JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

UNIT - I

Introduction: History of hypersonic flight- a logical progression in the light of advancing technical findings. Hypersonic flow- definition, importance, physical aspects. Brief descriptive introductory pre-view of various phenomena such as Thin shock layer, Entropy layer, Viscous interaction, Effects of high temperature and communication black out. Low density flow, free molecular flow. Hypersonic Shock and Expansion Wave Relations: Oblique shock relations for high Mach numbers, Expansion wave relations for high Mach numbers. Theoretical basis of Mach number independence principle- corroboration by experimental results. Importance of experiments.

UNIT - II

Local Surface Inclination Methods: Newtonian flow and the hypersonic double limit of M → ∞ & γ → 1, Modified Newtonian flow, Centrifugal force correction to Newtonian flow, Tangent wedge and tangent cone methods. Hypersonic Inviscid Flows - I: Hypersonic small disturbance theory, Equivalence principle and hypersonic similarity parameter; Hypersonic shock relations in terms of similarity parameter.

UNIT - III

Hypersonic Inviscid Flows – II: Application of small disturbance theory and equivalence of 1-dimensional piston motion with 2-dimensional hypersonic flow, Flat plate at an angle of attack by piston theory and comparison with exact shock expansion method, Bi-convex airfoil at zero angle of attack: comparison of piston theory and exact shock expansion method, Phenomenological aspects of hypersonic blunt body problem, Importance of blunt body problem and brief outline of computational time-marching finite difference method and its advantage over other methods.

UNIT - IV

Viscous Flows: Derivation of compressible boundary layer equations, Brief introduction to the flat plate case and some important results and conclusions for high Mach number flows, Special characteristics of hypersonic boundary layers, Introduction to hypersonic interaction parameters – weak & strong.

UNIT - V

Shock Tube Based Experimental Facilities: Shock tunnel, Gun tunnel, Free piston wind tunnel, Ludweig tube, Measurement techniques, Samples of comparison of experimental and theoretical results.

R16 B.TECH AERONAUTICAL ENGG.

Other Hypersonic Facilities: Continuous hypersonic tunnel free flight experiments in tunnels and ballistic ranges- Measurement techniques. Role of experiments in computer code validation and calibration, Brief introduction to heat transfer measurements.

TEXT BOOKS:

• 1. Anderson J D, Hypersonic and High Temperature Gas Dynamics, 2nd Edition, AIAA Education series, 2000.
• 2. Bertin, J. J. , Hypersonic Aerothermo-dynamics, AIAA Education series, 1994.
• 3. Spurk, J., Fluid Mechanics, Springer, Heidelberg, 1997.

REFERENCES:

• 1. Hayes W. D. and Probstein R. F., Hypersonic Flow Theory, Academic Press, 1959
• 2. Wendt J F, European Hypersonic Wind Tunnels, AGARD Conference Proceedings No. 428, Nov. 1987, Paper 2.
• 3. Canning T. N., Seiff A. and James, C. S., Ballistic Range Technology, AGARDograph Report AD 07 13915, Aug. 1970.
• 4. Brun, Raymond, Introduction to Reactive Gas Dynamics, Oxford Univ. Press, 2009, Chapter 11: Facilities and Experimental Methods.
• 5. Davies, H.J. and Churchack, H.D., Shock Tube Techniques & Instrumentation, 1969, US Army Material Command, Harry Diamond Lab, Washington DC (available on net – Free Copy).
• 6. Burtschell, Y., Brun, R., and Zeitoun, D., Shock Waves, Springer Verlag, Berlin , 1992.
• 7. An Album of Supersonic Flow Visualization, Edited by P I Kovalev & N P Mende, National Defense Industry Press (Write to Prof S V Bobashev, 26 Politechnicheskaya Street, St. Petersburg 194021, Russia).
• 8. Curtis, P. Shock tubes, Pegasus Eliot Mackenzie Publishers, October 2004. R16 B.TECH AERONAUTICAL ENGG.