ASCI
309 Final Exam (Part 1 and 2)
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Question 1
What would be the length of the
takeoff run (ft)?
GIVEN INFORMATION:
Use "g" = 32.2 ft / s2
1 knot = 1.69 ft / s
Gross Weight = 20,000 pounds
Average Drag = 1,500 pounds
Average Friction Force = 500 pounds
Average Thrust = 10,000 pounds
Lift Off Speed = 130 KTAS
655 feet
1870 feet
1644 feet
3650 feet
Question 2
According to the universal gas law,
temperature changes do not affect
density or pressure.
pressure is proportional to changes in
temperature but not density.
density is always constant with either
temperature or pressure changes.
density in proportional to pressure
changes and inversely proportional to temperature changes.
Question 3
Find Temperature Ratio at Cruising
Altitude.
Barometric Altimeter setting = 30.42
in.Hg
Cruising Indicated Altitude = 20,500
ft
Outside Air Temperature at Cruising
altitude = - 22.32 deg F
Atmosphere Table 2.1
0.8433
0.8625
0.9807
0.9287
Question 4
Find True Airspeed (KTAS).
Pressure Altitude = 20,000 ft
Outside Air Temperature at Altitude =
-22.32 deg F
Indicated Airspeed = 225 KIAS
Atmosphere Table 2.1
Compressibility Correction Figure 2.6
Position error correction chart
provided:
401 KTAS
219 KTAS
297 KTAS
225 KTAS
Question 5
Find Mach Number.
Pressure Altitude = 20,000 ft
Outside Air Temperature at Altitude =
-22.32 deg F
Indicated Airspeed = 225 KIAS
Atmosphere Table 2.1
Compressibility Correction Figure 2.6
Position error correction chart
provided
0.53 M
0.82 M
0.61 M
0.49 M
Question 6
Calibrated airspeed is indicated
airspeed corrected for:
Compressibility.
Position error.
Instrument error.
Both B & C above.
Question 7
A very low Reynolds number (<0.5
million) is associated with what type of boundary layer?
Laminar.
Turbulent.
Detached.
Adverse.
Question 8
Compute stall speed in Knots
Equivalent Airspeed (KEAS) for aircraft with the following conditions:
• Weight-20,000
lbs
• Sea
level
• Wing
area- 200 ft2
• CL-1.5
140 KTAS
151 KTAS
185 KTAS
135 KTAS
Question 9
How does decreasing camber on an
airfoil affect CL max and Stall AOA?
Stall AOA increases, CL max increases.
Stall AOA decreases, CL max increases.
Stall AOA increases, CL max decreases.
Stall AOA decreases, CL max decreases.
Question 10
What would you expect from an aircraft
that does not use its flaps for approach and landing?
Lower approach speeds
Higher Stall speeds
Lower nose attitude in Flare
All of the above
Question 11
Induced Drag on an aircraft flown at a
cruising altitude
Increases with Velocity
Increases with Angle of Attack
Is greater on low aspect ratio
aircraft
B
and C above
all of the above
Question 12
An aircraft taking-off and exiting
ground effect can expect what?
Increased induced drag
nose-down pitching moment
Lateral–directional oscillations
A & B above
Question 13
An aircraft with a low aspect ratio
wing
will produce more induced drag than a
high aspect ratio wing
will produce more parasite drag than a
high aspect ratio wing
will lose more energy in a high g turn
than a high aspect ratio wing
A & C above
Question 14
Which of the following contributes to
an increase in directional stability?
Decreasing wing sweepback
A fuselage with a big canopy forward of
the CG
Larger Vertical Stabilizer
A and B above
All of the above
Question 15
Swept-wing aircraft with T-Tails are
susceptible to what condition when in extended high AOA flight?
Nose slice
Dutch roll
Deep stall
Excessive nose down pitching moments
Question 16
If an aircraft exhibits positive
static and dynamic longitudinal stability, then
if upset from its trimmed condition it
will return to trimmed condition with diverging oscillations.
if upset from its trimmed condition,
it will return to trimmed condition with converging oscillations.
if upset from trimmed condition, it
will not return to its trimmed condition.
if upset from trimmed condition, it
will stabilize at a different trimmed condition.
Question 17
What are the two dynamic longitudinal
oscillatory modes?
Short Period and Dutch Roll
Short Period and Phugoid
Corriolis and Phugoid
Dutch Roll and Phugoid
Question 18
Which of the following contributes to
an increase in lateral stability?
Positive Wing Dihedral
More Wing Sweep back
High Wing
All of the above
None of the above
Question 19
Find Parasite drag (DP) of aircraft at
Stall speed.
Weight (W) = 20,000 lb
Wing Area (S) = 200 ft2
Altitude = 5, 000 ft
CLMAX = 1.5
Temperature - Standard
Drag coefficient (CDp) = 0.02
20,000 lb
2,000 lb
269 lb
320 lb
Question 20
Parasite drag on an aircraft
increases with velocity squared
increases with the square root of
velocity
decreases with velocity
is constant with respect to velocity
Question 1
All aircraft have what spin recovery
technique?
Rudder Opposite/Neutral Aileron/ Full
forward stick.
