JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

UNIT - I

Overview of the Design Process, Sizing From a Conceptual Sketch: Phases of aircraft design. Aircraft conceptual design process, project brief / request for proposal, problem definition, information retrieval, aircraft requirements, configuration options. Integrated product development and aircraft design. The initial conceptual sketches, L / D estimation. Initial takeoff weight build-up, empty weight estimation, historical trends, fuel fraction estimation, mission profiles, mission segment weight fractions.

UNIT - II

Airfoil and Geometry Selection, Thrust to Weight Ratio, Wing Loading: Airfoil selection, airfoil design, design lift coefficient, stall, airfoil thickness ratio and other airfoil considerations. Wing geometry and wing vertical location, wing tip shapes. Tail geometry and arrangements. Thrust to weight ratio, statistical estimation, thrust matching. Wing loading performance constraints. Selection of thrust-to-weight ratio and wing loading.

Initial Sizing and Configuration Layout, Crew Station, Passengers And Payload: Sizing with fixed engine and with rubber engine. Geometry sizing of fuselage, wing, tail, control surfaces. Development of configuration lay out from conceptual sketch. The inboard profile drawing, wetted area, volume distribution and fuel volume plots. Lofting- definition, significance and methods, flat wrap lofting. Special consideration in configuration lay out. Isobar tailoring, Sears-Haack volume distribution, structural load paths. Radar, IR, visual detectability, aural signature. Considerations of vulnerability, crashworthiness, producibility, maintainability. Fuselage design, crew station, passenger compartment, cargo provisions, weapons carriage, gun installation.

UNIT - III

Propulsion and Fuel System Integration, Landing Gear and Subsystems: Propulsion selection, jet engine integration, engine dimensions, inlet geometry, inlet location, capture area calculation, boundary layer diverters, nozzle integration, engine cooling provisions, engine size estimation. Fuel system design and integration. Landing gear arrangements, guidelines for lay out. Shock absorbers–types, sizing, stroke determination, gear load factors. Gear retraction geometry. Aircraft subsystems, significance to configuration lay out. The baseline design layout and report of initial specifications.

Baseline Design Analysis - Aerodynamics & Propulsion, Structures & Weight and Balance: Estimation of lift curve slope, maximum lift coefficient, complete drag build up. Installed performance of an engine, installed thrust methodology, net propulsive force, part power operation. Aircraft loads, categories: manoeuvre, gust, inertial, power plant, landing gear loads. Limit loads, the V, n diagram. Air load distribution on lifting surfaces. Review of

R16 B.TECH AERONAUTICAL ENGG.

methods of structural analysis. Material selection. Weights and moments statistical group estimation method, centre of gravity excursion control.

UNIT - IV

Baseline Design - Stability and Control, Performance and Constraint Analysis: Estimation of static pitch stability, velocity stability and trim. Estimation of stability and control derivatives. Static lateral, directional stability and trim. Estimation of aircraft dynamical characteristics, handling qualities. Cooper – Harper scale, relation to aircraft dynamic characteristics. Performance analysis and constraint analysis– steady level flight, minimum thrust required for level flight, range and loiter endurance. Steady climbing and descending flight, best angle and rate of climb, time to climb and fuel to climb. Level turning flight, instantaneous turn rate, sustained turn rate. Energy maneuverability methods of optimal climb trajectories and turns. The aircraft operating envelope. Take off analysis, Balanced field length. Landing analysis. Fighter performance measures of merit. Effects of wind on aircraft performance. Initial technical report of baseline design analysis and evaluation. Refined baseline design and report of specifications.

Cost Estimation, Parametric Analysis, Optimisation, Refined Sizing and Trade Studies: Elements of life cycle cost, cost estimating method, RDT&E and production costs, operation and maintenance costs, fuel and oil costs, crew salaries, maintenance expenses, depreciation. Cost measures of merit. Aircraft and airline economics, DOC and IOC, airline revenue, breakeven analysis, investment cost analysis. Parametric analysis and optimisation. Refined conceptual sizing methods. Sizing matrix plot and carpet plot. Trade studies, design trades, requirement trades, growth sensitivities. Multivariable design optimization methods. Measures of merit. Determination of final baseline design configuration, preparation of type specification report.

UNIT - V

Case Studies and Design of Unique Aircraft Concepts: Design of the DC – 1, DC – 2, DC- 3 aircraft, Boeing B-47 and 707, General Dynamics F-16, SR-71 Blackbird, Northrop- Grumman B-2 Stealth Bomber. A survey of the Indian aircraft design effort. Design of VTOL aircraft, helicopters, hypersonic vehicles, delta and double delta wings, forward swept wings, uninhabited air vehicles.

TEXT BOOKS:

• 1. Raymer, Daniel P. (2006), Aircraft Design: A Conceptual Approach, 4th edition, AIAA Educational Series, USA.
• 2. J. F. Marchman, L. R. Jenkinson (2003), Aircraft Design Projects for Engineering students, AIAA Publishers, USA.
• 3. Ajoy Kumar Kunda (2010), Aircraft Design, Cambridge University Press, UK.

REFERENCE BOOKS

• 1. Torenbeek E. (1986), Synthesis of Subsonic Airplane Design, Delft University Press, New York. R16 B.TECH AERONAUTICAL ENGG.
• 2. Bruhn. E. H (1973), Analysis and Design of Flight Vehicles Structures, New Edition, Jacobs Publishing House, USA.
• 3. Scheler E. E, Dunn L.G (1963), Airplane Structural Analysis and Design, John Wiley & Sons, USA.
• 4. D. Howe (2005), Aircraft conceptual Design Synthesis, John Wiley & Sons Publishers, USA. R16 B.TECH AERONAUTICAL ENGG.