The following specifications of an aircraft are given. Wing area: 17 m 2 Gross weight: 22700...
The following specifications of an aircraft are given.
Wing area: 17 m 2
Gross weight: 22700 N
Elevator control effectiveness: 0.04
C M,0 = 0.06
Slope of lift coefficient with respect to angle of attack: 0.08 deg
-1
Slope of moment coefficient with respect to angle of attack:
-0.0133 deg -1
Horizontal tail volume ratio: 0.34
Tail efficiency: 1
What is the elevator angle required to trim at 58 m/s? Provide
answer to 1 decimal place in units of degrees.
Homework Answers
Answer:
Given that:
Wing area: 17 m 2
Gross weight: 22700 N
Elevator control effectiveness: 0.04 = 
C M,0 = 0.06
we assume sea level condition.
So net pitching moment about c.g
eliwinding the qun(1) 
through to make in coefficient form
elerator deffection 
reawared to tnim 
Add Answer to:
The following specifications of an aircraft are given.
Wing area: 17 m 2
Gross weight: 22700...
Problem 2 (35%): Consider an airplane with the following characteristics: Weight, W Zero-lift moment coefficient, Go...
Problem 2 (35%): Consider an airplane with the following characteristics: Weight, W Zero-lift moment coefficient, Go 22700 N 0.06 ốc Moment coeff. Curve slope, Mg0.0133 deg -0.08 deg Lift curve slope, a Wing plan form area, S Tail volume ratio, VH 19 m2 - 0.34 Elevator control effectiveness, 0.04 deg! do Determine the elevator deflection required for this airplane to cruise at sea level with 50 m/sec and with 100 m/sec, respectively. (sea level density 1.225 kg/m')
3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S...
3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S 300 ft Mean aerodynamic chord of wing. -6f CG range: Max forward: 25% MAC, Max aft: 55% MAC Aerodynamic center of wing/body is at 25% MAC Tail lift slope, a-4.5 rad Elevator effectiveness, ae 2.0 rad Wing/body lift coefficient, CLwb 5.50ab Wing/body pitching moment coefficient about aerodynamic center, Cmac wb 0.1 · · b, or σε %α-0.3 radi Tail downwash angle, ε-0.3 Aircraft drag...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has ...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7m a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7mm a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
3. An airplane (weight 3,000 lb, wing span 35.5 ft, wing area 135 ft2, Oswald efficiency...
3. An airplane (weight 3,000 lb, wing span 35.5 ft, wing area 135 ft2, Oswald efficiency factor 0.85, zero-lift drag coefficient 0.05) flies with 90 kts at 8,000 ft. The asymmetrical airfoil has a lift-curve slope of 0.1 per degree, a zero-lift angle of attack of -3.0°, and a stall angle of attack of 15°. Assume a linear lift curve all the way to the stall. a. Calculate the density at the flight altitude in slug/ft? (6 points)
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
Rplane for which the starboard half-wing has the geometry give in Figure 1. For this wing, the li...
rplane for which the starboard half-wing has the geometry give in Figure 1. For this wing, the lift curve slope is CLaw 5.0 per radian and the aileron flap effectiveness parameter is 0.2 Estimate the aileron power Cl for the airplane. (This and the next problem refer back to the Topic 3 notes. You might also inthe supplemenial ro Aerodynamic Properties relevant.) 2.75 m I Cfc-0.25 1.34 m 3.4 m 4.8 m 5.2m Figure 1: Half-wing of an airplane for...
The lift force per unit span length on an aircraft wing is given by following function:...
The lift force per unit span length on an aircraft wing is given
by following function:
where L0 is the magnitude of the lift at the
centerline and b is the span length. Determine the Shear force(V),
Moment(M) and Displacement(w) as a function of x. The centerline of
the wing is located at x = 0 and the wing can be assumed to be
cantilevered at that point.
L(per unit span length)-L0(1-(2x/b
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N aspect ratio=7.0 span efficiency factor= 0.85 Parasit drag coefficient = 0.03 Each Jet Engine produces 4000on of Thrust at sea level airplane is taking off at full gross weight and the runway has paved surface. Given that the maximum lift coefficient during ground roll is 2.5 and the pair of wings are 2-m above the ground. At sea-level conditions, a) (10 pts) determine the...
