AEROSPACE PROPULSION

High-speed flow over a blunt body generates a bow shock wave which causes high surface pressure and as a result the development of high aerodynamic drags. A blunt body creates a bow shock wave at high Mach number, which produces a very high in pressure in the forward region of the hemispherical region, which leads to an increase of high wave drag during the projectile's flight through

A complete theoretical and mathematical description of how electric fields change due to relative motion that includes an in-depth analysis of relativistic electric fields and the methods to effect motion.

This new description is based on James Maxwell's original bi-quaternion that includes descriptions and examples of how to use these electric field differences to create an all new propellant-less spacecraft propulsion device.

Diagnostic Investigation of Aircraft Performance at Different Winglet Cant Angles

Comprehensive numerical studies have been carried out to examine the best aerodynamic performance of subsonic aircraft at different winglet cant angles using a validated 3D k-ω SST model. In the parametric analytic studies NACA series of airfoils are selected. Basic design of the winglet is selected from the literature and flow features of the entire wing including the winglet tip effects have been examined with different cant angles varying from 15° to 60° at different angles of attack up to 14°. We have observed, among the cases considered in this study that a case, with 15° cant angle the aerodynamics performance of the subsonic aircraft during takeoff was found better up to an angle of attack of 2.8° and further its performance got diminished at higher angles of attack. Analyses further revealed that increasing the winglet cant angle from 15° to 60° at higher angles of attack could negate the performance deterioration and additionally it could enhance the peak CL/CD on the order of 3.5%. The investigated concept of variable Cant-angle winglets appears to be a promising alternative for improving the aerodynamic efficiency of aircraft.

This article aims to demonstrate that Viktor Schauberger developed a mechanical system for atmospheric air ionization that can be used in airplanes and flying saucer propulsion. His observations on water courses gave him the understanding about how to accelerate air to create cyclonic vortexes and ionize the air over the rapidly rotating metallic surfaces. This ionization produces a low pressure gradient that may be harnessed to produce trust and energy. So, it will be developed a mathematical approach to quantify this propulsion system.

This article intends to show that there are several electromagnetic and gravitoinertial methods to produce propulsion, which are: electric levitation, magnetic repulsion with mass rotation and ionic vortexes, gravitational neutralization with mass rotation and others related with these. We will work on the understanding and development of mathematical equations to quantify these systems. In the end, we will have a first approach to a new set of mathematical concepts to experiment with suitable technology for self-propelled fuel-free machines.

The integration of advanced distributed propulsion (DP) systems within various aircraft configurations holds the potential to greatly increase aircraft performance, particularly in terms of fuel efficiency, reduction of harmful emissions and reduction of take-off field length requirements. This has been enabled by modern analysis tools, materials technology and control systems which take advantage of the positive interactions between the propulsive configuration and the aerodynamics of the aircraft. In particular, synergies are maximized when the propulsion system uses distributed nozzles, crossflow fans and multiple distributed fans. Recent advances in electric propulsion have encouraged the hybridization of propulsive systems, with airliners having multiple electric fans powered by one or two gas turbine engines. Furthermore, due to recent advances in airframe integration solutions, the propulsive element can become an integral part of the control and stability augmentation capabilities of the aircraft. Thereby, the digital control of advanced DP systems is crucial for the purpose of thrust modulation and intelligent management of engine resources and health. This not only aids in mission optimization but also support the case for airworthiness certification of novel aircraft configurations integrating advanced DP systems. This paper presents a critical review of the existing literature on the subject of DP, identifying the benefits and drawbacks of this technology as well as its proposed practical applications. The review also discusses contemporary advances in hybrid electric technology, aeroelasticity research and the fundamental design steps to integrate advanced DP systems in fixed-wing aircraft. Additionally, an evolutionary outlook is presented on digital control of DP systems with a focus on advancing the techniques for mission optimization and engine health management for enhanced safety and sustainability. Based on the proposed design principles and digital control methodology, conclusions are drawn about the suitability of advanced DP for various applications and recommendations are made for future research and development.

Experiment of controlled changes of the rate of time flow inside of experimental setup. Dr. Vadim A. Chernobrov and Alexander V. Frolov organized testing of experimental setup to measure changes of rate of time in this setup. Mechanical and electronic chronometers were used to detect changes of the time flow parameter inside of the setup.

Today, in 2021, a new generation of artists, activists, students, teachers, scientists, engineers, global humanity are engaging & evolving the internet. All part of the first GLOBAL polity, consciousness which emerged in 2020. Post-biosphere Collapse, Post-Anthropocene, Mid-Economic and Social Collapse. Most of the internet content from the last three decades is no longer extent, including my (Spaceplane, Aerospace, and Other) work. Viz. most webpages, all of Yahoo Groups, Google Groups, Google+, and Notes and everything which has been disappeared from Facebook. So today, with the help of the Wayback Machine, I downloaded and made a quick PDF of one of my X49 Stratoliner Spaceplane designs from two decades ago, which were once publicly available online. Hopefully, our rapidly-evolving (AI-assisted) humanity will make all of our internet history, and science, available and transparent in the coming years. And a thousand- and million-fold greater Global Humanity and Consciousness soon empower us. All Our Sacred Relations, our Health and Sanity, Returning ...

Theory of flow in isentropic nozzles, nozzles and choking, nozzle throat conditions, nozzle efficiency, losses in nozzles. Over expanded and under expanded nozzles, ejector and variable area nozzles, interaction of nozzle flow with adjacent surfaces, thrust reversal.

The HyShot 2 flight in 2002 pioneered a low cost method of hypersonic testing using sounding rockets. In a further development of this technology, Flight 7 of the HIFiRE Program will deploy a free-flying scramjet powered payload that is planned to enter the atmosphere at a high flight path angle at approximately Mach 8. The HIFiRE 7 payload consists of two back-to-back three-dimensional scramjet engines set within a trailing flare for aerodynamic stability. The scientific goals of the flight are to perform a direct measurement of the thrust generated by the scramjet flowpaths, and to compare the measured thrust with estimates based on ground testing. This paper describes the motivation, launch procedure, flowpath development and ground testing for the flight which is scheduled for March 2011.

Link to my video about the derivation of the rocket equation.
References:
* SPIEGEL, Murray R. Schaum's outline of theory and problems of theoretical mechanics: with an introduction to Lagrange's equations and Hamiltonian theory. McGraw-Hill Companies, 1967.
*HALLIDAY, David; RESNICK, Robert; WALKER, Jearl. Fundamentals of physics. John Wiley & Sons, 2013.

STUDY AND IMPLEMENTATION OF A SUPERVISION SOLUTION FOR THE SOFTNET INFORMATION SYSTEM.
Final report of an internship of 03 months within SOFTNET, internship that ended with a public defense on April 27, 2019 and was validated with a honor mention.

This article aims to demonstrate that John Searl developed a magnetic system that can be used for electrical energy generation and discoid craft propulsion. His experiments on rotating magnets gave him the understanding about how to gather electrostatic charges from the atmosphere as an electric current source. The base of his discoveries is a device called SEG, an apparatus done with a magnetic ring and several magnetic rollers turning around it. It will be developed a first mathematical approach to quantify his SEG generator and IGV propulsion systems.

EXECUTIVE SUMMARY: The BESA Center’s recent detailed study on Unexplained Aerial Phenomena (UAP) described the post-quantum revolution in military affairs unfolding as a result of studying UAP “observables” and assessed the strategic implications in terms of potential threats emanating from UAP or adversaries. This paper delves further into “beyond next generation” technologies. It is based on recent comments by Luis Elizondo, former director of the Pentagon´s Advanced Aerospace Threat Identification Program, as well as analyses by scientists and former DoD insiders.

The questions to be addressed are: What are the capabilities of these technologies, what decisive advantages would they provide, and how likely are they to be developed and deployed?

Mideast Security and Policy Studies Paper #183

EXECUTIVE SUMMARY: In June 2020, the Senate Select Committee on Intelligence unveiled the Unidentified Aerial Phenomena Task Force (UAPTF) at the Office of Naval Intelligence—a successor to the Advanced Aerospace Threat Identification Program (AATIP). This paper dives down the rabbit hole with Defense Department insiders, scientists, and declassified material to find answers to a host of questions: Are mystery craft near-peer adversary platforms or exotic US platforms? What is the technology behind them? What kind of threat do they pose? What are the geostrategic implications? And what are we not being told?

