The document summarizes the development and characteristics of several airfoil series developed by the National Advisory Committee for Aeronautics (NACA). It describes the early 4-digit and 5-digit series which used analytical equations to define airfoil shape based on camber and thickness. Later series like the 6-series used more advanced theoretical methods. The document provides details on naming conventions and equations used to define the geometry of airfoils within each series.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
What are the elements of aircraft performance?
How much thrust do you need?
How fast and how slow can you fly?
#WikiCourses
http://wikicourses.wikispaces.com/Topic+Performance+of+aerospace+vehicles
Nomenclature and classification of controls in an airplane (slide # 3-4).
Which are the aerodynamic forces acting on airplane (slide # 5).
Working principle of an airplane (slide # 6).
How an airplane flies (basic motions of an airplane) (slide # 7).
How controls play their roles in these motions (slide # 8-22).
Simulate a flight in Cessna Skyhawk (slide # 23-28).
References and Questions & answers (slide # 30).
For Video Lecture of this presentation: https://youtu.be/NAjezfbWh4Y
The topics covered in this session are, drag, categories of drag, drag polar equation and drag polar graph, drag polar derivation, induced drag coefficient.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
Airspeeds | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, Formulae and topic wise Solutions for the topic "Airspeeds" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
What are the elements of aircraft performance?
How much thrust do you need?
How fast and how slow can you fly?
#WikiCourses
http://wikicourses.wikispaces.com/Topic+Performance+of+aerospace+vehicles
Nomenclature and classification of controls in an airplane (slide # 3-4).
Which are the aerodynamic forces acting on airplane (slide # 5).
Working principle of an airplane (slide # 6).
How an airplane flies (basic motions of an airplane) (slide # 7).
How controls play their roles in these motions (slide # 8-22).
Simulate a flight in Cessna Skyhawk (slide # 23-28).
References and Questions & answers (slide # 30).
For Video Lecture of this presentation: https://youtu.be/NAjezfbWh4Y
The topics covered in this session are, drag, categories of drag, drag polar equation and drag polar graph, drag polar derivation, induced drag coefficient.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
Airspeeds | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, Formulae and topic wise Solutions for the topic "Airspeeds" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
Airfoil properties, shapes & structural dynamical features are described. Nomenclature or the classification types are presented along with the application.
Common methods for analysis of the structural dynamics on a wing or blade are presented along with the possible applications.
Design of Rear wing for high performance cars and Simulation using Computatio...IJTET Journal
The performance of a sports car is not only limited to its engine power but also to aerodynamic properties of the car. By decreasing the drag force it is possible to reduce the engine power required to achieve same top speed thus decreasing the fuel requirement. The stability of a sports car is considerably important at high speed. The provision of a rear wing increases the downforce thus reducing the rear axle lift and provides increased traction. In this study an optimum rear wing is designed for the high performance car so as to decrease drag and increase downforce. The CAD designed baseline model with or without rear wing is being analyzed in computational fluid dynamics software. The lift and drag coefficient are calculated for all the design thus an optimum rear wing is designed for the considered baseline model.
COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF AIRFOIL NACA0015IAEME Publication
In this chapter we choose standard airfoil NACA 0015. Which is symmetrical airfoil with a 15%thickness to chord ratio was analyzed on ANSYS FLUENT to determine the coefficient of lift,
coefficient of drag and graph of coefficient of lift vs. coefficient of drag. The 2-dimensional crosssectional view was considered. The wind velocity was taken as 17m/s which arecorresponding to232,940 Reynolds number. The airfoil, with an 8 in chord, was analyzed at 0, 5, 10 and 15 degrees.
Parameters viz. Coefficient of lift (Cl), Coefficient of drag (Cd) nd Cl/Cd are calculated and areplotted against different angle of attack.
Aerofoil Shapes plays a major role in understanding the principles of flight. This ppt gives basic knowledge about the aerofoil shapes and the variation of aerodynamic forces.
