The document provides information about a workshop on coroplast RC plane design being held by the Aero Modelling Club of NIT Kurukshetra. It includes specifications for acceptable RC plane models, such as a thrust-to-weight ratio below 0.75 and a maximum wingspan of 1.2 meters. Formulas are provided for calculating thrust, weight limits, and wing area based on the type of motor and propellers used. The document also covers topics to be discussed at the workshop, including wing design, aerofoil selection and nomenclature, tail design, relevant electronic components, and a sample circuit diagram.
Angle of attack | Flight Mechanics | GATE AerospaceAge of Aerospace
For Video Lecture of this presentation: https://youtu.be/GXKgH0guKqg
The topics covered in this session are, Definition: Angle of Attack (AOA), Insights,FoilSim AOA effect Visualization: Symmetric Airfoil, Cambered Airfoil, Flat Plate,Special Question: Why Airfoil?, Why not flat plate?
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
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).
Angle of attack | Flight Mechanics | GATE AerospaceAge of Aerospace
For Video Lecture of this presentation: https://youtu.be/GXKgH0guKqg
The topics covered in this session are, Definition: Angle of Attack (AOA), Insights,FoilSim AOA effect Visualization: Symmetric Airfoil, Cambered Airfoil, Flat Plate,Special Question: Why Airfoil?, Why not flat plate?
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
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).
This is the presentation on flow past an airfoil . An airfoil-shaped body moving through a fluid produces an aerodynamic force. The component of this force perpendicular to the direction of motion is called lift. The component parallel to the direction of motion is called drag. Subsonic flight airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces.
Longitudinal static stability of boeing 737 max 8Lahiru Dilshan
Recently there were two aircraft crashes, Lion Air and Ethiopian airline crash with 346 people with the flight crew. Ethiopian aircraft incident is currently under investigation and the final report will be published in near future and the Lion Air incident report was published.
Both these aircrafts were in the same type aircraft, Boeing 737 MAX 8, brand new aircraft that introduced very recently for commercial use. There several design modifications and several new systems were included for that aircraft by the designers and manufacturers.
Angle of Attack | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, and topic wise Solutions for the topic "Angle of Attack" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
This slide is prepared by me for the students studying in 1st Semester of Aircraft Maintenance Engineering. This is only the the introduction of Maintenance Practices involved in Aircraft Maintenance. Reference is taken from various aviation books and websites. Suggestions are welcome. Pls leave a like
PS- after downloading please don't change the name of author as you will be disregarding all the hard work done by me.
This is the presentation on flow past an airfoil . An airfoil-shaped body moving through a fluid produces an aerodynamic force. The component of this force perpendicular to the direction of motion is called lift. The component parallel to the direction of motion is called drag. Subsonic flight airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces.
Longitudinal static stability of boeing 737 max 8Lahiru Dilshan
Recently there were two aircraft crashes, Lion Air and Ethiopian airline crash with 346 people with the flight crew. Ethiopian aircraft incident is currently under investigation and the final report will be published in near future and the Lion Air incident report was published.
Both these aircrafts were in the same type aircraft, Boeing 737 MAX 8, brand new aircraft that introduced very recently for commercial use. There several design modifications and several new systems were included for that aircraft by the designers and manufacturers.
Angle of Attack | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, and topic wise Solutions for the topic "Angle of Attack" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
This slide is prepared by me for the students studying in 1st Semester of Aircraft Maintenance Engineering. This is only the the introduction of Maintenance Practices involved in Aircraft Maintenance. Reference is taken from various aviation books and websites. Suggestions are welcome. Pls leave a like
PS- after downloading please don't change the name of author as you will be disregarding all the hard work done by me.
• Created a conceptual aircraft that can use wing in ground effect to fly at low altitude to achieve fuel efficiency and high payload carrying capacity.
Fighter jet Swept back wing design and Analysis by using of Xflr5Mani5436
1.V-N DIAGRAM
2.Prepared an aircraft wing design for the proposed structure.
3.Selected geometry in the plane (wing area, aspect ratio, cords) and sweep, dihedral, twist angles.
4.Airfoil Aerodynamic characteristics
This was my final year project thesis, based on the results from NASA Langley Research Centre’s work on the PRANDTL-D project which was into minimizing the induced drag of a wing body along with elimination of adverse yaw.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
The flow velocity over airfoils increases over the convex surface resulting in lower average pressure on the 'suction' side of the airfoil compared with the concave or 'pressure' side of the airfoil.
Meanwhile, viscous friction between the air and the airfoil surface slows the airflow to some extent next to the surface.
Airflow over an airfoil produces a distribution of forces over the airfoil surface.
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.
Output equation of Induction motor; Main dimensions; Separation of D and L; Choice of Average flux density; length of air gap; Design of Stator core; Rules for selecting rotor slots of squirrel cage machines; Design of rotor bars and slots; Design of end rings; Design of wound rotor; Magnetic leakage calculations; Leakage reactance of polyphase machines; Magnetizing current; Short circuit current; Operating characteristics; Losses and Efficiency.
Dive into the innovative world of smart garages with our insightful presentation, "Exploring the Future of Smart Garages." This comprehensive guide covers the latest advancements in garage technology, including automated systems, smart security features, energy efficiency solutions, and seamless integration with smart home ecosystems. Learn how these technologies are transforming traditional garages into high-tech, efficient spaces that enhance convenience, safety, and sustainability.
Ideal for homeowners, tech enthusiasts, and industry professionals, this presentation provides valuable insights into the trends, benefits, and future developments in smart garage technology. Stay ahead of the curve with our expert analysis and practical tips on implementing smart garage solutions.