Rudder Opposite/Into spin Aileron/
Full Aft stick.
Rudder Into spin/ Aileron away from
spin/ Stick full aft.
Every aircraft has a different
recovery technique. Consult the flight manual.
Question 2
Most commonly effective spin recovery
for a straight-wing aircraft
Stop spin rotation with opposite
aileron and lower AOA with Aft Stick
Stop spin rotation with aileron into
the spin and lower AOA with Aft stick
Hold what you got
Stop spin rotation with opposite
rudder and lower AOA with Forward stick
Question 3
The Auto rotation spin characteristics
of a straight-wing aircraft are induced by
More Drag on the down going wing
More Lift on the up going wing
A & B above
None of the above
Question 4
What is the recommended way to
decrease airspeed while flying in the region of reverse command?
Increase Drag
Decrease Thrust
Increase Angle of Attack
Pitch nose down
Question 5
What is the effect of altitude on
Specific Endurance for a jet aircraft?
Thrust specific fuel consumption is
lower due to lower temperature
Thrust Required (drag) remains the
same at Best Endurance Airspeed regardless of altitude
Fuel Flow is lower at higher altitudes
up to the Tropopause so Specific Endurance is improved.
All of the above
Question 6
How does the weight change during
flight due to fuel burn affect Best Range Airspeed (VBR) and Best Endurance
Airspeed (VBE)?
Both VBR and VBE decrease
Both VBR and VBE increase
Both VBR and VBE stay the same
throughout flight
VBR decreases but VBE stays the same
Question 7
According to the Aerodynamic text-How
does Thrust Specific Fuel Consumption (Ct) vary with altitude?
Thrust Specific Fuel Consumption does
not change with altitude.
Thrust Specific Fuel Consumption
increases with increases in altitude.
Thrust Specific Fuel Consumption
decreases with increases in altitude.
Thrust Specific Fuel Consumption is
equal to thrust.
Question 8
What is the affect of landing rollout
performance if approach speed is 10% higher (i.e., 110 KIAS versus 100 KIAS).
Assume braking action is the same.
Landing distance is 10% greater
Landing distance is 21 % greater
Landing distance is 5% greater
Landing distance is the same
Question 9
At what speed does the normal shock
wave on top of the wing cause the boundary layer to separate from the wing
causing Drag divergence?
Mach 1.0
airspeeds of about 5% above Mcrit
airspeeds of about 10% above Mcrit
Mcrit
Question 10
Normal shock waves
Do not Change direction of air stream
Decrease air stream velocity to
subsonic speeds
Compress air making it more dense with
a higher static pressure
All of the above
Question 11
What is the Ultimate positive Load
before structural failure for the following aircraft?
Aircraft Weight = 20,000 lbs
Aerobatic Category aircraft = (+6g,
-3g)
9,000 lbs
30,000 lbs
120,000 lbs
180,000 lbs
Question 12
If an aircraft is maneuvering above
Maneuvering Airspeed (VA) what is the potential danger?
Spin
Deep Stall
Structural damage
Uncoordinated flight
Question 13
What is the turn radius for an
aircraft under the following conditions?
Airspeed = 300 KTAS
Angle of Bank = 80 deg
Altitude constant - Sea Level
1000 ft
1400 ft
2000 ft
3500 ft
Question 14
At 120 KTAS, what is a good angle of
bank to use to generate a level standard rate turn for instrument flight
conditions?
18 deg AOB
9 deg AOB
12 deg AOB
25 deg AOB
Question 15
Given T-38 Thrust Available/ Thrust
Required Curve Figure 6.11. Weight 10,000 lbs. What is the Best Angle of Climb
(AOC) and Best Climb Angle Airspeed (VX) at 100% RPM?
0.342 deg, 270 KTAS
19.9 deg, 245 KTAS
0.127 deg, 265 KTAS
7.3 deg, 245 KTAS
Question 16
If the aircraft lost thrust to all
engines at 10,000 ft what would the glide range (nm) be if the aircraft was
flown at the AOA associated with best L/D in figure 5.2 from the text?
8.2 nm
11,000 nm
18.1 nm
15.5 nm
Question 17
Given T-38 Thrust Available/ Thrust
Required Curve Figure 6.11. Weight 10,000 lbs. What is the Rate of Climb (fpm)
at Best Climb Angle Airspeed (Vx)?
8400 fpm
3152 fpm
1000 fpm
10,000 fpm
Question 18
Why is a“spike" inlet a better
aerodynamic design than a flat circular intake?
The intake can block foreign object
damage items
The “spike” produces normal shock
waves instead of oblique shock waves
The “spike” produces oblique shock
waves which increase the induced drag
The “spike” produces oblique shock
waves which weaken the normal shock wave and reduces compressibility drag
Question 19
What causes Airspeed Maximum
restrictions in high speed aircraft?
Aerodynamic heating
Tuck under
Control effectiveness
High Speed Buffet
All of the above
Question 20
What are some of the causes of “tuck
under” as an airplane exceeds Mcrit?
Less downwash so Horizontal tail
develops more Lift
Movement of shock waves toward the
front of the wing
AC moving from 25% Chord to 50% Chord
All of the above
A and C above
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