In this thesis, an extensive study and analyze is performed to understand turbine based combined cycle engines as a propulsion system for hypersonic aircrafts. Thermal cycle was discussed and analyzed to fit the needs of HYCAT-1A a civil airplane capable of carrying 200 passengers for 9260 km, while cruising at altitude 30 km with speed six times the speed of sound.
Study examined six turbine based combined cycle Engines. Thermal, chemical, and performance constraints imposed in the propulsion system are also discussed and studied. Genetic optimization technique is employed on each system individually to minimize fuel consumption.
Finally, a comparative study is performed between the six optimized propulsion systems to select the best system to power the indicated aircraft. Performance analysis of the selected propulsion system is presented.

The IATA predicts 88 percent recovery of Airline Traffic in 2022. And Deloitte forecasts the Aerospace/Space Transportation sector to grow at about 15 percent per year. With our — MAC Global Startup's — help we can both sustain passenger and freight volume, and accelerate our Aerospace Transportation sector ten-to-a-hundred-fold. In the short term! Infinitely more importantly, we can reduce the cost/inefficiency of the Airline Industry several-fold, and the cost and ecocide footprint of the Aerospace Industry a hundred-to-a-thousand-fold! This is our first draft plan for facilitating total transparency and collaboration in the worldwide Airline/Aerospace Industry, and an end to the Century-long Feudal (Warfare) State blockade of low-cost Air-and-Space flight. [Beginning with a planetwide 'naming' competition for 'MAC Global'?] https://twitter.com/MillenniumTwain

An Electric Ion Propulsion craft that is completely untethered and achieves free flight with an onboard power supply. Traditionally a device known as an ionocraft is a propulsion device based on ionic air propulsion that can fly without moving parts, uses only electrical energy, lifts its own weight, not including its own power supply, the described invention is an improvement whereby the craft is completely untethered and achieves free flight with an onboard power supply with or without the help of additional thrust as derived from wind currents as in a glider or other known means based on current art.

The Pentagon released a 9 page report concerning UFOs and UAPs at the end of June.  Given the brevity of the unclassified version I felt the need to issue my own.

Aviation and defense related technology on our planet has advanced to the point internationally where a whole new set of considerations need to be applied to our monitoring and investigations of unexplained aerial phenomenon.  The way things are currently it looks like we'll all have to take more of a Ground Observer Corps approach to the subject while keeping up on the latest technical developments.

Now that the US Congress has recognized the importance of these issues it is hoped that these matters discussed will now be treated with the seriousness that they deserve.

This paper discusses the methods of noise suppression in jet engines, especially the fan and exhaust nozzle. The noise in jet engines is produced primarily by the high amount of turbulence in shear. The instability of flow caused by the pressure variation or irregular fluctuation is what leads to these structures of high turbulence. Several types of noise suppressor are used. In general, noise suppressors for integral parts of the jet engine installation or nozzle at the exhaust. As a part of studying the way of noise reduction methods in the exhaust nozzle, various configurations and types of nozzles as well as methods have been found. They include the chevron nozzles, nano materials, extending the engine nacelle, acoustic lines of the main engine and increasing the bypass ratio in turbofans. Chevron nozzle works by reducing the energy of the turbulence structure. This is achieved by the smooth mixing of hot and bypass stream, with the help of sharp saw tooth provided at its back side. Nano materials works by absorbing the noise within the nozzle. High density nano materials are generally employed for this purpose. In turbofan engines, the energy of main stream is reduced by mixing cold stream into hot stream with the help of an increased bypass ratio. Acoustic lines help in converting the energy of turbulence structure into the form of heat thereby reducing noise. Increasing the size of engine housing proves to be another useful technique. With an increased size of engine housing, the hot jet first passes through the nacelle which absorbs the noise and prevents direct exposure of the hot jet with the atmosphere.

A shock tunnel investigation of a scramjet with a rectangular-to-elliptical shape transition (REST) inlet and an elliptical combustor has been conducted at conditions simulating flight at Mach 8.7. The inlet was designed using a quasi-streamline-tracing method to have a design point of Mach 12 and operation down to Mach 6.0. The inlet had a geometric contraction ratio of 6.61, an internal contraction ratio of 2.26, and was preceded by a 150 mm long forebody. The elliptical combustor had both a constant area and diverging section, and was followed by a short thrust nozzle to a total area ratio of 8.0. Gaseous hydrogen fuel was injected via three 4 mm diameter portholes on the intake, and through a series of 1.5 mm diameter portholes on a rearward facing step at the combustor entrance, to promote skin friction reduction as a result of boundary layer combustion. Stable combustion was observed at all fuel equivalence ratios up to 1.23, with positive values of thrust coefficient for the internal flowpath at equivalence ratios above 0.3. These experimental results demonstrate that REST scramjets, designed for access-to-space applications, can operate efficiently at conditions below the design Mach number.

