Reading...
Play button
Play button
Use LEFT and RIGHT arrow keys to navigate between flashcards;
Use UP and DOWN arrow keys to flip the card;
H to show hint;
A reads text to speech;
70 Cards in this Set
- Front
- Back
|
For constant Lift force,
each ... requires a specific .... . |
* IAS
* AOA |
|
|
Min IAS is determined by ....
|
CLmax
|
|
|
GS @ high altitude airport landing is ...
while ... is unchanged |
* higher than low altitude
* IAS |
|
|
Expected flight condition @ leaving ground effect
|
* increased Di
* demand for higher AOA |
|
|
Lift vs. Airspeed
[math] |
Lift ∝ AS²
|
|
|
TAS & AOA for same Lift @ higher altitude
|
* Higher TAS
> for any given AOA |
|
|
For the same Lift, a .... AOA is req. @ ground effect.
|
lower
|
|
|
Flight condition @ worst wingtip vortices
|
> Heavy
> Slow > Gear & flaps up |
|
|
Hazardous vortex turb
created only when ... . |
developing lift
|
|
|
Vortex circulation around wingtip is
|
> outward
> upward > around the wingtip |
|
|
@ Crosswind
... vortex tend to stay longer @ rwy. |
Upwind
|
|
|
To avoid wingtip vortices of departing jet.
pilot to .... & .... |
> climb above
> & stay upwind |
|
|
what wind condition
prolongs hazards of wake turb? |
light quartering TWD
|
|
|
To avoid wake turb.
plat to lift off ... the point where the preceding jet toke touched down. |
beyond
|
|
|
Lift @ wing def.
|
* force
> acting perp. to > relative wind/flight path |
|
|
AOA directly controls ...
|
distribution of Px acting @ wing
|
|
|
Opposing forces @ level steady state flight
|
are equal
|
|
|
A/C always stalls @ same ... not ...
|
*AOA
* airspeed |
|
|
@ Given IAS
effect of increased air density @ lift/drag? |
* both remain constant
(hahaha) |
|
|
Aspect Ratio
ratio of ... . |
* wing span
> to average/mean chord |
|
|
T.O from low density altitude airfield
run? TAS? |
* shorter T.O. run
> due to lower TAS for same IAS |
|
|
Induced vs. parasite drag
@ increase gross Wt. |
* Di increases more than parasite
|
|
|
Induced drag is a .... created by .... .
|
* portion of total drag
* production of lift |
|
|
Best L/D when Dp is ... .
|
= Di
.~.,` |
|
|
wind effect @ L/D
|
no effect !
(not affected by speed) |
|
|
Best L/D @ given config
vs. IAS |
* remains constant
* regardless of IAS |
|
|
Skin friction is part of ... drag
|
* parasite
(Form drag is another branch of parasite!) |
|
|
Aspect ratio vs. control qualities
|
Hi AR : Poor control @ low speed
|
|
|
Di vs. AR
|
Cdi inv.prop to AR
|
|
|
@ constant velocity
Hi AR will have ... drag esp @ .... AOA |
* decreased
* Hi |
|
|
Considering AR only
the wing with .... AR generates more lift |
Higher
|
|
|
Total drag behavior
form CLmax to max speed |
dec
then inc ☻ |
|
|
Tangent on ..... is the best L/D
|
* whole a/c CL / CD polar
|
|
|
a/c stall at same ... regardless of .... (3).
|
* AOA
> attitude with relation to horizon > gross wight > being in a turn |
|
|
Weight inc with no change of CG position
Stalling AOA will .... . |
* Remain the same
(be careful!) |
|
|
New stall speed calculation formula
using the new Wt. |
* Vs.new
= Vs.old x √ (new Wt. / old Wt.) |
|
|
New stall speed calculation formula
@ turn |
* Vs.turn
= Vs x √(1/cos ø) |
|
|
Stalling speed @ steady turn is ... .
|
higher
|
|
|
Effect of ice @ leading edge
on stalling speed / AOA |
speed : higher :(
AOA : lower :( |
|
|
Load factor is ... .
|
Lift ÷ Wight
|
|
|
Stalling may be delayed to higher AOA by ...
|
increasing KE of boundary layer
|
|
|
A .... causes wing to stall first @ root.
|
* Stall inducer strip
|
|
|
On .... tapered wing
stall first @ tip :( |
Highly
(> without wing twist ) |
|
|
Sweepback effect on tip stall ...
|
* increases tip stall tendency
|
|
|
Purpose of
Boundary layer fence @ swept wing to control ... . and delay ... . |
* spanwise flow
* tip stall |
|
|
Wing washout has ... .
|
* tip incidence
> less than * root incidence |
|
|
Downwash @ untapered wing without twist
[behavior] |
inc from root to tip
|
|
|
Wing of constant thickness
without sweep back could .... due to ... . [stall behavior) |
* drop a wing @ stall
* lack of any particular stall inducing charac. |
|
|
Slots increase .... by ....
|
* stalling AOA
* delaying separation |
|
|
Rectangular wing
tendency to stall first @ ... . |
* Root
|
|
|
Vortex generators
used for .... . |
reducing boundary layer separation.
|
|
|
Stick shaker ?
|
* device vibrates control column
> give stall warning |
|
|
Stall warning set to operate @ .... .
|
5% to 10% above Vs
|
|
|
Stagnation point pos.
just before stall |
Below stall warning vane
|
|
|
Stall warning vane is positioned @ ....
|
LE @ lower surface
|
|
|
Stall warning device input(s)?
|
AOA
sometimes rate of chx of AOA |
|
|
Stick pusher?
|
device to prevent a/c stalling
|
|
|
@ Developed spin
wings AOA sign? (+ve/-ve) |
both wings +ve
|
|
|
Spin recovery
Elevators ? |
* move down
> to reduce AOA |
|
|
Hi speed buffet (shock stall)
caused by ... |
* boundary layer separation
> immediately behind shock wave |
|
|
Indications of icing induced stall
[4] |
1. violent roll
2. airframe buffet 3. violent wing drop 4. extremely hi rate of descent @ normal flight att. |
|
|
Single engine stall recovery
@ power on climbing turn |
> Elev fwd
> Aileron neutral > rudder to prevent wing drop |
|
|
Flaps lowered
stalling speed will ... . |
decrease
[good!] |
|
|
Flaps lowered
Stalling AOA will ... CLmax will ... . |
decrease ☹
Increase ☺ |
|
|
Full flap effect @ Max L/D ratio ?
|
decreasing
|
|
|
Leading edge slot effect @ stalling speed :
|
decrease
|
|
|
Purpose of LE droop
is to increase .... and .... . |
* wing camber
* delay separation > when TE flaps lowered |
|
|
.... flap gives greatest change of pitching moment
|
fowler
|
|
|
Flaps lowered
spanwise flow @ upper surface ? |
inc towards the root
|
|
|
Flaps lowered @ app.
AOD will ... without ... . |
* increase
* power increase |
