ADMIX
admix
admix
Set of flashcards Details
| Flashcards | 90 |
|---|---|
| Language | English |
| Category | Physics |
| Level | Other |
| Created / Updated | 08.12.2016 / 15.09.2022 |
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Which of the following planforms gives the HIGHEST local profile lift coefficient at the wingroot?
Rectangular
Highest lift coefficient = Rectangular!
The fundemental difference between the areodynamic charecteristics of two and three-dimensional flow is that, in a three-dimensional flow about a wing:
a spanwise component exists in addition to the chordwise speed component.
in 3-D: a spanwise component + chordwise speed component!
flow on the upper surface:
The flow on the upper surface of the wing has a component in wing root dircetion.
flow above the wing has a component in wing root direction.
Airplane accerlerates from 80 to 160 with load factor 1.
The induced drag coefficient alters with factor 1:16
and induced drag with factor 1/4.
Acceleration: doubles
CDi: 1/16
Di 1/4
increasing AR on induced Drag:
it is reduced because the effect of wing-tip vortices is reduced.
increasing AR # decreasing induced Drag.
Induced drag is created by the:
spanwise flow pattern* resulting in the tip vortices.
*bilden
Di = spanwise flow pattern = tip vortices.
AR and induced Drag (Relationship)
a decrease in AR increases the induced drag
AR "^" : Di "v"
What is the effect on induced drag of mass and speed changes?
Induced Drag decreases with increasing speed and
induced drag decreases with decreasing weight!
DI ~ Weight
DI anti ~ speed
The induced drag increases as the lift coefficient increases.
DI ~ CL (lift coefficient)
High AR, as compared with Low AR has the effect:
decreasing induced drag and critical angle of attack.
High AR = decreased DI and AoA
TAS & Induced Drag
"TAS increases - DI decreases"
TAS anti ~ DI ((Diagramm) x und TAS))
CDi (The induced drag coefficient) is proportional with:
CL²
CDi ~ CL²
Induced AoA is the result of:
downwash due to tip vortices.
Induced angle of attack results from downwash due to tip vortices.
The span-wise flow on an unswept wing is from the:
lower to the upper surface via wing tip.
span-wise flow on an unswept wing:
lower to the upper surface via the wing tip!
local flow pattern:
By fitting winglets to the wing tip the strength of the wing tip vortices is reduced, which in turn reduces induced drag.
fitting winglets, reduces induced drag.
Dihedral of a wing is the angle between:
wing plane and the horizontal with the aeroplane in an unbanked, level condition.
Dihedral of a wing is the angle between:
WING PLANE and HORIZONTAL with the aeroplane in an unbanked, level condition.
Taper ratio is the ratio of:
the root chord to the tip chord.
TR: Root Chord to TIP CHORD
The aspect ratio of the wing is:
the ratio between the WING SPAN and the MEAN GEOMETRIC CHORD.
AR is the ratio WING SPAN : MEAN GEOMETRIC CHORD.
The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
the chord of a rectangular untwisted wing with the same moment and lift.
MAC = The Chord of a rectangular untwisted wing with the same moment and lift.
The angle between the aeroplane longitudinal axis and the chord line is the
angle of incidicne.
Angle between longitudinal axis and the chord line:
Angle of Incidence.
An aerofoil is cambered when:
the line, which connects the centres of all inscribed circles, is curved.
Cambered aerofoil : the line, which connects the centres of all inscribed circles, is curved.
A line connecting the leading- and trailing edge MIDWAY between the upper and lower surface o an aerofoil: This definiton is applicable for
the camber line.
connecting line between leading and trailing edge midway between the upper and lower surface: the camber line.
The relative thickness of an aerofoil is expressed in:
% chord.
Thickness of aerofoil in "% chord."
The lift- and drag forces, acting on an aerofoil:
depend on the pressure around the aerofoil.
Lift and Drag forces depend on pressure around the aerofoil.
Lift is the component of the total aerodynamic force, perpendicular to the undisturbed airflow.
Lift : component of total Aerodynamic force, perpendicular (senkrecht) to undisturber air/windflow.
An aeroplane's angle of incidence is defined as the angle between the:
longitudinal axis and the wing root chord line.
AoI is the angle between : longitudinal axis and the wing root chord line.
statement about weight or mass:
The weight of a body can determined by multiplying its mass by the acceleration due to gravity.
weight - multiplying - by its mass!
statemant: Mass!
The mass of a body can be determined by dividing its weight by the acceleration due to gravity.
Mass - dividing - weight!
In the SI system the unit of measurement for weight is Newton.
SI System: weight = NEWTON!
Mass in the SI-System:
In the SI-System the unit of measurement for mass is the kilogramm.
SI-System: Mass = KG!
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