High Speed Aero Dynamics | EveryEng

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Self-paced Beginner

High Speed Aero Dynamics

4(1581)

16 enrolled

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FREE

2336 min

Anytime

English

863 views

Team EveryEngMechanical Engineering

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Foundational Learning
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Why enroll

Participants join the High Speed Aerodynamics course to understand how aircraft and spacecraft behave at very high speeds. It helps them learn important concepts like shock waves, compressible flow, and supersonic flight. The course also builds practical knowledge useful for careers in aerospace engineering and aircraft design. By learning these advanced aerodynamics principles, participants can enhance their skills and explore opportunities in the aviation and space industries.

Your instructor

Team EveryEng

Engineer

Mechanical Engineering

22+ yrs experience·India

Is this course for you?

You should take this if

You work in Aerospace or Automotive
You're a Mechanical Engineering professional
You prefer self-paced learning you can revisit

You should skip if

You need a different specialisation outside Mechanical Engineering
You need live interaction with an instructor

Course details

The High Speed Aerodynamics course introduces learners to the exciting field of aerodynamics involved in high-velocity flight. It focuses on how air behaves around aircraft and spacecraft when they travel at very high speeds. Participants will study key concepts such as compressible flow, shock waves, and supersonic and hypersonic flight conditions. The course explains how aerodynamic forces change as speed increases beyond the speed of sound. Students will also learn about drag, lift, and thermal effects experienced during high-speed travel. Practical examples from modern aircraft and space vehicles help make the concepts easier to understand. The course highlights the challenges engineers face when designing high-speed vehicles. Participants will explore simulation techniques and real engineering applications. By the end of the course, learners will gain a strong understanding of the principles behind high-speed flight. This knowledge is valuable for careers in aerospace engineering, research, and advanced aircraft design.

Source: nptelhrd (YouTube Channel)
High Speed Aero Dynamics by Dr. K.P. Sinhamahapatra, Department of Aerospace Engineering, IITKharagpur.

Course suitable for

Key topics covered

Understand high-speed aerodynamic phenomena
Analyze and predict aerodynamic behavior
Design and optimize high-speed vehicles
Apply advanced concepts to real-world problems
Develop expertise in aerodynamics and aerospace engineering

Course content

The course is readily available, allowing learners to start and complete it at their own pace.

40 lectures38 hr 56 min

Introduction and Review of Thermodynamics
58 min
Review of Thermodynamics (Contd.)
59 min
Review of Thermodynamics (Contd.)
58 min
Review of Thermodynamics (Contd.)
104 min
One-dimensional gas dynamics
56 min
One-dimensional gas dynamics
61 min
One-dimensional gas dynamics (Contd.)
56 min
One-dimensional gas dynamics (Contd.)
56 min
One-dimensional waves (Contd.)
59 min
One-dimensional waves (Contd.)
53 min
Waves and Supersonic Flow
60 min
Waves and Supersonic Flow (Contd.)
59 min
Waves and Supersonic Flow (Contd.)
61 min
Waves and Supersonic Flow (Contd.)
53 min
Shock Expansion Theory
60 min
Flow through ducts and channels
60 min
Flow in ducts
59 min
Flow in ducts (Contd.)
57 min
Adiabatic Flow in ducts with friction
57 min
Adiabatic flow in ducts with friction (Contd.)
51 min
Isothermal flow in ducts with friction
53 min
Flow in uniform duct with heating
55 min
Multi - dimensional flow problems
56 min
Multi - dimensional flow problems (Contd.)
58 min
Linearized flow problems
60 min
Linearized flow problems (Contd.)
58 min
Linearized flow problems ( Contd.)
56 min
Linearized flow problems (Contd.)
59 min
Linearized flow problems ( Contd.)
58 min
Linearized flow problems ( Contd.)
55 min
Linearized flow problems ( Contd.)
58 min
Linearized Problems - Forces on Slender Bodies
61 min
Linearized Problems - Forces on Slender Bodies (Contd.)
55 min
Similarity Rules for High Speed Flows
58 min
Similarity Rules for High Speed Flows (Contd.)
58 min
Similarity Rules for High Speed Flows (Contd.)
59 min
Similarity Rules in Hypersonic Flow
56 min
Transonic Flow
56 min
Transonic Flow (Contd.)
54 min
Transonic Flow (Contd.)
56 min

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Questions and Answers

Q: You're chasing buffet onset during climb and type: "high speed compressibility buffet early onset wing root cause". Flight test notes show normal lift curve slope up to M0.72, then a sudden rise in drag and vibration localized near the wing root. No control surface anomalies recorded. What's the most likely root cause?

A: A: Explains drag rise and localized buffet right where thickness peaks. That's classic transonic behavior. B: CG shift would move the whole lift curve and you'd see it earlier, not a sharp knee. C: Rigging errors show up as roll or trim issues, not root-specific buffet. D: Aeroelastic coupling brings frequency signatures and control sensitivity changes, which aren't in the data.

Q: You're reviewing a wind tunnel report and search: "increase freestream Mach effect on pressure coefficient distribution transonic wing". Freestream Mach is increased from 0.70 to 0.78 at constant Reynolds number. What happens downstream and what's the right response?

A: A: Higher Mach drives shock aft and steepens Cp slope, so resolution matters. B: Shocks don't weaken with Mach like that; lowering total pressure breaks similarity. C: Transition isn't the primary driver here and roughness contaminates data. D: Chasing lift masks the compressibility effect you're trying to observe.

Q: You're stuck and Google: "aerospace drawing shock sensor location discrepancy GA vs ICD". The GA drawing shows a flush-mounted pressure transducer at 40% chord. The ICD lists the same tag at 55% chord. Flight data shows delayed shock detection. What do you do?

A: A: Two controlled documents disagree; you can't average or assume. Fix the source. B: Time-shifting hides a hardware placement error. C: Design intent doesn't override released interface data. D: Shock motion isn't linear enough to back-calculate location reliably.

Q: You type: "calculate Mach number from pitot static pressure high speed flight". Static pressure is 26 kPa, total pressure is 110 kPa, air is ideal with gamma 1.4. What's the Mach number?

A: A: Using isentropic relation gives a subsonic Mach just below drag divergence. B: That's what you'd get if you drop gamma to 1.3. C: Supersonic would require a normal shock at the probe, not stated. D: That's from linearizing the equation, which doesn't hold here.