Electrical, Electronics and Computer Engineering,
Information Engineering and Technology,
Mechanical, Industrial and Manufacturing Engineering,
Automation and Mechatronics Engineering,
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Civil and Architecture Engineering,
Biotechnology and Bio Engineering,
Environmental Engineering,
Petroleum and Mining Engineering,
Marine and Agriculture engineering,
Aerospace Engineering.
Dynamic aerodynamic structural coupling numerical simulation on the flexible ...ijmech
Most biological flyers undergo orderly deformation in flight, and the deformations of wings lead to complex fluid-structure interactions. In this paper, an aerodynamic-structural coupling method of flapping wing is developed based on ANSYS to simulate the flapping of flexible wing.
Firstly, a three-dimensional model of the cicada’s wing is established. Then, numerical simulation method of unsteady flow field and structure calculation method of nonlinear large deformation are studied basing on Fluent module and Transient Structural module in ANSYS,
the examples are used to prove the validity of the method. Finally, Fluent module and Transient Structural module are connected through the System Coupling module to make a two-way fluidstructure Coupling computational framework. Comparing with the rigid wing of a cicada, the
coupling results of the flexible wing shows that the flexible deformation can increase the aerodynamic performances of flapping flight.
Model Attribute Check Company Auto PropertyCeline George
In Odoo, the multi-company feature allows you to manage multiple companies within a single Odoo database instance. Each company can have its own configurations while still sharing common resources such as products, customers, and suppliers.
June 3, 2024 Anti-Semitism Letter Sent to MIT President Kornbluth and MIT Cor...Levi Shapiro
Letter from the Congress of the United States regarding Anti-Semitism sent June 3rd to MIT President Sally Kornbluth, MIT Corp Chair, Mark Gorenberg
Dear Dr. Kornbluth and Mr. Gorenberg,
The US House of Representatives is deeply concerned by ongoing and pervasive acts of antisemitic
harassment and intimidation at the Massachusetts Institute of Technology (MIT). Failing to act decisively to ensure a safe learning environment for all students would be a grave dereliction of your responsibilities as President of MIT and Chair of the MIT Corporation.
This Congress will not stand idly by and allow an environment hostile to Jewish students to persist. The House believes that your institution is in violation of Title VI of the Civil Rights Act, and the inability or
unwillingness to rectify this violation through action requires accountability.
Postsecondary education is a unique opportunity for students to learn and have their ideas and beliefs challenged. However, universities receiving hundreds of millions of federal funds annually have denied
students that opportunity and have been hijacked to become venues for the promotion of terrorism, antisemitic harassment and intimidation, unlawful encampments, and in some cases, assaults and riots.
The House of Representatives will not countenance the use of federal funds to indoctrinate students into hateful, antisemitic, anti-American supporters of terrorism. Investigations into campus antisemitism by the Committee on Education and the Workforce and the Committee on Ways and Means have been expanded into a Congress-wide probe across all relevant jurisdictions to address this national crisis. The undersigned Committees will conduct oversight into the use of federal funds at MIT and its learning environment under authorities granted to each Committee.
• The Committee on Education and the Workforce has been investigating your institution since December 7, 2023. The Committee has broad jurisdiction over postsecondary education, including its compliance with Title VI of the Civil Rights Act, campus safety concerns over disruptions to the learning environment, and the awarding of federal student aid under the Higher Education Act.
• The Committee on Oversight and Accountability is investigating the sources of funding and other support flowing to groups espousing pro-Hamas propaganda and engaged in antisemitic harassment and intimidation of students. The Committee on Oversight and Accountability is the principal oversight committee of the US House of Representatives and has broad authority to investigate “any matter” at “any time” under House Rule X.
• The Committee on Ways and Means has been investigating several universities since November 15, 2023, when the Committee held a hearing entitled From Ivory Towers to Dark Corners: Investigating the Nexus Between Antisemitism, Tax-Exempt Universities, and Terror Financing. The Committee followed the hearing with letters to those institutions on January 10, 202
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Macroeconomics- Movie Location
This will be used as part of your Personal Professional Portfolio once graded.
Objective:
Prepare a presentation or a paper using research, basic comparative analysis, data organization and application of economic information. You will make an informed assessment of an economic climate outside of the United States to accomplish an entertainment industry objective.
1. The NACA airfoil series
The early NACA airfoil series, the 4-digit, 5-digit, and modified 4-/5-digit, were generated using
analytical equations that describe the camber (curvature) of the mean-line (geometric centerline) of
the airfoil section as well as the section's thickness distribution along the length of the airfoil. Later
families, including the 6-Series, are more complicated shapes derived using theoretical rather than
geometrical methods. Before the National Advisory Committee for Aeronautics (NACA) developed
these series, airfoil design was rather arbitrary with nothing to guide the designer except past
experience with known shapes and experimentation with modifications to those shapes.
This methodology began to change in the early 1930s with the publishing of a NACA report entitled
The Characteristics of 78 Related Airfoil Sections from Tests in the Variable Density Wind Tunnel.
In this landmark report, the authors noted that there were many similarities between the airfoils that
were most successful, and the two primary variables that affect those shapes are the slope of the
airfoil mean camber line and the thickness distribution above and below this line. They then
presented a series of equations incorporating these two variables that could be used to generate an
entire family of related airfoil shapes. As airfoil design became more sophisticated, this basic
approach was modified to include additional variables, but these two basic geometrical values
remained at the heart of all NACA airfoil series, as illustrated below.
NACA airfoil geometrical construction
NACA Four-Digit Series:
The first family of airfoils designed using this approach became known as the NACA Four-Digit
Series. The first digit specifies the maximum camber (m) in percentage of the chord (airfoil length),
the second indicates the position of the maximum camber (p) in tenths of chord, and the last two
numbers provide the maximum thickness (t) of the airfoil in percentage of chord. For example, the
NACA 2415 airfoil has a maximum thickness of 15% with a camber of 2% located 40% back from
the airfoil leading edge (or 0.4c). Utilizing these m, p, and t values, we can compute the coordinates
for an entire airfoil using the following relationships:
1. Pick values of x from 0 to the maximum chord c.
2. Compute the mean camber line coordinates by plugging the values of m and p into the
following equations for each of the x coordinates.
2. where
x = coordinates along the length of the airfoil, from 0 to c (which stands for chord, or length)
y = coordinates above and below the line extending along the length of the airfoil, these are
either yt for thickness coordinates or yc for camber coordinates
t = maximum airfoil thickness in tenths of chord (i.e. a 15% thick airfoil would be 0.15)
m = maximum camber in tenths of the chord
p =position of the maximum camber along the chord in tenths of chord
3. Calculate the thickness distribution above (+) and below (-) the mean line by plugging the
value of t into the following equation for each of the x coordinates.
4. Determine the final coordinates for the airfoil upper surface (xU, yU) and lower surface (xL, yL)
using the following relationships.
NACA Five-Digit Series:
The NACA Five-Digit Series uses the same thickness forms as the Four-Digit Series but the mean
camber line is defined differently and the naming convention is a bit more complex. The first digit,
when multiplied by 3/2, yields the design lift coefficient (cl) in tenths. The next two digits, when
divided by 2, give the position of the maximum camber (p) in tenths of chord. The final two digits
again indicate the maximum thickness (t) in percentage of chord. For example, the NACA 23012
has a maximum thickness of 12%, a design lift coefficient of 0.3, and a maximum camber located
15% back from the leading edge. The steps needed to calculate the coordinates of such an airfoil
are:
1. Pick values of x from 0 to the maximum chord c.
2. Compute the mean camber line coordinates for each x location using the following equations,
and since we know p, determine the values of m and k1 using the table shown below.
