Annotated_Bib_AVIA305
.docx
keyboard_arrow_up
School
Liberty University *
*We aren’t endorsed by this school
Course
305
Subject
Mechanical Engineering
Date
Jul 3, 2024
Type
docx
Pages
2
Uploaded by GeneralMoonPrairieDog29
1
AVIA305
Sec D02
Brian Cortez
Annotated Bibliography
J. Domino, Z. Czyż and R. Bąbel, "Aerodynamic Load Measurements on the Example of Diamond DA42 Model Aircraft," 2023 IEEE 10th International Workshop on Metrology for AeroSpace (MetroAeroSpace), Milan, Italy, 2023, pp. 704-708, doi: 10.1109/MetroAeroSpace57412.2023.10189976.
This paper deals with the design, preparation and manufacture of a model aircraft for wind tunnel
testing. The project was based on the twin-engine aircraft, Diamond DA42. Based on technical drawings, a model of thie aircraft was made in a CAD environment and subsequently 3D printed using FDM technology. The dimensions of the model were adjusted to the size of the wind tunnel
measurement space. The model omitted aircraft structural elements such as propellers and landing gear. The entire model was then mounted on a 6-component force balance. For the final version of the model, wind tunnel tests were conducted. The work was supplemented with a description of the test stand and several tests were carried out. The test results provide useful insights into the aerodynamic design and characteristics of the aircraft.
Szczepaniak, R., Pożoga, Ł., Stabryn, S., & Stryczniewicz, W. (2016). FCFD analysis of the influence of winglets on the aerodynamic performance of the DA42 diamond aircraft.
Journal of KONES. Powertrain and Transport
,
23
(1), 361–368. https://doi.org/10.5604/12314005.1213551
This journal presents the application of CAE software for an investigation of the aerodynamic performance of a small two-engine aircraft, the DA42. In the study, Computational Fluid Dynamics was applied in order to determine the influence of winglets on the aerodynamic performance of the DA42 Diamond aircraft. The simulations were performed with the use of SolidWorks Flow Simulation software. In order to evaluate the influence of the winglets on the lift and drag force, two configurations of the selected aircraft were modelled: with and without
2
AVIA305
Sec D02
Brian Cortez
winglets. The results of the simulations confirmed a reduction of induced drag caused by wingtips vortices dissipation introduced by winglets. The maximum reduction of the induced drag was achieved at high angles of attack. This research is pivotal to a well structured argument on the reasoning for the design of the subject aircraft. Collins, P. (2019, October 9).
Flight test: Diamond Aircraft DA42 - sparkling performer
. Flight Global. https://www.flightglobal.com/flight-test-diamond-aircraft-da42-sparkling-
performer/55396.article
This article from flight global gives an overview on the key features of the Diamond DA42 that made it appealing to the masses when it first released. The article goes on to talk about the development, configuration, and operational ability of the DA42. It is particularly useful because
it was published at the time of release of the aircraft, giving it timely relevance. Diamond. (n.d.-a). Da 42 AFM 7.01.05-e revision 9. http://support.diamond-air.at/fileadmin/uploads/files/after_sales_support/
DA42_Twin_Star/Airplane_Flight_Manual/Basic_Manual/70105e-Rev9-complete.pdf
This is the 9
th
revision of the AFM for the Diamond DA42 NG. It contains everything from performance calculations, weight and balance, systems, operating procedures and limitations. It is a comprehensive overview into the inner workings of this aircraft and is an invaluable resource
in calculating aerodynamic performance metrics to add sustenance to my essay.
Your preview ends here
Eager to read complete document? Join bartleby learn and gain access to the full version
- Access to all documents
- Unlimited textbook solutions
- 24/7 expert homework help
Related Questions
I need help with my MATLAB code. There is an error in the following code. The error says my orbitaldynamics function must return a column vector. Can you help me fix it?
mu_earth = 398600.4418; % Earth's gravitational parameter (km^3/s^2)
R_earth = 6378.137; % Earth's radius (km)
C_d = 0.3; % Drag coefficient (assumed)
A = 0.023; % Cross-sectional area of ISS (km^2)
m = 420000; % Mass of ISS (kg)
% Initial conditions: position and velocity (ISS state vector)
% ISS initial state vector (km and km/s) - sample data
state_ISS =[-2.1195e+03, 3.9866e+03, 5.0692e+03, -5.3489, -5.1772, 1.8324];
% Time span for 10 revolutions
T_orbit = 2 * pi * sqrt((norm(state_ISS(1:3))^3) / mu_earth);
time_span = [0, 10 * T_orbit];
% Step 3: Numerical integration using ODE solver
options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12);
[t, state] = ode45(@orbitalDynamics, time_span, state_ISS, options);
% Step 4: Plot the results
figure;
plot3(state(:, 1), state(:, 2), state(:, 3));
xlabel('X…
arrow_forward
Problem 3: Aerodynamics
Consider a UPS delivery van.
