Question 1 An aircraft is flying trim stick-fixed at steady level flight with a speed of 80 m/s and at standard sea level conditions, where the air density is 1.225 kg/m³. The ratio of the wings' surface area to the tail plane's surface area is 10, the tail arm is 10 m and the wings' mean aerodynamic chord length is 2 m. The ratio of the tail plane's lift to the wings' lift is -0.01 at that condition. The rest of the known data are given in the two tables at the end of the question. Justify any assumption that you make. al Calculate the Calculate the downwa the tail plane angle of attack [6 marks] c) Find the elevator's deflection angle and the hinge moment coefficient. You may assume the tab's deflection angle is zero. Barkst d) Calculate the c.g. margin H, of the aircraft, argue for the sign of dCм/dC, and whether the aircraft is statically stable or not. d) Cal MCI MOC Vallato assu margin H KS de/dCL Смо ho h nT 50 -0.05 2º 0.2 0.15 Lift curve slopes and hinge moment curve slopes a a1 I az a3 b₁ bz b3 5.7 rad 1 4 rad 1.5 rad 1 1 rad 0.2 rad 1 -0.5 rad1 -0.02 rad-1 You may find the following expression useful STIT CM CMO + (h-ho)CL - VTC, Vr = Swe Ca₁a + a2n + a3ẞ CH = b₁α + b₂+b3ẞ a1 a as (1-4) de da
Question 1 An aircraft is flying trim stick-fixed at steady level flight with a speed of 80 m/s and at standard sea level conditions, where the air density is 1.225 kg/m³. The ratio of the wings' surface area to the tail plane's surface area is 10, the tail arm is 10 m and the wings' mean aerodynamic chord length is 2 m. The ratio of the tail plane's lift to the wings' lift is -0.01 at that condition. The rest of the known data are given in the two tables at the end of the question. Justify any assumption that you make. al Calculate the Calculate the downwa the tail plane angle of attack [6 marks] c) Find the elevator's deflection angle and the hinge moment coefficient. You may assume the tab's deflection angle is zero. Barkst d) Calculate the c.g. margin H, of the aircraft, argue for the sign of dCм/dC, and whether the aircraft is statically stable or not. d) Cal MCI MOC Vallato assu margin H KS de/dCL Смо ho h nT 50 -0.05 2º 0.2 0.15 Lift curve slopes and hinge moment curve slopes a a1 I az a3 b₁ bz b3 5.7 rad 1 4 rad 1.5 rad 1 1 rad 0.2 rad 1 -0.5 rad1 -0.02 rad-1 You may find the following expression useful STIT CM CMO + (h-ho)CL - VTC, Vr = Swe Ca₁a + a2n + a3ẞ CH = b₁α + b₂+b3ẞ a1 a as (1-4) de da
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
Related questions
Question
Answer c and D
![Question 1
An aircraft is flying trim stick-fixed at steady level flight with a speed of 80 m/s and at standard sea
level conditions, where the air density is 1.225 kg/m³. The ratio of the wings' surface area to the tail
plane's surface area is 10, the tail arm is 10 m and the wings' mean aerodynamic chord length is 2
m. The ratio of the tail plane's lift to the wings' lift is -0.01 at that condition. The rest of the known
data are given in the two tables at the end of the question. Justify any assumption that you make.
al Calculate the
Calculate the downwa
the tail plane angle of attack
[6 marks]
c) Find the elevator's deflection angle and the hinge moment coefficient. You may assume the tab's
deflection angle is zero.
Barkst
d) Calculate the c.g. margin H, of the aircraft, argue for the sign of dCм/dC, and whether the aircraft
is statically stable or not.
d) Cal
MCI MOC Vallato assu
margin H
KS
de/dCL
Смо
ho
h
nT
50
-0.05
2º
0.2
0.15
Lift curve slopes and hinge moment curve slopes
a
a1
I
az
a3
b₁
bz
b3
5.7 rad 1
4 rad
1.5 rad 1
1 rad
0.2 rad 1
-0.5 rad1
-0.02 rad-1
You may find the following expression useful
STIT
CM CMO + (h-ho)CL - VTC, Vr =
Swe
Ca₁a + a2n + a3ẞ
CH = b₁α + b₂+b3ẞ
a1
a
as (1-4)
de
da](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F60272644-2df7-4793-bdff-d8f1f2c711e5%2F1913e879-86a9-4010-9729-22d233e2fbc1%2Furcg1w2_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Question 1
An aircraft is flying trim stick-fixed at steady level flight with a speed of 80 m/s and at standard sea
level conditions, where the air density is 1.225 kg/m³. The ratio of the wings' surface area to the tail
plane's surface area is 10, the tail arm is 10 m and the wings' mean aerodynamic chord length is 2
m. The ratio of the tail plane's lift to the wings' lift is -0.01 at that condition. The rest of the known
data are given in the two tables at the end of the question. Justify any assumption that you make.
al Calculate the
Calculate the downwa
the tail plane angle of attack
[6 marks]
c) Find the elevator's deflection angle and the hinge moment coefficient. You may assume the tab's
deflection angle is zero.
Barkst
d) Calculate the c.g. margin H, of the aircraft, argue for the sign of dCм/dC, and whether the aircraft
is statically stable or not.
d) Cal
MCI MOC Vallato assu
margin H
KS
de/dCL
Смо
ho
h
nT
50
-0.05
2º
0.2
0.15
Lift curve slopes and hinge moment curve slopes
a
a1
I
az
a3
b₁
bz
b3
5.7 rad 1
4 rad
1.5 rad 1
1 rad
0.2 rad 1
-0.5 rad1
-0.02 rad-1
You may find the following expression useful
STIT
CM CMO + (h-ho)CL - VTC, Vr =
Swe
Ca₁a + a2n + a3ẞ
CH = b₁α + b₂+b3ẞ
a1
a
as (1-4)
de
da
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