3. Calculate the thickness distribution using the same equation as the Four-Digit Series.
3. 4. Determine the final coordinates using the same equations as the Four-Digit Series.
Modified NACA Four- and Five-Digit Series:
The airfoil sections you mention for the B-58 bomber are members of the Four-Digit Series, but the
names are slightly different as these shapes have been modified. Let us consider the root section,
the NACA 0003.46-64.069, as an example. The basic shape is the 0003, a 3% thick airfoil with 0%
camber. This shape is a symmetrical airfoil that is identical above and below the mean camber line.
The first modification we will consider is the 0003-64. The first digit following the dash refers to the
roundedness of the nose. A value of 6 indicates that the nose radius is the same as the original
airfoil while a value of 0 indicates a sharp leading edge. Increasing this value specifies an
increasingly more rounded nose. The second digit determines the location of maximum thickness in
tenths of chord. The default location for all four- and five-digit airfoils is 30% back from the leading
edge. In this example, the location of maximum thickness has been moved back to 40% chord.
Finally, notice that the 0003.46-64.069 features two sets of digits preceeded by decimals. These
merely indicate slight adjustments to the maximum thickness and location thereof. Instead of being
3% thick, this airfoil is 3.46% thick. Instead of the maximum thickness being located at 40% chord,
the position on this airfoil is at 40.69% chord. To compute the coordinates for a modified airfoil
shape:
1. Pick values of x from 0 to the maximum chord c.
2. Compute the mean camber line coordinates using the same equations provided for the Four-
or Five-Digit Series as appropriate.
3. Calculate the thickness distribution above (+) and below (-) the mean line using these
equations. The values of the ax and dx coefficients are determined from the following table
(these are derived for a 20% thick airfoil).
4. Determine the "final" coordinates using the same equations as the Four-Digit Series.
5. As noted above, this procedure yields a 20% thick airfoil. To obtain the desired thickness,
simply scale the airfoil by multiplying the "final" y coordinates by [t / 0.2].
NACA 1-Series or 16-Series:
Unlike those airfoil families discussed so far, the 1-Series was developed based on airfoil theory
rather than on geometrical relationships. By the time these airfoils were designed during the late
1930s, many advances had been made in inverse airfoil design methods. The basic concept behind
this design approach is to specify the desired pressure distribution over the airfoil (this distribution
dictates the lift characteristics of the shape) and then derive the geometrical shape that produces
4. this pressure distribution. As a result, these airfoils were not generated using some set of analytical
expressions like the Four- or Five-Digit Series. The 1-Series airfoils are identified by five digits, as
exemplified by the NACA 16-212. The first digit, 1, indicates the series (this series was designed for
airfoils with regions of barely supersonic flow). The 6 specifies the location of minimum pressure in
tenths of chord, i.e. 60% back from the leading edge in this case. Following a dash, the first digit
indicates the design lift coefficient in tenths (0.2) and the final two digits specify the maximum
thickness in tenths of chord (12%). Since the 16-XXX airfoils are the only ones that have ever seen
much use, this family is often referred to as the 16-Series rather than as a subset of the 1-Series.
NACA 6-Series:
Although NACA experimented with approximate theoretical methods that produced the 2-Series
through the 5-Series, none of these approaches was found to accurately produce the desired airfoil
behavior. The 6-Series was derived using an improved theoretical method that, like the 1-Series,
relied on specifying the desired pressure distribution and employed advanced mathematics to
derive the required geometrical shape. The goal of this approach was to design airfoils that
maximized the region over which the airflow remains laminar. In so doing, the drag over a small
range of lift coefficients can be substantially reduced. The naming convention of the 6-Series is by
far the most confusing of any of the families discussed thus far, especially since many different
variations exist. One of the more common examples is the NACA 641-212, a=0.6.