Part A
Is this vehicle streamlined? (yes/no)
Part B
Which drag force will be dominant, friction drag or pressure drag, and why? (<25 words)
Part C
By what percentage does the speed increase from 55 to 75 mph? [%]
Centr
Part D
By what percentage does the drag force increase from 55 to 75 mph? Assume air as given by the
ICAO standard atmosphere at an elevation of 5,000 ft. Assume the aerodynamics of the truck can
be predicted by a disk with diameter 9.0 ft.
arrow_forward
-Sear x
dynamics systems questions 1[1 x
Week 15-Mechanical (Tutorials x +
| C:/Users/40332698/AppData/Local/Packages/microsoft
windowscommunicationsapps_8wekyb3d8bbwe/LocalState/Files/SO/145/Attachments/dynamics%...
Q
- +3
Page view A Read aloud Add textDraw
Highlight
V
Erase
ate the
3/104 The car is moving with a speed vo= 105 km/h up
the 6-percent grade, and the driver applies the
brakes at point A, causing all wheels to skid. The
coefficient of kinetic friction for the rain-slicked
bogne-road is = 0.60. Determine the stopping distance
ed ISAB. Repeat your calculations for the case when the
booga car is moving downhill from B to A.
the case
-8.0
ai noilsi' SA noitisoq de JDT mot gainnige ge
= $1 bacilyon
A
S
→ vo
6
search
10.
$
R
F
T
V
25
%
5
T
G
B
O Ai
O
A
6
Y
H
N
&
7
U
J
Fa
★
8
M
1
K
FO
100
9
prt sc
F10
O
L
)
O
home
P
;
B
A
end
F12
{
?
+
insert
}
1
To
6
9°C Cloudy DENG
^
7
arrow_forward
\
arrow_forward
What is the link between gust spectrum and force spectrum, and
what is the link between force spectrum and response
spectrum? Please give the related formulas.
arrow_forward
>
| E9
docs.google.com/form
تبديل الحساب
Questions
7 نقاط
Q1/ The power of 6-blade flat blade turbine agitator in a tank is a function of diameter of impeller, number of
rotations of the impeller per unit time, viscosity and density of liquid. From a dimensional analysis, obtain a
relation between the power and the four variables.
3.
صفحة 2 من
arrow_forward
The following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image.
Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed
Aircraft lift-off speed
155 knots
Max take-off gross weight
220 tonnes
Wing planform area (S)
358 m
Wing CL (t/o flaps deployed, a = 0)
1.1
Wing span
53.18 m
Oswald efficiency factor, e
0.7
KGE = CD(IGE) / Co(OGE)
0.4
Co sum (fuselage, wing, tailplane and nacelle)
0.015
Co for undercarriage
0.021
Co for flaps at taking-off setting
0.0073
Coefficient of rolling friction, u
0.02
Engine thrust (assumed constant)
310 kN per engine
It may be assumed that 1knot = 0.51444 m/s
It may be assumed that 1knot = 0.51444 m/s
arrow_forward
Question 5
a) A 1:20 scale model of a surface vessel is used to test the influence of a proposed design on
the wave drag. A wave drag of 6.2 lb is measured at a model speed of 8.0 ft/sec. What speed
does this correspond to on the prototype, and what wave drag is predicted for the prototype?
