Advanced High-Speed Aircraft
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Brazilian 14-Xs Hypersonic Unpowered Scramjet Aerospace Vehicle
ISSN 2176-5480 22nd International Congress of Mechanical Engineering (COBEM 2013) November 3-7, 2013, Ribeirão Preto, SP, Brazil Copyright © 2013 by ABCM BRAZILIAN 14-X S HYPERSONIC UNPOWERED SCRAMJET AEROSPACE VEHICLE STRUCTURAL ANALYSIS AT MACH NUMBER 7 Álvaro Francisco Santos Pivetta Universidade do Vale do Paraíba/UNIVAP, Campus Urbanova Av. Shishima Hifumi, no 2911 Urbanova CEP. 12244-000 São José dos Campos, SP - Brasil [email protected] David Romanelli Pinto ETEP Faculdades, Av. Barão do Rio Branco, no 882 Jardim Esplanada CEP. 12.242-800 São José dos Campos, SP, Brasil [email protected] Giannino Ponchio Camillo Instituto de Estudos Avançados/IEAv - Trevo Coronel Aviador José Alberto Albano do Amarante, nº1 Putim CEP. 12.228-001 São José dos Campos, SP - Brasil. [email protected] Felipe Jean da Costa Instituto Tecnológico de Aeronáutica/ITA - Praça Marechal Eduardo Gomes, nº 50 Vila das Acácias CEP. 12.228-900 São José dos Campos, SP - Brasil [email protected] Paulo Gilberto de Paula Toro Instituto de Estudos Avançados/IEAv - Trevo Coronel Aviador José Alberto Albano do Amarante, nº1 Putim CEP. 12.228-001 São José dos Campos, SP - Brasil. [email protected] Abstract. The Brazilian VHA 14-X S is a technological demonstrator of a hypersonic airbreathing propulsion system based on supersonic combustion (scramjet) to fly at Earth’s atmosphere at 30km altitude at Mach number 7, designed at the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, at the Institute for Advanced Studies. Basically, scramjet is a fully integrated airbreathing aeronautical engine that uses the oblique/conical shock waves generated during the hypersonic flight, to promote compression and deceleration of freestream atmospheric air at the inlet of the scramjet. -
CHAPTER 11 Subsonic and Supersonic Aircraft Emissions
CHAPTER 11 Subsonic and Supersonic Aircraft Emissions Lead Authors: A. Wahner M.A. Geller Co-authors: F. Arnold W.H. Brune D.A. Cariolle A.R. Douglass C. Johnson D.H. Lister J.A. Pyle R. Ramaroson D. Rind F. Rohrer U. Schumann A.M. Thompson CHAPTER 11 SUBSONIC AND SUPERSONIC AIRCRAFT EMISSIONS Contents SCIENTIFIC SUMMARY ......................................................................................................................................... 11.1 11.1 INTRODUCTION ............................................................................................................................................ 11.3 11.2 AIRCRAFT EMISSIONS ................................................................................................................................. 11.4 11.2.1 Subsonic Aircraft .................................................................................................................................. 11.5 11.2.2 Supersonic Aircraft ............................................................................................................................... 11.6 11.2.3 Military Aircraft .................................................................................................................................... 11.6 11.2.4 Emissions at Altitude ............................................................................................................................ 11.6 11.2.5 Scenarios and Emissions Data Bases ................................................................................................... -
Subsonic Aircraft Wing Conceptual Design Synthesis and Analysis
