cF amounts to 30% of the chord. The plain flap increases lift by increasing the airfoil camber. Ailerons, elevators and rudders are plain flaps.
9 Empennage General Design - HAW Hamburg
www.fzt.haw-hamburg.de9 - 7 Fig. 9.5 Positioning of horizontal tailplanes The aim of the V-tail is to achieve a smaller tail area than with horizontal and vertical tail- planes, for example in the form of the conventional tail. The V-tail is designed as follows: In the first step the required areas of a conventional horizontal tailplane SH and vertical tailplane SV are determined (see below).
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www.fzt.haw-hamburg.deThe airfoil section is described by the section coordinates of the top of the section yu = f (x) and the bottom of the section yl = f (x) with0≤x ≤1. Sections can also be described by the thickness distribution t = f (x) combined with the camber yc = f (x). Fig. 7.2 contains additional parameters for describing the section geometry: Chord c ...
4 Aircraft Configurations - HAW Hamburg
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