Neglect viscous effects, and assume the same fluid for model and prototype.
arrow_forward
(Review experimental scaling) A lightweight parachute is being designed for
military use. Its diameter D is 20 ft and the total weight W of the falling payload,
parachute, and equipment is 190 lb. The design terminal settling speed V. (or
terminal velocity) of the parachute at this weight is 16 ft/s. A one-twelfth scale
model of the parachute is tested in a wind tunnel. The wind tunnel temperature and
pressure are the same as those of the prototype, which is 70 °F and standard
atmospheric pressure.
a) Calculate the drag coefficient of the prototype. (Hint: At terminal velocity,
speed is constant so weight is in equilibrium with aerodynamic drag.)
b) At what speed should the wind tunnel be run in order to achieve dynamic
similarity?
c) Find the aerodynamic drag force of the model parachute in the wind tunnel
in pounds.
Payload
arrow_forward
The drag force of a new sports car is to be predicted at a speed of 65 mi/h at an air temperature of 25 C. Automotive engineers build a 0.333333333333333 scale model of the car to test in a wind tunnel. The temperature of the wind tunnel air is also 25 C. Determine how fast (in mi/h) the engineers should run the wind tunnel to achieve similarity between the model and the prototype.
arrow_forward
What is the major difference between spacecraft orbital mechanics and spacecraft attitude
dynamics? (support your answer with examples and mathematical formulas)
Please don't copy from internet or chegg
NEED DETAILED AND STEP BY STEP ANSWER
Short or incomplete answer = thumbs down
arrow_forward
i need the answer quickly
arrow_forward
Question 3
The aerodynamic derivative X, may be determined from the following expression:
X
-pU SCD
%3D
where p is the air density, S is the wing area, U is the airspeed, and Cp is the drag coefficient.
Consider an aircraft of weight 68 kN and wing area 43 m?, flying straight and level under international
standard atmosphere (ISA) conditions, where p 1.018 kg/m, at an airspeed of 155 m/s. The aircraft
%3D
has a drag polar
Cp = 0.011 +
where Ci is the lift coefficient.
Calculate the value of X, at this flight condition. Give your answer in units of Ns/m.
arrow_forward
Mechanical EngineeringFluid mechanics
arrow_forward
Give me right solution with clear calculations
arrow_forward
ai the first 3 are a part
arrow_forward
A model of a golf ball is to be studied to
determine the effects of the dimples. A
sphere 10 times larger in diameter than an
actual golf ball is used in the wind tunnel
study. What speed should be selected for
the model to simulate a prototype speed of
50 m/s?
arrow_forward
Discuss how you would create the solid model of the given objects.
arrow_forward
5.8 Calculate the drag coefficient and drag force on a cylindrical shape flag post of the
ship having diameter 60 mm and 3m long exposed to wind velocity of 10m/s. The
density and the kinematic viscosity of air are 1.2 kg/m and 1.6x 10m'/s respectively.
[Ans: 10.8 N]
arrow_forward
How do you get this answer?
arrow_forward
2. Outcomes 1 and 4.Show and explain all work. You must show and explain all work. The drag
on the hull of a sailboat can be shown to depend on the boat velocity V, the water density p and viscosity
μ, the length of the hull f, and the acceleration due to gravity g.
JIH
Class 40 Racing Yacht.
30
arrow_forward
Step by step work starting with the formula.
arrow_forward
1. (a)
The motion of a floating vessel through the surrounding fluid results in
a drag force D which is thought to depend upon the vessel's speed v,
its length I, the density p and dynamic viscosity μ of the fluid and the
acceleration due to gravity g.
Show that:-
D = pv²1² (1)
(b)
In order to predict the drag on a full scale 50m long ship traveling at
7m/s in sea water at 5°C of density 1027.7225 kg/m³ and viscosity
1.62 x 103 Pa.s, a model 3m long is tested in a liquid of density
805 kg/m³.
What speed does the model need to be tested at and what is the
required viscosity of the liquid?
arrow_forward
Define the following:
1. Flight path diagrams
2. Wreckage or scene diagrams
3. Technical diagrams
4. Flight depictions
arrow_forward
The one-dimensional motion experiment carried out in the air table experimental setup. the results are indicated in the table below.