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by GSSRR.ORG: International Journals: Publishing Research Papers in all Fields International Journal of Sciences: Basic and Applied Research (IJSBAR) ISSN 2307-4531 (Print & Online) http://gssrr.org/index.php?journal=JournalOfBasicAndApplied --------------------------------------------------------------------------------------------------------------------------- Subsonic Aircraft Wing Conceptual Design Synthesis and Analysis Abderrahmane BADIS Electrical and Electronic Communication Engineer from UMBB (Ex.INELEC) Independent Electronics, Aeronautics, Propulsion, Well Logging and Software Design Research Engineer Takerboust, Aghbalou, Bouira 10007, Algeria [email protected] Abstract This paper exposes a simplified preliminary conceptual integrated method to design an aircraft wing in subsonic speeds up to Mach 0.85. The proposed approach is integrated, as it allows an early estimation of main aircraft aerodynamic features, namely the maximum lift-to-drag ratio and the total parasitic drag. First, the influence of the Lift and Load scatterings on the overall performance characteristics of the wing are discussed. It is established that the optimization is achieved by designing a wing geometry that yields elliptical lift and load distributions. Second, the reference trapezoidal wing is considered the base line geometry used to outline the wing shape layout. As such, the main geometrical parameters and governing relations for a trapezoidal wing are -
10. Supersonic Aerodynamics
Grumman Tribody Concept featured on the 1978 company calendar. The basis for this idea will be explained below. 10. Supersonic Aerodynamics 10.1 Introduction There have actually only been a few truly supersonic airplanes. This means airplanes that can cruise supersonically. Before the F-22, classic “supersonic” fighters used brute force (afterburners) and had extremely limited duration. As an example, consider the two defined supersonic missions for the F-14A: F-14A Supersonic Missions CAP (Combat Air Patrol) • 150 miles subsonic cruise to station • Loiter • Accel, M = 0.7 to 1.35, then dash 25 nm - 4 1/2 minutes and 50 nm total • Then, must head home, or to a tanker! DLI (Deck Launch Intercept) • Energy climb to 35K ft, M = 1.5 (4 minutes) • 6 minutes at M = 1.5 (out 125-130 nm) • 2 minutes Combat (slows down fast) After 12 minutes, must head home or to a tanker. In this chapter we will explain the key supersonic aerodynamics issues facing the configuration aerodynamicist. We will start by reviewing the most significant airplanes that had substantial sustained supersonic capability. We will then examine the key physical underpinnings of supersonic gas dynamics and their implications for configuration design. Examples are presented showing applications of modern CFD and the application of MDO. We will see that developing a practical supersonic airplane is extremely demanding and requires careful integration of the various contributing technologies. Finally we discuss contemporary efforts to develop new supersonic airplanes. 10.2 Supersonic “Cruise” Airplanes The supersonic capability described above is typical of most of the so-called supersonic fighters, and obviously the supersonic performance is limited. -
Aircraft of Today. Aerospace Education I
DOCUMENT RESUME ED 068 287 SE 014 551 AUTHOR Sayler, D. S. TITLE Aircraft of Today. Aerospace EducationI. INSTITUTION Air Univ.,, Maxwell AFB, Ala. JuniorReserve Office Training Corps. SPONS AGENCY Department of Defense, Washington, D.C. PUB DATE 71 NOTE 179p. EDRS PRICE MF-$0.65 HC-$6.58 DESCRIPTORS *Aerospace Education; *Aerospace Technology; Instruction; National Defense; *PhysicalSciences; *Resource Materials; Supplementary Textbooks; *Textbooks ABSTRACT This textbook gives a brief idea aboutthe modern aircraft used in defense and forcommercial purposes. Aerospace technology in its present form has developedalong certain basic principles of aerodynamic forces. Differentparts in an airplane have different functions to balance theaircraft in air, provide a thrust, and control the general mechanisms.Profusely