DASH 1 Sec 6: Flight Characteristics

Question 1

Define Critical mach number

Answer 1

IAS at which the air velocity over the wings reaches Mach 1.0.

Question 2

Critical mach number will always occur at aircraft speeds greater than Mach 1.0.

Answer 2

FALSE

Question 3

Critical mach number will always occur at aircraft speeds less than Mach 1.0.

Answer 3

TRUE

Question 4

_______ is one of the most effective methods of increasing the critical mach number.

Answer 4

sweptwing design

Question 5

The maximum lift capability of a swept-wing aircraft is ______(less or more) than a straight-wing aircraft.

Answer 5

less

Question 6

The reduced lift capability of swept-wing aircraft is mor evident at (low/high) airspeeds.

Answer 6

low

Question 7

The decreased lift capability of swept-back wings on the T-1 at low airspeeds is offset by ______.

Answer 7

Fowler-type flaps

Question 8

The disadvantage of swept-back wings is _______(in terms of stall progression).

Answer 8

they cause a stall progression from the wing tips to the wing root

Question 9

Name four things that is gained by the T-tail aft engine design

Answer 9

1. Cleaner wing design 2. Lowers drag and increases maximum lift 3. Increases vertical tail and rudder effectiveness 4. Reduces downwash on the horizontal stabilizer

Question 10

A “deep stall” is when you feel the aircraft buffet.

Answer 10

FALSE

Question 11

A part of a “deep stall” can be describe as an AOA where the tail enters the turbulent wakes of the wings.

Answer 11

TRUE

Question 12

The T-1 has _____ type flaps.

Answer 12

fowler

Question 13

The rudder is more effective than the spoilers in picking up a low wing at low airspeeds.

Answer 13

TRUE

Question 14

With the speed brakes extended, roll forces will increase but roll rate will decrease.

Answer 14

FALSE

Question 15

______ degrees of pitch change is required to maintain level flight while lowering flaps to 10 degrees.

Answer 15

4

Question 16

____ degrees of pitch change is required to maintain level flight while lowering flaps from 0 to 30 degrees.

Answer 16

8

Question 17

____ degrees of pitch change is required to maintain level flight while lowering flaps from 10 to 30 degrees.

Answer 17

4

Question 18

Why is the limiting airspeeds for flaps 30 degrees 165, while it is 170 to lower flaps to 30.

Answer 18

pitot-static installation error.

Question 19

As fuel is burned, the T-1’s CG moves.

Answer 19

forward

Question 20

The T-1 is less pitch sensitive with a ______ (forward or aft) CG.

Answer 20

forward

Question 21

T-1 pilots only have to worry about wake turbulance and not cg problems during takeoff and landings.

Answer 21

FALSE

Question 22

At low altitude (I.e. final approach), to minimize your exposure to wake turbulence avoid the area ____ and ____ the preceeding aircraft.

Answer 22

below; behind

Question 23

Dudring a dive recovery the speed brakes will provide a lot of deceleration

Answer 23

FALSE,

Still pop them out, but prioritize pulling up first

Question 24

During single-engine operations in the T-1, more drag is created using the spoilers to counter asymmetrical thrust than using the roll trim tab.

Answer 24

TRUE

Question 25

Dutch roll is most evident at _____ airspeeds and _____ altitudes.

Answer 25

low/hig

Question 26

Name the three methods the Dash-1 recommends to dampen Dutch Roll.

Answer 26

yaw damper, autopilot, manual

Question 27

The primary method to eliminate Dutch Roll in the T-1 is _____

Answer 27

yaw damper

Question 28

During flight, the stick shaker will activate at approximatley _____ units on the AOA.

Answer 28

0.8 to 0.85

Question 29

During flight, the stall warning light and horn will activate at _____ units on the AOA indicator

Answer 29

1

Question 30

The stick shaker may activate at as low as _____ units AOA at high altitudes.

Answer 30

0.5

Question 31

The T-1 is less likely to spin with a forward CG than an aft CG.

Answer 31

TRUE

Question 32

The airspeed indicator is not reliable in a spin.

Answer 32

TRUE

Question 33

A compressor stall is characterized by a thumping sound.

Answer 33

TRUE