(1.jpg)
a) Calculate the theoretical speed value belonging to the motion.
b) Calculate the experimental velocity value by drawing the graph with the table values above.
c) Calculate the percentage error by comparing the obtained theoretical and experimental values.
arrow_forward
Do 1st 3
arrow_forward
The Reynold's number of a sphere falling in air is 1E6. If the sphere's radius is 1ft, what is its velocity? Density of air is 0.00234 slug/ft³ and viscosity of air is 3.8E-7 lbf-sec/ft²A. 2.5 ft/sB. 5.1 ft/sC. 40.6 ft/sD. 81.2 ft/s
arrow_forward
A tanker 300 m long is to be tested by a 1: 50 scale model. If the ship is to travel at 46
km/h, at what speed must the model be towed to obtain dynamic similarity (neglecting friction)
with its prototype?
arrow_forward
You are given a drone with an average chord length of 8 in., a wingspan of 2.5 ft, and a weight of 300 g. Based on figure 2, would it stay in the air at a speed of 5 m/s? (Assume ρ=1.225 kg/m3 and Nu=1.516*10-5 m^2/s)
arrow_forward
Can you please attempt question 1 please.
arrow_forward
SEE MORE QUESTIONS
Recommended textbooks for you
Elements Of Electromagnetics
Mechanical Engineering
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Oxford University Press
Mechanics of Materials (10th Edition)
Mechanical Engineering
ISBN:9780134319650
Author:Russell C. Hibbeler
Publisher:PEARSON
Thermodynamics: An Engineering Approach
Mechanical Engineering
ISBN:9781259822674
Author:Yunus A. Cengel Dr., Michael A. Boles
Publisher:McGraw-Hill Education
Control Systems Engineering
Mechanical Engineering
ISBN:9781118170519
Author:Norman S. Nise
Publisher:WILEY
Mechanics of Materials (MindTap Course List)
Mechanical Engineering
ISBN:9781337093347
Author:Barry J. Goodno, James M. Gere
Publisher:Cengage Learning
Engineering Mechanics: Statics
Mechanical Engineering
ISBN:9781118807330
Author:James L. Meriam, L. G. Kraige, J. N. Bolton
Publisher:WILEY
Related Questions
- I need help with my MATLAB code. There is an error in the following code. The error says my orbitaldynamics function must return a column vector. Can you help me fix it? mu_earth = 398600.4418; % Earth's gravitational parameter (km^3/s^2) R_earth = 6378.137; % Earth's radius (km) C_d = 0.3; % Drag coefficient (assumed) A = 0.023; % Cross-sectional area of ISS (km^2) m = 420000; % Mass of ISS (kg) % Initial conditions: position and velocity (ISS state vector) % ISS initial state vector (km and km/s) - sample data state_ISS =[-2.1195e+03, 3.9866e+03, 5.0692e+03, -5.3489, -5.1772, 1.8324]; % Time span for 10 revolutions T_orbit = 2 * pi * sqrt((norm(state_ISS(1:3))^3) / mu_earth); time_span = [0, 10 * T_orbit]; % Step 3: Numerical integration using ODE solver options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12); [t, state] = ode45(@orbitalDynamics, time_span, state_ISS, options); % Step 4: Plot the results figure; plot3(state(:, 1), state(:, 2), state(:, 3)); xlabel('X…arrow_forwardProblem 3: Aerodynamics Consider a UPS delivery van. Part A Is this vehicle streamlined? (yes/no) Part B Which drag force will be dominant, friction drag or pressure drag, and why? (<25 words) Part C By what percentage does the speed increase from 55 to 75 mph? [%] Centr Part D By what percentage does the drag force increase from 55 to 75 mph? Assume air as given by the ICAO standard atmosphere at an elevation of 5,000 ft. Assume the aerodynamics of the truck can be predicted by a disk with diameter 9.0 ft.arrow_forward-Sear x dynamics systems questions 1[1 x Week 15-Mechanical (Tutorials x + | C:/Users/40332698/AppData/Local/Packages/microsoft windowscommunicationsapps_8wekyb3d8bbwe/LocalState/Files/SO/145/Attachments/dynamics%... Q - +3 Page view A Read aloud Add textDraw Highlight V Erase ate the 3/104 The car is moving with a speed vo= 105 km/h up the 6-percent grade, and the driver applies the brakes at point A, causing all wheels to skid. The coefficient of kinetic friction for the rain-slicked bogne-road is = 0.60. Determine the stopping distance ed ISAB. Repeat your calculations for the case when the booga car is moving downhill from B to A. the case -8.0 ai noilsi' SA noitisoq de JDT mot gainnige ge = $1 bacilyon A S → vo 6 search 10. $ R F T V 25 % 5 T G B O Ai O A 6 Y H N & 7 U J Fa ★ 8 M 1 K FO 100 9 prt sc F10 O L ) O home P ; B A end F12 { ? + insert } 1 To 6 9°C Cloudy DENG ^ 7arrow_forward
