AS309 ERAU Test 1

Knots x ____ = feet per second

1.69

Feet per second x _____ = knots

0.5925

Miles per hour x ______ = feet per second

1.47

Feet per second x ______ = miles per hour

0.6818

1 NM = ___ feet

6076

1 NM = ____ SM

1.15

Knots x _____ = feet per minute

101.3

lb * sec^2 / ft =

slug

Acceleration due to Gravity

32 feet per second

PE =

Wh

KE=

1/2mv²

HP=

TV/325

F=

ma

Dynamic pressure (q) =

σv²/295

Bernoulli's Equation (H) =

P + q

TAS =

EAS / sq(σ)

δ =

P/P₀

θ =

T/T₀

σ =

ρ/ρ₀

Q =

ρAV

Continuity Equation =

A1V1 = A2V2

EAS =

CAS + ΔV

Standard Density

0.002377 slugs/ft³

Standard Pressure

29.92

Standard Temperature (R)

519

Standard Temperature (K)

288

Calibrated Airspeed is Indicated Airspeed corrected for

Ram Air Effect

Equivalent Airspeed is Calibrated Airspeed corrected for

compressibility effects

True Airspeed is Equivalent Airspeed corrected for

Density ratio

______ is a straight line connecting the leading edge and trailing edge of the airfoil

Chord Line

_____ is the length of the chord line

Chord

________ is a line drawn halfway between the upper surface and lower surface

Mean camber line

______ is the maximum distance between the mean camber line and chord line

Maximum camber

________ is the maximum distance between the upper and lower surfaces

Maximum thickness

The last two digits of any NACA description are

max thickness

At maximum thickness of the airfoil, static pressure is at its

minimum

In a four digit NACA description, the first digit stands for

maximum camber

ROC (ft/min) =

V sin y

ROC (ft/sec) =

101.3 v sin y

Fb =

μFn

What pressure is in a pitot tube?

Total Pressure

L =

ClqS

Stall Speed =

√295L/Cl(max)σS

S =

Wing area

The heaver the aircraft weights, the ____ the stall speed is.

faster

The thicker the airfoil, the ________ the aircraft can fly

slower

What are the two types of airflow?

Laminar and Turbulent

RN =

Vx/v

The airflow in the boundary layer is acted upon by what two forces?

Friction and Adverse Pressure Gradient

Devices that increase Cl by changing the camber of the wing are called

camber changers

Devices that increase Cl by changing the energy in the boundary layer are called

energy adders

V₂ =

V₁√W₂/W₁