Principles of Flight (POF)
Principles of Flight FS 15 Klasse:AV14 Dozent:Manfrian Weiteres Lernmaterial unter: www.tinyurl.com/av14fs15
Principles of Flight FS 15 Klasse:AV14 Dozent:Manfrian Weiteres Lernmaterial unter: www.tinyurl.com/av14fs15
Set of flashcards Details
| Flashcards | 126 |
|---|---|
| Students | 127 |
| Language | English |
| Category | Technology |
| Level | University |
| Created / Updated | 29.05.2015 / 14.04.2024 |
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\({Re_x}_{cr}\) is the ...
critical Reynoldys Number. It is the Reynolds number at \(x_{cr}\) where the boundary layer becomes turbulent
\(x_{cr}\) is ...
the critical value where the boundary layer becomes turbulent
Name the two major consequences of flow separation
1. drastic loss of lift
2. major increas in drag, caused by pressure drag due to separation
Name the two sources of drag due to viscous effect
1. Skin friction
2. pressure drag due to separation
Number 1
Leading edge
2
Thickness
3?
Mean camber line
4
Trailing edge
5
Chord line
6
chord
7
camber
The straight line connecting the leading and trailing edges is the ...
chord line
The distance between the leading and the trailing edge is the ...
chord , c
The ... ist the maximum distance between the ... and the ...
(airfoil)
camber, camber line, chord line
The moment about the aerodynamic center of an airfoil is ...
The quarter chord point is for low-speed subsonic airfoils close to the ...
aerodynamic center
\(c_L\) is a function of
shape of the airfoil, angle of attack, Reynolds-Number
angle of attack is the angel between the relative wind and ...
All airfoil with positive camber have a \(\alpha_{L=0}\) .... 0
1
\({c_L}_{max}\)
2
Stall
3
\(a_0\) Lift slope
4
stalling angle of attack
5
\(a_{L=0}\) zero lift angle of attack
The Reynolds number has a big influence when the airfoil is in ...
Profiles with positive camber have a ... \(c_{m,c/4}\)
Lift of an Airfoil is always to be considered as ....
Lift per unit span
Airfoil:
The Drag varies alot with different .... because ....
Reynold Numbers, the drag of a slender aerodynamic shape is mainly skin friction drag
The center of pressure is the point where ...
Which profile is the thickest?
The Prandtl-Glauert correction
takes the effects of compressibility between 0.7> \(M_{\infty}\)>0.3 into account
The critical Mach number for a wing decreases when
thicker airfoils have a ... \(M_{crit}\) than thin ones
\(c_p\) can by definition not be ....
Wing tip vortices are formed because
The pressure at the bottom of the wing is higher then on the top. Consequently there is some tendency for the air to flow around the wing tips
As the aspect ratio is increased
induced drag is ... for an elliptical wings
the effective angle of attack \(\alpha_{eff}\) is ... than the geometric angle of attack
Consider downwash
\(\alpha-\alpha_{eff} =....\)
the lift curve slope of a .... wing is ... than that of a ... wing
the lift curve slope of a finite wing is smaller than that of a infinite wing