- \arrow_forwardWhat is the link between gust spectrum and force spectrum, and what is the link between force spectrum and response spectrum? Please give the related formulas.arrow_forward> | E9 docs.google.com/form تبديل الحساب Questions 7 نقاط Q1/ The power of 6-blade flat blade turbine agitator in a tank is a function of diameter of impeller, number of rotations of the impeller per unit time, viscosity and density of liquid. From a dimensional analysis, obtain a relation between the power and the four variables. 3. صفحة 2 منarrow_forward
- The following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image. Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed Aircraft lift-off speed 155 knots Max take-off gross weight 220 tonnes Wing planform area (S) 358 m Wing CL (t/o flaps deployed, a = 0) 1.1 Wing span 53.18 m Oswald efficiency factor, e 0.7 KGE = CD(IGE) / Co(OGE) 0.4 Co sum (fuselage, wing, tailplane and nacelle) 0.015 Co for undercarriage 0.021 Co for flaps at taking-off setting 0.0073 Coefficient of rolling friction, u 0.02 Engine thrust (assumed constant) 310 kN per engine It may be assumed that 1knot = 0.51444 m/s It may be assumed that 1knot = 0.51444 m/sarrow_forwardQuestion 5 a) A 1:20 scale model of a surface vessel is used to test the influence of a proposed design on the wave drag. A wave drag of 6.2 lb is measured at a model speed of 8.0 ft/sec. What speed does this correspond to on the prototype, and what wave drag is predicted for the prototype? Neglect viscous effects, and assume the same fluid for model and prototype.arrow_forward(Review experimental scaling) A lightweight parachute is being designed for military use. Its diameter D is 20 ft and the total weight W of the falling payload, parachute, and equipment is 190 lb. The design terminal settling speed V. (or terminal velocity) of the parachute at this weight is 16 ft/s. A one-twelfth scale model of the parachute is tested in a wind tunnel. The wind tunnel temperature and pressure are the same as those of the prototype, which is 70 °F and standard atmospheric pressure. a) Calculate the drag coefficient of the prototype. (Hint: At terminal velocity, speed is constant so weight is in equilibrium with aerodynamic drag.) b) At what speed should the wind tunnel be run in order to achieve dynamic similarity? c) Find the aerodynamic drag force of the model parachute in the wind tunnel in pounds. Payloadarrow_forward
- The drag force of a new sports car is to be predicted at a speed of 65 mi/h at an air temperature of 25 C. Automotive engineers build a 0.333333333333333 scale model of the car to test in a wind tunnel. The temperature of the wind tunnel air is also 25 C. Determine how fast (in mi/h) the engineers should run the wind tunnel to achieve similarity between the model and the prototype.arrow_forwardWhat is the major difference between spacecraft orbital mechanics and spacecraft attitude dynamics? (support your answer with examples and mathematical formulas) Please don't copy from internet or chegg NEED DETAILED AND STEP BY STEP ANSWER Short or incomplete answer = thumbs downarrow_forwardi need the answer quicklyarrow_forward
arrow_back_ios
SEE MORE QUESTIONS
arrow_forward_ios
Recommended textbooks for you
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY
Elements Of Electromagnetics
Mechanical Engineering
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Oxford University Press
Mechanics of Materials (10th Edition)
Mechanical Engineering
ISBN:9780134319650
Author:Russell C. Hibbeler
Publisher:PEARSON
Thermodynamics: An Engineering Approach
Mechanical Engineering
ISBN:9781259822674
Author:Yunus A. Cengel Dr., Michael A. Boles
Publisher:McGraw-Hill Education
Control Systems Engineering
Mechanical Engineering
ISBN:9781118170519
Author:Norman S. Nise
Publisher:WILEY
Mechanics of Materials (MindTap Course List)
Mechanical Engineering
ISBN:9781337093347
Author:Barry J. Goodno, James M. Gere
Publisher:Cengage Learning
Engineering Mechanics: Statics
Mechanical Engineering
ISBN:9781118807330
Author:James L. Meriam, L. G. Kraige, J. N. Bolton
Publisher:WILEY