illustrated descriptions provide a picture of whatkinds of aircraft are used for cargo, passenger travel, bombing, and supersonicflights. Propulsion principles and descriptions of differentkinds of engines are quite helpful. At the end of each chapter,new terminology is listed. The book is not available on the market andis to be used only in the Air Force ROTC program. (PS) SC AEROSPACE EDUCATION I U S DEPARTMENT OF HEALTH. EDUCATION & WELFARE OFFICE OF EDUCATION THIS DOCUMENT HAS BEEN REPRO OUCH) EXACTLY AS RECEIVED FROM THE PERSON OR ORGANIZATION ORIG INATING IT POINTS OF VIEW OR OPIN 'IONS STATED 00 NOT NECESSARILY REPRESENT OFFICIAL OFFICE OF EOU CATION POSITION OR POLICY AIR FORCE JUNIOR ROTC MR,UNIVERS17/14AXWELL MR FORCEBASE, ALABAMA Aerospace Education I Aircraft of Today D. S. Sayler Academic Publications Division 3825th Support Group (Academic) AIR FORCE JUNIOR ROTC AIR UNIVERSITY MAXWELL AIR FORCE BASE, ALABAMA 2 1971 Thispublication has been reviewed and approvedby competent personnel of the preparing command in accordance with current directiveson doctrine, policy, essentiality, propriety, and quality. -
7. Transonic Aerodynamics of Airfoils and Wings
W.H. Mason 7. Transonic Aerodynamics of Airfoils and Wings 7.1 Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = 0.6 or 0.7 to 1.2). Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds. This complicates both computations and wind tunnel testing. It also means that there is very little analytic theory available for guidance in designing for transonic flow conditions. Importantly, not only is the outer inviscid portion of the flow governed by nonlinear flow equations, but the nonlinear flow features typically require that viscous effects be included immediately in the flowfield analysis for accurate design and analysis work. Note also that hypersonic vehicles with bow shocks necessarily have a region of subsonic flow behind the shock, so there is an element of transonic flow on those vehicles too. In the days of propeller airplanes the transonic flow limitations on the propeller mostly kept airplanes from flying fast enough to encounter transonic flow over the rest of the airplane. Here the propeller was moving much faster than the airplane, and adverse transonic aerodynamic problems appeared on the prop first, limiting the speed and thus transonic flow problems over the rest of the aircraft. However, WWII fighters could reach transonic speeds in a dive, and major problems often arose. One notable example was the Lockheed P-38 Lightning. Transonic effects prevented the airplane from readily recovering from dives, and during one flight test, Lockheed test pilot Ralph Virden had a fatal accident. -
Introduction to Aerospace Engineering
Introduction to Aerospace Engineering Lecture slides Challenge the future 1 Introduction to Aerospace Engineering Aerodynamics 11&12 Prof. H. Bijl ir. N. Timmer 11 & 12. Airfoils and finite wings Anderson 5.9 – end of chapter 5 excl. 5.19 Topics lecture 11 & 12 • Pressure distributions and lift • Finite wings • Swept wings 3 Pressure coefficient Typical example Definition of pressure coefficient : p − p -Cp = ∞ Cp q∞ upper side lower side -1.0 Stagnation point: p=p t … p t-p∞=q ∞ => C p=1 4 Example 5.6 • The pressure on a point on the wing of an airplane is 7.58x10 4 N/m2. The airplane is flying with a velocity of 70 m/s at conditions associated with standard altitude of 2000m. Calculate the pressure coefficient at this point on the wing 4 2 3 2000 m: p ∞=7.95.10 N/m ρ∞=1.0066 kg/m − = p p ∞ = − C p Cp 1.50 q∞ 5 Obtaining lift from pressure distribution leading edge θ V∞ trailing edge s p ds dy θ dx = ds cos θ 6 Obtaining lift from pressure distribution TE TE Normal force per meter span: = θ − θ N ∫ pl cos ds ∫ pu cos ds LE LE c c θ = = − with ds cos dx N ∫ pl dx ∫ pu dx 0 0 NN Write dimensionless force coefficient : C = = n 1 ρ 2 2 Vc∞ qc ∞ 1 1 p − p x 1 p − p x x = l ∞ − u ∞ C = ()C −C d Cn d d n ∫ pl pu ∫ q c ∫ q c 0 ∞ 0 ∞ 0 c 7 T=Lsin α - Dcosα N=Lcos α + Dsinα L R N α T D V α = angle of attack 8 Obtaining lift from normal force coefficient =α − α =α − α L Ncos T sin cl c ncos c t sin L N T =cosα − sin α qc∞ qc ∞ qc ∞ For small angle of attack α≤5o : cos α ≈ 1, sin α ≈ 0 1 1 C≈() CCdx − () l∫ pl p u c 0 9 Example 5.11 Consider an airfoil with chord length c and the running distance x measured along the chord. -
Effects of Base Shape to Drag at Transonic and Supersonic Speeds by Cfd
DAAAM INTERNATIONAL SCIENTIFIC BOOK 2019 pp. 071-080 Chapter 06 EFFECTS OF BASE SHAPE TO DRAG AT TRANSONIC AND SUPERSONIC SPEEDS BY CFD SERDAREVIC-KADIC, S. & TERZIC, J. Abstract: This work is focused on numerical simulations of air flow around a projectile in order to determine the influence of base shape on the drag coefficient. Simulations are made for transonic and supersonic speeds of air flow. Several shapes of projectile base is considered and the results are compared to drag coefficient of projectile with flat base. Base drag component can be as high as 50% or more of drag and any reduction in base drag can have a large payoff in increased range. Base drag is depended by flow characteristics and geometrical parameters. Influence of base shape to drag coefficient of projectile is studied by commercially CFD code FLUENT. Key words: Drag, Base, Pressure, CFD Authors´ data: Assist. Prof. Dr. Sc. Serdarevic-Kadic S[abina]; Assist. Prof. Dr. Sc. Terzic, J[asmin], Faculty of Mechanical Engineering, University of Sarajevo, Vilsonovo setaliste 9, Sarajevo 71000, Bosnia and Herzegovina, [email protected], [email protected]. This Publication has to be referred as: Serdarevic-Kadic, S[abina] & Terzic, J[asmin] (2019). Effects of Base Shape to Drag at Transonic and Supersonic Speeds by CFD, Chapter 06 in DAAAM International Scientific Book 2019, pp.071-080, B. Katalinic (Ed.), Published by DAAAM International, ISBN 978-3-902734-24-2, ISSN 1726-9687, Vienna, Austria DOI: 10.2507/daaam.scibook.2019.06 071 Serdarevic-Kadic, S. & Terzic, J.: Effects of Base Shape to Drag at Transonic and S.. -
Supersonic Combustion Ramjet: Analysis on Fuel Options
SUPERSONIC COMBUSTION RAMJET: ANALYSIS ON FUEL OPTIONS by Stephanie W. Barone A thesis submitted to the faculty of The University of Mississippi in partial fulfillment of the requirements of the Sally McDonnell Barksdale Honors College. Oxford May 2004 Approved by ___________________________________ Advisor: Dr. Jeffrey Roux ___________________________________ Reader: Dr. Erik Hurlen ___________________________________ Reader: Dr. John O’Haver 1 © 2016 STEPHANIE BARONE ALL RIGHTS RESERVED 2 ABSTRACT STEPHANIE BARONE: Supersonic Combustion Ramjet: Analysis on Fuel Options This report focuses on different fuel options available to use for scramjet engines. The advantages and disadvantages of JP-7, JP-8, and hydrogen fuels are covered, also the effectiveness and requirements for each fuel are discussed. The recent history of the scramjet engine is included as well as its advantages and disadvantages. An explanation of what each fuel option encompasses and engineering analysis for each fuel are shown. The equations presented for the parametric analysis are shown as functions of the freestream Mach number, with the combustion Mach number as a parameter. The results can be seen for the theoretical possibilities of the scramjet engine and the most likely operating situations. Hydrogen has the highest lower heating value which makes it very appealing to use as a fuel, but it is not very dense so more volume of it is needed to create enough energy. The hydrocarbon fuels, JP-7 and JP-8, have half the value of hydrogen for the lower heating value -
After Concorde, Who Will Manage to Revive Civilian Supersonic Aviation?