Problem 2 (35%): Consider an airplane with the following characteristics: Weight, W Zero-lift moment coefficient, Go 22700 N 0.06 ốc Moment coeff. Curve slope, Mg0.0133 deg -0.08 deg Lift curve slope, a Wing plan form area, S Tail volume ratio, VH 19 m2 - 0.34 Elevator control effectiveness, 0.04 deg! do Determine the elevator deflection required for this airplane to cruise at sea level with 50 m/sec and with 100 m/sec, respectively. (sea level density 1.225 kg/m')
3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S 300 ft Mean aerodynamic chord of wing. -6f CG range: Max forward: 25% MAC, Max aft: 55% MAC Aerodynamic center of wing/body is at 25% MAC Tail lift slope, a-4.5 rad Elevator effectiveness, ae 2.0 rad Wing/body lift coefficient, CLwb 5.50ab Wing/body pitching moment coefficient about aerodynamic center, Cmac wb 0.1 · · b, or σε %α-0.3 radi Tail downwash angle, ε-0.3 Aircraft drag...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7m a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7mm a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
3. An airplane (weight 3,000 lb, wing span 35.5 ft, wing area 135 ft2, Oswald efficiency factor 0.85, zero-lift drag coefficient 0.05) flies with 90 kts at 8,000 ft. The asymmetrical airfoil has a lift-curve slope of 0.1 per degree, a zero-lift angle of attack of -3.0°, and a stall angle of attack of 15°. Assume a linear lift curve all the way to the stall. a. Calculate the density at the flight altitude in slug/ft? (6 points)
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
rplane for which the starboard half-wing has the geometry give in Figure 1. For this wing, the lift curve slope is CLaw 5.0 per radian and the aileron flap effectiveness parameter is 0.2 Estimate the aileron power Cl for the airplane. (This and the next problem refer back to the Topic 3 notes. You might also inthe supplemenial ro Aerodynamic Properties relevant.) 2.75 m I Cfc-0.25 1.34 m 3.4 m 4.8 m 5.2m Figure 1: Half-wing of an airplane for...
The lift force per unit span length on an aircraft wing is given
by following function:
where L0 is the magnitude of the lift at the
centerline and b is the span length. Determine the Shear force(V),
Moment(M) and Displacement(w) as a function of x. The centerline of
the wing is located at x = 0 and the wing can be assumed to be
cantilevered at that point.
L(per unit span length)-L0(1-(2x/b
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N aspect ratio=7.0 span efficiency factor= 0.85 Parasit drag coefficient = 0.03 Each Jet Engine produces 4000on of Thrust at sea level airplane is taking off at full gross weight and the runway has paved surface. Given that the maximum lift coefficient during ground roll is 2.5 and the pair of wings are 2-m above the ground. At sea-level conditions, a) (10 pts) determine the...
Most questions answered within 3 hours.
-
The random variable X is exponentially distributed, where X
represents the time it takes for a...
asked 3 minutes ago -
MATLAB
write a MATLAB function (1) output a third-order polynomial
function with the coefficients as the...
asked 10 minutes ago -
A z-score
communicates a raw score’s "relative standing"
under the normal curve in relation to:
asked 19 minutes ago -
An object is vibrating on a spring with the following equation
of motion:
?=(30 ??)cos((2?)/(160)?)
a)...
asked 18 minutes ago -
Vulcan Flyovers offers scenic overflights of Mount St. Helens,
the volcano in Washington State that explosively...
asked 21 minutes ago -
If organizations do not adapt fast enough and move incrementally
from the twentieth-century model to the...
asked 21 minutes ago -
A helium balloon with 2.5L of gas has a gauge pressure of 10,000
Pa. The balloon...
asked 26 minutes ago -
What is responsible for Jupiter's enormous magnetic field?
asked 41 minutes ago -
At the end of the year, a company offered to buy 5,000 units of
a product...
asked 42 minutes ago -
Implement C++ program for each of the following.
Let D = [-48, -14, -8, 0, 1,...
asked 1 hour ago -
Consider a labor market in which LD = 400 – 4W and LS = 250 +...
asked 1 hour ago -
Let’s say you are teaching a typically-developing young child
how to eat with a spoon. Describe...
asked 1 hour ago