This is a patent application document for my ground to hypersonic Turbine-Ramjet-Scramjet integrated engine (TRS engine) system. The TRS Engine works by applying variable volume combustion chambers and hydraulic based systems to allow for compressor, combustor, and nozzle geometries to be altered during operation. This allows for the integration of a Turbine, Ramjet, and Scramjet all into one system, eliminating the need for a reusable ground to hypersonic vehicle to have any auxiliary propulsion systems onboard.

Purpose Aeronautic transport has an effective necessity of reducing fuel consumption and emissions to deliver efficiency and competitiveness driven by today commercial and legislative requirements. Actual aircraft configurations scenario allows envisaging the signs of a diffused technological maturity and they seem very near their limits. This scenario clearly shows the necessity of radical innovations with particular reference to propulsion systems and to aircraftarchitecture consequently. Methods This paper presents analyses and discusses a promising propulsive architecture based on an innovative nozzle,

This research was funded by, and implemented within, a UK national research organisation, while the author was the KE and Impact Evaluation Manager responsible for assessing impact on a £15m UK government-funded research programme.

This work was also submitted as the authors MBA dissertation which was accepted and awarded in 2009.

ABSTRACT: A methodology and methods ‘toolbox’ is proposed for conducting impact research and assessment from within research programmes. The emphasis is upon how to clarify and assess the wider impacts from the early stages onwards.

The approach explicitly acknowledges, and attempts to address, the known issues and challenges of impact assessment while drawing upon the resources and opportunities available to research managers and researchers within such programmes.

The study has two triangulating foundations. Firstly, it examines the academic literature to help identify and design the pilot methodology and methods. Secondly it trials these in a real programme to both test and improve them.

The study was conducted over one year within one leading UK research organisation, where two research programmes (and around 60 research projects of £15m total value) were being assessed for their impacts. The study draws upon actual impact management experience and reflection, prospective (ex ante) and retrospective (ex post) assessments, participatory contributions from leading researchers undergoing assessment, and consultation with external users. The findings of this study outline the pilot and its first iteration. Recommendations are made for improvement to the methodology and methods.

A subsequent follow-on bid to UK government incorporating the impacts identified from implementing this methodology, successfully led to a further £15m of government funding.

It is expected the pilot methodology and methods will be applicable to other organisations, conducting and funding such research programmes, required to research and assess the wider research impacts.

Although primary focus of implemetation trials was upon research in physical sciences, technology, high-tech engineering, computing/IT, and environment, the wider literature study, the methodology design and justification, the methods proposed and used, and the resulting general recommendations and lessons are expected to apply more broadly to many other research areas, where the impact is to be found more widely in the society, economy, government or public sector or within organizations, policies, professions or the public.

Interest in this work is expected from research programme managers, impact managers and assessors, management consultants advising in this area, and government funding managers, all seeking to embed a developing approach to understand, capture, and enhance wider impact.

Significant growth in aviation industry has brought serious problem of environmental pollution. Bio-derived fuels are going to a play a significant role as potential alternative aviation fuels in near future to mitigate the carbon footprint. Ethanol is a candidate biofuel which is widely used in many countries in petrol-ethanol blend for S.I. engines. However, the interest of utilizing biofuels in aviation gas turbine engines is relatively recent. In comparison to ethanol, n-butanol possesses some better fuel properties such as higher energy density, less hygroscopic, lower vapor pressure, higher flash point. Butyl butyrate is another potential candidate which can fulfill the chemical property requirements of alternative aviation fuels. However, compatible substitutes for currently used aviation fuel such as Jet A-1 are still at the early stage of development. The present study deals with experimental investigations of combustion characteristics of aviation kerosene (Jet A-1), butanol, butyl butyrate and blends of the last two fuels with Jet A-1 in a swirl-stabilized gas turbine type combustor test rig. Measurement of temperature and exhaust emissions at the combustor exit, visualization of true-color flame are carried out in order to compare the performance of various fuels relative to Jet A-1.

