:Bingo!!!!!Cheers LOFT:D
It will be highly appreciated if u can solve it here in details

Q2.De Compression Sickness is related with
1. Henry's Law
2. Dalton Law
3. Boyle Law
4.Charles law

Henrys Law of Gases - Nitrogen forming bubbles and escaping out of tissues.
:ok:

Hey guys,hv a small doubt..wot is the accuracy of DME acc to ICAO standards,is it 0.25nm+1.25% of range or (.5 or 3% of range)??

I believe its 0.5Nm or 3% which ever is higher

@LOFT-U r right again.Guys every body post some question also...
Q3.What are frangible objects?

DME Accuracy is + - 0.2nm as per the latest ICAO Annex ;
( and 0.25 nm + 1.25 % of range for older aircraft, older than 1989)

Frangible = brakeable (easily broken)

:ok:

@aviator4u-

it is .25nm 1.25%if u go by oxford and .5nm 3% if u go by GSP. I'll rather prefer oxford over GSP at this stage. :ok:

@pradeep747-

objects which tend break into fragments if deformation force applied.:ok:

CHEERS..!!

How does leading and trailing edge flaps affect critical angle of attack ?

Why is Vmcg determined with nosewheel steering disconnected ??:ugh:

Disengaging the Nosewheel Steering provides a wet runway simulation.
:ok:

@LOFT-

What about my previous ques.?

Leading edge flaps Increases critical AOA and trailing edge reduces critical AOA

Basically you can pitch up higher when using the Leading edge devices and lesser with the Trailing edge flaps in comparison to the Clean configuration.
:ok:

Nice work guys....btw..all these questions being posted from oxford??

The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42. An increase in angle of attack of 1 degree increases CL by 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be:

1.71
1.49
2.49
0.74

Request u to put up an explained answer.

[IMG]file:///C:/Users/yogesh/AppData/Local/Temp/moz-screenshot-7.jpg[/IMG][IMG]file:///C:/Users/yogesh/AppData/Local/Temp/moz-screenshot-8.jpg[/IMG]

the answer is 1.71
heres the explanation well its another example hope it helps u
Example 1.
An aeroplane is flying straight and level with a coefficient of lift of 0.55. The coefficient of lift
increases by 0.08 per degree increase in angle of attack. If a vertical gust increases the angle of
attack by 3º, what is the load factor?
Since the vertical gust increased the angle of attack by 3º the coefficient of lift will have increased
by 0.24 (0.08 x 3), and the new coefficient of lift is 0.79 (0.55 + 0.24). Since the coefficient of lift
and lift are proportional to the load factor the new load factor is 0.79/0.55 = 1.44. The new load
factor is therefore 1.44 and if the question had asked for the increase in load factor this would be
0.44.
Example 2
What is the percentage increase in lift if the angle of attack increases by 4º due to a vertical gust.

Load factor is 1.71
 

@ wings on fire
Let's assume lift is propotional to CL since other factors are not changing

Load factor = lift(produced at that instant/ wing loading/ wt
Here let's call AOA as variable 'x' fr simplicity

CL= k*x. k is a constant for all other variables which are nit changing like wing area, density etc

0.42=k*x
0.52=k*(x+1)

When AOA changes by 3 deg equation becomes
CL=k*(x+3)

Substitue values frm above equation n get CL= 0.72 when gust is experienced.

Now go back to st n level condition

Load factor=1
that means wt= lift in this case which is 0.42

Load factor in gust= lift(in gust)/ wt(which is constant)

Load factor = 0.72/0.42
= 1.71

Cheers

@ wings on fire
Hi.... Have you got the payment mail yet,,? .... i got the first mail on 3 DEC too and haven't got any reply yet :sad: