C4 - Aerodynamic Force/Aerofoil Pressure Flashcards
1
Q
Chord
A
Straight Line between LE and TE
Chord Line = Distance
2
Q
Camber
A
Distance between chord and mean camber line
3
Q
Mean Camber Line
A
Equal distance from upper/lower surface LE to TE
4
Q
Positive Camber
A
Ideal for wings/aerofoil
Creates lift at 0 degree AOA
CP moves up forward with AOA
5
Q
Negative Camber
A
Usually on tailplane
Creates a nose down moment at 0 degrees AOA
6
Q
Lift
A
Component of total reaction perpendicular to relative airflow
7
Q
Drag
A
Component of total reaction parallel to relative airflow
8
Q
CP
A
Total aerodynamic origin
9
Q
Thickness chord ratio
A
Ratio of aerofoil thickness to chord length
10
Q
AOA
A
Angle between relative air flow and chord line
11
Q
Dynamic Pressure Equation
A
1/2 x p x v2
12
Q
SI units for velocity
A
M/s
Knots x 0.514
M/S / 0.514
