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9 Empennage General Design - HAW Hamburg
9 - 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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7 Wing Design - HAW Hamburg
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 ...
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www.fzt.haw-hamburg.deWhen discussing advantages and disadvantages of several configurations one should always keep in mind that each person has its own subjective preferences. These personal views must not preclude to perfom an assessment as objective as possible. 4.2 Three-View Drawings of Unconventional Configurations
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J. Abulawi - fzt.haw-hamburg.de
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www.fzt.haw-hamburg.deApplying gained insight in a critical investigation of current long range aircraft operation. The report has to be written in English based on German or …
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www.fzt.haw-hamburg.de2 Jet Engine Shafts and Bearings Main jet engine shafts are supported by a minimum of two bearings. At least one bearing has to be a thrust ball bearing that can take axial and radial loads. The other bearing can be a cylinder roller bearing that takes only radial loads. Bearings are located inside a bearing sump.
A380 Landing Gear and Systems - HAW Hamburg
www.fzt.haw-hamburg.decommercial transport aircraft, powered by 4 RR Trent 900 or ... •5 Rotor Carbenix®4000 heat-sink •1.59inch wear pin •23 spline titanium torque tube ... Normal ATA32 functions controlled by shared avionics units for all systems 4 Core Processor Input Output Module (Integrated Modular Avionics) CPIOM-G (IMA): All ATA32 System functions ...
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.
5 Preliminary Sizing - HAW Hamburg
www.fzt.haw-hamburg.de5 - 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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