After Concorde, who will manage to revive civilian supersonic aviation? By François Sfarti and Sebastien Plessis December 2019 Commercial aircraft are flying at the same speed as 60 years ago. Since Concorde, which made possible to fly from Paris to New York in only 3h30, no civilian airplane has broken the sound barrier. The loudness of the sonic boom was a major technological lock to Concorde success, but 50 years after its first flight, an on-going project led by NASA is about to make supersonic flights over land possible. If successful, it will significantly increase the number of supersonic routes and increase the supersonic aircraft market size substantially. This technological improvement combined with R&D efforts on operational costs and a much larger addressable market than when Concorde flew may revive civilian supersonic aviation in the coming years. Who are the new players at the forefront and the early movers? What are the current investments in this field? What are the key success drivers and remaining technological and regulatory locks to revive supersonic aviation? EXECUTIVE SUMMARY Commercial aircraft are typically flying between 800 km/h and 900 km/h, which is between 75% and 85% of the speed of sound. It is the same speed as 60 years ago and since Concorde, which flew at twice the speed of sound, was retired in 2003, there has been no civilian supersonic aircraft in service. Due to a prohibition to fly supersonic over land and large operational costs, Concorde did not reach commercial success. Even if operational costs would remain larger than subsonic flights, current market environment seems much more favourable: since Concorde was retired in 2003, the air traffic has more than doubled and the willingness to pay can be supported by an increase in the number of high net worth individuals and the fact that business travellers value higher speed levels. -
The Cold War and Beyond
Contents Puge FOREWORD ...................... u 1947-56 ......................... 1 1957-66 ........................ 19 1967-76 ........................ 45 1977-86 ........................ 81 1987-97 ........................ 117 iii Foreword This chronology commemorates the golden anniversary of the establishment of the United States Air Force (USAF) as an independent service. Dedicated to the men and women of the USAF past, present, and future, it records significant events and achievements from 18 September 1947 through 9 April 1997. Since its establishment, the USAF has played a significant role in the events that have shaped modem history. Initially, the reassuring drone of USAF transports announced the aerial lifeline that broke the Berlin blockade, the Cold War’s first test of wills. In the tense decades that followed, the USAF deployed a strategic force of nuclear- capable intercontinental bombers and missiles that deterred open armed conflict between the United States and the Soviet Union. During the Cold War’s deadly flash points, USAF jets roared through the skies of Korea and Southeast Asia, wresting air superiority from their communist opponents and bringing air power to the support of friendly ground forces. In the great global competition for the hearts and minds of the Third World, hundreds of USAF humanitarian missions relieved victims of war, famine, and natural disaster. The Air Force performed similar disaster relief services on the home front. Over Grenada, Panama, and Libya, the USAF participated in key contingency actions that presaged post-Cold War operations. In the aftermath of the Cold War the USAF became deeply involved in constructing a new world order. As the Soviet Union disintegrated, USAF flights succored the populations of the newly independent states. -
Section 7, Lecture 3: Effects of Wing Sweep
Section 7, Lecture 3: Effects of Wing Sweep • All modern high-speed aircraft have swept wings: WHY? 1 MAE 5420 - Compressible Fluid Flow • Not in Anderson Supersonic Airfoils (revisited) • Normal Shock wave formed off the front of a blunt leading g=1.1 causes significant drag Detached shock waveg=1.3 Localized normal shock wave Credit: Selkirk College Professional Aviation Program 2 MAE 5420 - Compressible Fluid Flow Supersonic Airfoils (revisited, 2) • To eliminate this leading edge drag caused by detached bow wave Supersonic wings are typically quite sharp atg=1.1 the leading edge • Design feature allows oblique wave to attachg=1.3 to the leading edge eliminating the area of high pressure ahead of the wing. • Double wedge or “diamond” Airfoil section Credit: Selkirk College Professional Aviation Program 3 MAE 5420 - Compressible Fluid Flow Wing Design 101 • Subsonic Wing in Subsonic Flow • Subsonic Wing in Supersonic Flow • Supersonic Wing in Subsonic Flow A conundrum! • Supersonic Wing in Supersonic Flow • Wings that work well sub-sonically generally don’t work well supersonically, and vice-versa à Leading edge Wing-sweep can overcome problem with poor performance of sharp leading edge wing in subsonic flight. 4 MAE 5420 - Compressible Fluid Flow Wing Design 101 (2) • Compromise High-Sweep Delta design generates lift at low speeds • Highly-Swept Delta-Wing design … by increasing the angle-of-attack, works “pretty well” in both flow regimes but also has sufficient sweepback and slenderness to perform very Supersonic Subsonic efficiently at high speeds. • On a traditional aircraft wing a trailing vortex is formed only at the wing tips.