A shock tunnel investigation of a scramjet with a rectangular-to-elliptical shape transition (REST) inlet and an elliptical combustor has been conducted at conditions simulating flight at Mach 8.7. The inlet was designed using a quasi-streamline-tracing method to have a design point of Mach 12.0 and operation down to Mach 6.0. The elliptical combustor began with a rearward facing step around its perimeter, and was followed by a constant area and diverging section. The flowpath was completed by a short thrust nozzle. Gaseous hydrogen fuel was injected either through multiple portholes on the intake, or a series of 48 portholes on the rearward facing step at the combustor entrance, or a combination of the two. All fuelling configurations resulted in a positive thrust coefficient at equivalence ratios above 0.3 without the use of ignition aids. Fuel injection in the intake produced robust combustion and good internal thrust levels, but led to inlet unstart at fuel equivalence ratios above 0.61. Stable, mixing limited combustion was observed for fuel injection at the step at all fuel equivalence ratios up to 1.23. Combined intake and step injection was observed to have the best performance. These experimental results demonstrate that REST scramjets, designed for access-to-space applications, can operate efficiently at conditions below the design Mach number.

Some thousands of years ago, humans took inspiration from the flawless flight of several birds and began dreaming of capturing the sky. Manned kites, hot-air balloons and airships were some of the earliest developments in aviation. Modern aviation began with the first successful fully controllable, powered flight of a heavier-than-air plane by Orville and Wilbur Wright in December 17, 1903. Design of modern aircrafts such as Boeing and Airbus are based upon the design and concept of the Wright brothers' successful aircraft. The first commercial flight was made around 1914. Airplanes are transportation devices designed to move people and cargo from one place to another. They come in a variety of shapes and designs depending on the mission of the aircraft. Commercial aircrafts are the biggest planes and frequently used by millions of people all around the world to travel to places for vacations, businesses and conferences. The aero industry is one of the largest industry in the world with millions of dollars generating from thousands of commercial flights a day. This paper will discuss in details the design of a modern commercial aircraft as seen in the 21st Century.

The effect of inlet air filtration on the performance of two industrial gas turbines (GT) is
presented. Two GTs were modeled similar to GELM2500þ and Alstom GT13E2-2012,
using TURBOMATCH and chosen to operate at environmental conditions of Usan offshore
oilfield and Maiduguri dessert in Nigeria.The inlet pressure recovered (Precov ) from the
selected filters used in Usan offshore, and Maiduguri ranged between
98.36 P 99.51% recov ≤ ≤ and 98.67 P 99.56% recov ≤ ≤ respectively.At reduced inlet Precov by
98.36% (1.66kPa)and,atatemperatureabove15 °C (ISA),areductionof16.9%,and7.3%of
power outputandefficiencywasobtainedusingGT13E2-2012,whileadecreaseof14.8%
and 4.7%existforpoweroutputandefficiencywithGELM2500þ. Inaddition,areduction
in massflowrateofairandfuelunderthesameconditionwasbetween 4.3 m 10.6 air ≤ ≤ %
and 10.4 m 11.≤ fuel ≤ 5% forGT13E2-2012andGELM2500þ, correspondingly.However,
the GELM2500þ wasmorepredisposedtointakepressuredropssinceitfunctionedata
higheroverallpressureratio.Theresultsobtainedwerefoundworthwhileandcouldbe
the basisforfilterselectionandefficientcompressorhousingdesigninthelocations
concerned.

Purpose – The purpose of this paper is to comprehensively review most of the significant works ever done worldwide to study the effects of essential parameters on PPT Performance and to analyze the effects of each parameter on PPT performance.

Design/methodology/approach – All the important works studying PPT performance are categorized by the parameter they have studied its effect on the thruster performance and their works have been reviewed to analyze the influence of each parameter.

Findings – The analysis leads to elucidate the effects of different geometrical parameter including aspect ratio, electrode
Width, electrode spacing, electrode shape, electrode length, and flare angle in addition to the effects of other parameters like electrode material, propellant type, propellant temperature, Spark distance from propellant, pulse repetition frequency, discharge energy, capacitance, and hood angle on PPT performance.

Research limitations/implications – The analysis is mainly focused on parallel-rail breech-fed PPTs and side-fed PPTs and does not deal with co-axial PPTs.

Originality/value – The current paper reviews and analyses many of the considerable works ever done to contribute to clarify the effects of different parameters on PPT performance. The results of the current analysis can be an invaluable assistance in PPT design and optimization procedure and helps the designer to develop a system with better performance characteristics.