QuizzesAccident investigation has traditionally focused on preventing accidents by concentrating on simple theories to determine "what happened," "who was responsible," and "when did it occur."

An airfoil's aerodynamic center is located on the chordline;

25% subsonic and 50% supersonic

You are flying at a Calibrated airspeed of 300 knots, at 25,000ft, in a standard atmosphere. Use the graphs on pages 25 and 26 of the textbook to find your EAS (Equivalent Airspeed);

290 kts

What is your TAS (True Airspeed)?

433 kts

Calculate the speed of sound at the freezing isothermal in the atmosphere where the air temperature is 0°C:

644 knots

Which Combination is correct;

For a constant TAS your Mach number increases as you climb

A laminar flow or 6 series airfoil has lower drag at all angles of attack than a cambered airfoil;

false

The speed of sound decreases at a constant rate as you climb to the Tropopause;

false

All cambered airfoils pitch;

nose-down

The ambient air temperature decreases at a constant rate in a standard atmosphere until it reaches the Tropopause:

true

Using the speed of sound from the table on page 20 of the text what is your Mach Number.

.72

At 40,000 ft the density of the air has dropped to;

1/4 of sea level

A 6 series or laminar flow airfoil's 'drag bucket' on a polar plot of Cl vs Cd shows;

Both b and c above

Choose the correct combination from these;

Cambered airfoils pitch nose down whereas symmetrical airfoils do not have pitching moments.

If your true airspeed is 488 knots at 38,000ft what is your Mach speed?

M0.85

As you climb in an aircraft

Your True Airspeed increases

The Magnus effect explains why;

both b and c

A 6 series airfoil or laminar flow airfoil is designed to;

keep the boundary layer laminar for longer than most airfoils

An air operated instrument that takes into account airspeed and altitude is;

machmeter

The speed of sound in air depends on;

temperature

As long as a "laminar flow" airfoil operates with the lift coefficient within the "Drag Bucket" the air flow will remain laminar farther back on the wing's upper surface with associated lower drag than a conventional airfoil.

true