Hello everyone! I am thrilled to present my latest portfolio on LinkedIn, marking the culmination of my architectural journey thus far. Over the span of five years, I've been fortunate to acquire a wealth of knowledge under the guidance of esteemed professors and industry mentors. From rigorous academic pursuits to practical engagements, each experience has contributed to my growth and refinement as an architecture student. This portfolio not only showcases my projects but also underscores my attention to detail and to innovative architecture as a profession.
Between Filth and Fortune- Urban Cattle Foraging Realities by Devi S Nair, An...Mansi Shah
This study examines cattle rearing in urban and rural settings, focusing on milk production and consumption. By exploring a case in Ahmedabad, it highlights the challenges and processes in dairy farming across different environments, emphasising the need for sustainable practices and the essential role of milk in daily consumption.
5. Model Specification:
1. T/W <=0.75 without payload (If excess thrust is measured, it will be neutralized
by adding weight below the aircraft at center of gravity)
2. Propeller diameter should not be greater than 13 inches.
3. Total wingspan should be a maximum of 1.2 m.
4. Only electrical motors are allowed. The use of IC engines or any other means
of providing thrust is prohibited.
6. Thrust and weight calculation
maximum thrust:
BLDC A2212 1400kv with 10*4 propellors = 480gm
BLDC A2212 1000kv with 10*4 propellors = 800gm
BLDC A2212 1000kv with 8*4 propellors = 650gm
Thrust/Weight |max = T/W <= 75% = 0.75
Maximum Weight of plane:
weight of plane should be less than T/0.75
BLDC A2212 1400kv with 10*4 propellors = 640gm
BLDC A2212 1000kv with 10*4 propellors = 1066gm
BLDC A2212 1000kv with 8*4 propellors = 866 gm
#if we are making plane using any of these BLDC Motors and propellor
10. ● The leading edge is the point at the front
of the aerofoil that has maximum
curvature.
● The trailing edge is defined similarly as the
point of maximum curvature at the rear of
the aerofoil.
● The chord line is a straight line connecting
the leading and trailing edges of the
aerofoil.
● The chord length, or simply chord, is the
length of the chord line and is the
characteristic dimension of the aerofoil
section.
11. ● The mean camber line is the locus of points
midway between the upper and lower
surfaces. Its exact shape depends on how
the thickness is defined;
● The thickness of an aerofoil varies along the
chord. It may be measured in either of two
ways:
○ Thickness measured perpendicular to the
camber line This is sometimes described
as the "American convention“.
○ Thickness measured perpendicular to the
chord line. This is sometimes described as
the "British convention".
● Most linear dimensions are measured as
a percentage of chord length.
12. Types of Airfoils
There are three types of airfoils:
1. Symmetric Airfoils:
2. Positive cambered
3. Negative cambered
19. Dihedral angle (Γ)
● Used to increase lateral
stability of an aircraft at the
cost of lift, adds complexity to
construction.
Why
??
20. Aspect ratio (AR)
● High aspect ratio decreases rolling sensitivity but make airplane fly in
much efficient manner.
21. Wing Calculation
1. According to our problem statement,out wing span should not be greater
than 120cm.
2. Depending upon our requirement we determine the following wing
parameters -
a.Aspect Ratio
bombers = 4 to 5
aerobatic plane = 5 to 6
Normal powered flight = 5 to 7
sail planes = 8 to 16
gliders = > 16
b.Taper Ratio -For wing we take it 1.
c.Sweep angle -0 degrees
d.Dihedral angle -we can make it 2-5 degrees to increase stability.
e.Airfoil.
22. Let ARW
= 6
wing span = b = 120cm
s = wing area
wing area = s = 120*120/6 = 2400 cm sq.
Assuming our wing to be rectangular.
Taper ratio (λ) = Root chord / tip chord = 1
=> root chord = tip chord = chord = c
s = wing area = span * chord
chord = wing area/span = s/c = 20cm.
23. Choosing an airfoil
● Most aero modellers like us choose their airfoils from
already designed set of airfoils like NACA or Eppler
aerofoils etc.
● Try to figure out what sort of airplane you need**
:
• Slow flying airplane like sailplane or glider (look for high Cl
/Cd
ratio)
• Aerobatic stunt plane (symmetric aerofoils)
• High speed race aircraft (very low Cd
, thin and semi symmetric aerofoils)
**above points are just for very rough idea, for final selection of airfoil many parameters are considered.
24. NACA Aerofoils
NACA 4 digit Aerofoils
• This NACA aerofoil series is controlled by 4 digits e.g. NACA 2412.
It stands for National Advisory Committee for Aeronautics
• These designate the camber, position of the maximum camber and
thickness of an aerofoil.
• If an aerofoil number is NACA MPXX
e.g. NACA 2412
• Here M is the maximum camber as % of chord length. M=2 so the camber
is 2% of the chord
• P is the position of the maximum camber as tens of % of chord length. P=4
so the maximum camber is at 40% of the chord.
• XX is the thickness as % of chord length. XX=12 so the thickness is 12% of
the chord.
37. Brushless
Motor:
● KV is motor velocity constant
RPM per volt (kilovolt)
● RPM of motor = KV * voltage
● Thrust- Depends on propeller,
Battery, ESC and power of motor
44. ● Battery voltage
● 1S = 3.7V
● 2S battery pack means that there are 2 cells in Series.
● So a two-cell (2S) pack is 7.4V, a three-cell (3S) pack is 11.1V
● CAPACITY
● 1000mAh = 1 Amp Hour (1Ah)
● Discharge Rating ("C" Rating)
● 50C = 50 x Capacity (in Amps)
● Calculating the C-Rating of our example battery: 50 x 5 = 250A
● CHARGING
● The safest charge rate for most LiPo batteries is 1C, or 1 x capacity of battery in Amps.
● Watts = Voltage x Amperage
● A LiPo cell should NEVER be discharged below 3.0V