In this example, 6 denotes the series and indicates that this family is designed for greater laminar
flow than the Four- or Five-Digit Series. The second digit, 4, is the location of the minimum pressure
in tenths of chord (0.4c). The subscript 1 indicates that low drag is maintained at lift coefficients 0.1
above and below the design lift coefficient (0.2) specified by the first digit after the dash in tenths.
The final two digits specify the thickness in percentage of chord, 12%. The fraction specified by
a=___ indicates the percentage of the airfoil chord over which the pressure distribution on the airfoil
is uniform, 60% chord in this case. If not specified, the quantity is assumed to be 1, or the
distribution is constant over the entire airfoil.
NACA 7-Series:
The 7-Series was a further attempt to maximize the regions of laminar flow over an airfoil
differentiating the locations of the minimum pressure on the upper and lower surfaces. An example
is the NACA 747A315. The 7 denotes the series, the 4 provides the location of the minimum
pressure on the upper surface in tenths of chord (40%), and the 7 provides the location of the
minimum pressure on the lower surface in tenths of chord (70%). The fourth character, a letter,
indicates the thickness distribution and mean line forms used. A series of standaradized forms
derived from earlier families are designated by different letters. Again, the fifth digit incidates the
design lift coefficient in tenths (0.3) and the final two integers are the airfoil thickness in perecentage
of chord (15%).
NACA 8-Series:
A final variation on the 6- and 7-Series methodology was the NACA 8-Series designed for flight at
supercritical speeds. Like the earlier airfoils, the goal was to maximize the extent of laminar flow on
the upper and lower surfaces independently. The naming convention is very similar to the 7-Series,
an example being the NACA 835A216. The 8 designates the series, 3 is the location of minimum
pressure on the upper surface in tenths of chord (0.3c), 5 is the location of minimum pressure on
the lower surface in tenths of chord (50%), the letter A distinguishes airfoils having different camber
or thickness forms, 2 denotes the design lift coefficient in tenths (0.2), and 16 provides the airfoil
thickness in percentage of chord (16%).
5. Summary:
Though we have introduced the primary airfoil families developed in the United States before the
advent of supersonic flight, we haven't said anything about their uses. So let's briefly explore the
advantages, disadvantages, and applications of each of these families.
Family Advantages Disadvantages Applications
4-Digit 1. Good stall characteristics 1. Low maximum lift coefficient 1. General aviation
2. Horizontal tails
2. Small center of pressure movement 2. Relatively high drag
across large speed range Symmetrical:
3. High pitching moment
3. Roughness has little effect 3. Supersonic jets
4. Helicopter blades
5. Shrouds
6. Missile/rocket fins
5-Digit 1. Higher maximum lift coefficient 1. Poor stall behavior 1. General aviation
2. Piston-powered bombers,
transports
2. Low pitching moment 2. Relatively high drag
3. Commuters
4. Business jets
3. Roughness has little effect
16-Series 1. Avoids low pressure peaks 1. Relatively low lift 1. Aircraft propellers
2. Ship propellers
2. Low drag at high speed
6-Series 1. High maximum lift coefficient 1. High drag outside of the 1. Piston-powered fighters
optimum range of operating 2. Business jets
conditions 3. Jet trainers
2. Very low drag over a small range of
4. Supersonic jets
operating conditions
2. High pitching moment
3. Optimized for high speed
3. Poor stall behavior
4. Very susceptible to roughness
7-Series 1. Very low drag over a small range of 1. Reduced maximum lift Seldom used
operating conditions coefficient
2. Low pitching moment 2. High drag outside of the
optimum range of operating
conditions
3. Poor stall behavior
4. Very susceptible to roughness
8-Series Unknown Unknown Very seldom used
Today, airfoil design has in many ways returned to an earlier time before the NACA families were
created. The computational resources available now allow the designer to quickly design and
optimize an airfoil specifically tailored to a particular application rather than making a selection from
an existing family.