Maximum Range Glide of a Supersonic Aircraft in the Presence of Wind

In this chapter the wide array of engineering devices, from the kitchen tap (a valve) to supersonic aircraft, the basic design of which depends upon considerations of the flow of gases and liquids, is shown. Much the same is true of most natural phenomena from the atmosphere and our weather to ocean waves, and the movement of sperm and other bodily fluids. In this textbook a number of the concepts, principles, and procedures which underlie the analysis of any problem involving fluid flow or a fluid at rest are introduced. In this Introduction, examples have been selected for which, by the end of the book, the student should be in a position to make practically useful engineering-design calculations. These include a dam, a rocket motor, a supersonic aerofoil with shock and expansion waves, a turbojet engine, a turbofan engine, and the blading of a gas turbine.

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Effects of Increased Noise Levels by Supersonic Aircraft on Annoyance Levels and Time Estimations

Perceptual and Motor Skills ◽

10.1177/003151258005000239 ◽

1980 ◽

Vol 50 (2) ◽

pp. 563-569

Author(s):

John A. Allen

Keyword(s):

Aircraft Noise ◽

Noise Levels ◽

Supersonic Aircraft ◽

International Airport

Several tests designed to assess the effects of increased noise levels created by the Concorde supersonic aircraft were administered to 48 residents living around Dulles International Airport and 31 persons not living near an airport. Results of a pretest questionnaire and lack of significant changes in annoyance levels and time estimations indicate that, while airport-area residents may be more conscious of aircraft noise, changes in the perceived intensities of sounds may not occur.

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The Determination of Maximum Range for an Unpowered Atmospheric Vehicle

Journal of the Royal Aeronautical Society ◽

10.1017/s0001924000061364 ◽

1964 ◽

Vol 68 (638) ◽

pp. 111-116 ◽

Cited By ~ 2

Author(s):

D. J. Bell

Keyword(s):

Calculus Of Variations ◽

Lagrange Multipliers ◽

Digital Computer ◽

Necessary Conditions ◽

Lagrange Equations ◽

Initial Portion ◽

End Conditions ◽

Maximum Range ◽

Isothermal Atmosphere

SummaryThe problem of maximising the range of a given unpowered, air-launched vehicle is formed as one of Mayer type in the calculus of variations. Eulers’ necessary conditions for the existence of an extremal are stated together with the natural end conditions. The problem reduces to finding the incidence programme which will give the greatest range.The vehicle is assumed to be an air-to-ground, winged unpowered vehicle flying in an isothermal atmosphere above a flat earth. It is also assumed to be a point mass acted upon by the forces of lift, drag and weight. The acceleration due to gravity is assumed constant.The fundamental constraints of the problem and the Euler-Lagrange equations are programmed for an automatic digital computer. By considering the Lagrange multipliers involved in the problem a method of search is devised based on finding flight paths with maximum range for specified final velocities. It is shown that this method leads to trajectories which are sufficiently close to the “best” trajectory for most practical purposes.It is concluded that such a method is practical and is particularly useful in obtaining the optimum incidence programme during the initial portion of the flight path.

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Method for comparison of the maximum range of chemical pollutants

Russian Journal of General Chemistry ◽

10.1134/s1070363214130283 ◽

2014 ◽

Vol 84 (13) ◽

pp. 2677-2680 ◽

Cited By ~ 1

Author(s):

S. Ketin ◽

S. Sacirovic ◽

S. Plojovic ◽

R. Skrijelj ◽

R. Biocanin

Keyword(s):

Chemical Pollutants ◽

Maximum Range

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Maximum Range Of Ballistic Missiles

SIAM Review ◽

10.1137/1007111 ◽

1965 ◽

Vol 7 (4) ◽

pp. 544-550 ◽

Cited By ~ 3

Author(s):

Kasturi L. Arorat ◽

Nguyen X. Vinh

Keyword(s):

Ballistic Missiles ◽

Maximum Range

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Background Oriented Schlieren (BOS) of a Supersonic Aircraft in Flight

AIAA Flight Testing Conference ◽

10.2514/6.2016-3356 ◽

2016 ◽

Cited By ~ 7

Author(s):

James T. Heineck ◽

Daniel Banks ◽

Edward T. Schairer ◽

Edward A. Haering ◽

Paul Bean

Keyword(s):

Supersonic Aircraft ◽

Background Oriented Schlieren

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Practical Structural Design Problems of Supersonic Aircraft

Aircraft Engineering and Aerospace Technology ◽

10.1108/eb032851 ◽

1957 ◽

Vol 29 (7) ◽

pp. 206-215

Author(s):

W.G. Heath ◽

B.O. Heath

Keyword(s):

Structural Design ◽

Design Problems ◽

Supersonic Aircraft

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Life Prediction of Directionally Solidified Air Cooled HPT Gas Turbine Blade Used in a Supersonic Aircraft Using FEM

ASME 2013 Gas Turbine India Conference ◽

10.1115/gtindia2013-3572 ◽

2013 ◽

Author(s):

S. Esakki Muthu ◽

S. Dileep ◽

S. Saji Kumar ◽

D. K. Girish

Keyword(s):

Gas Turbine ◽

Turbine Blade ◽

Operating Conditions ◽

Test Facility ◽

Time To Failure ◽

Generation Process ◽

Gas Turbine Blade ◽

Directionally Solidified ◽

Life Estimation ◽

Supersonic Aircraft

Life estimation of Directionally Solidified (DS) MARM-247 HPT gas turbine blade used in a turbofan engine of a supersonic aircraft is presented. These blades were drafted into the engine as a replacement for the polycrystal (NIMONIC) blades since a more efficient, reliable and durable material with high strength and temperature resistance was required to further enhance the life of the turbine blade and the efficiency of the power generation process. The supersonic aircraft is having a repeated mission cycle of a fast acceleration from idle, a 1hr cruise at Mach 1.5 and a fast deceleration to idle. The mission cycle which is a repetition of acceleration, cruise and deceleration cycles can produce wide variety of complex loading conditions which can result in HCF, LCF and creep damage of the turbine blade. Empirical equation of the universal slope developed by Manson was used to estimate the damage component due to LCF. The cumulative stresses and strains due to creep as a function of time was determined using Time hardening rule. Creep data for MARM-247 was correlated using LMP to predict the lives to 1% of creep strain at worst possible combination of temperature and stress value. Damage due to creep per mission cycle was determined using Life fraction Rule proposed by Robinson and Taira. The vibration characteristics of the turbine blade were predicted using Modal analysis. Campbell diagram was plotted to ascertain whether any nozzle passing frequency fall within the working range of the blade. Harmonic analysis was carried out to evaluate the magnitude of the alternating stresses resulting from the blade vibrations at resonance during the acceleration and deceleration cycle. HCF life of the turbine blade was assessed using Goodman diagram. The total damage of the turbine blade per mission cycle due to the above loading was assumed as the combination of the individual damage due to fatigue and creep. Time to failure under combined creep and fatigue damage was estimated using linear damage rule. Non linear features of FEA tool ANSYS12.0 was exploited to calculate the stress distribution, creep, plastic and the total strain encountered by the turbine blade as a function of mission cycle time. The loading spectrum associated with the mission cycle which includes the temperature, gas pressure and the speed profiles were obtained from a sophisticated engine ground test facility which was configured to simulate actual engine operating conditions. The proposed method of cyclic life estimation using FEM was validated by performing various component and engine level tests. A good agreement was observed between the calculated and observed blade lives.

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