46 Reducing Sonic Boom
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Concorde Is a Museum Piece, but the Allure of Speed Could Spell Success
CIVIL SUPERSONIC Concorde is a museum piece, but the allure Aerion continues to be the most enduring player, of speed could spell success for one or more and the company’s AS2 design now has three of these projects. engines (originally two), the involvement of Air- bus and an agreement (loose and non-exclusive, by Nigel Moll but signed) with GE Aviation to explore the supply Fourteen years have passed since British Airways of those engines. Spike Aerospace expects to fly a and Air France retired their 13 Concordes, and for subsonic scale model of the design for the S-512 the first time in the history of human flight, air trav- Mach 1.5 business jet this summer, to explore low- elers have had to settle for flying more slowly than speed handling, followed by a manned two-thirds- they used to. But now, more so than at any time scale supersonic demonstrator “one-and-a-half to since Concorde’s thunderous Olympus afterburn- two years from now.” Boom Technology is working ing turbojets fell silent, there are multiple indi- on a 55-seat Mach 2.2 airliner that it plans also to cations of a supersonic revival, and the activity offer as a private SSBJ. NASA and Lockheed Martin appears to be more advanced in the field of busi- are encouraged by their research into reducing the ness jets than in the airliner sector. severity of sonic booms on the surface of the planet. www.ainonline.com © 2017 AIN Publications. All Rights Reserved. For Reprints go to Shaping the boom create what is called an N-wave sonic boom: if The sonic boom produced by a supersonic air- you plot the pressure distribution that you mea- craft has long shaped regulations that prohibit sure on the ground, it looks like the letter N. -
Ovrhyp, Scramjet Test Aircraft STATE UNIVERSITY Student Authors: J
https://ntrs.nasa.gov/search.jsp?R=19910000728 2020-03-19T20:21:21+00:00Z /z7 H OVRhyp, Scramjet Test Aircraft STATE UNIVERSITY Student Authors: J. Asian, T. Bisard, S. Dallinga, K. Draper, G. Hufford, W. Peters, and J. Rogers Supervisor: Dr. G. M. Gregorek Assistant: R. L. Reuss Department of Aeronautical & Astronautical Engineering Universities Space Research Association Houston, Texas 77058 Subcontract Dated November 17, 1989 Final Report May 1990 03/0_ OVRhyp, Scramjet Test Aircraft UNIVERSITY Student Authors: J. Asian, T. Bisard, S. Dallinga, K. Draper, G. Hufford, W. Peters, and J. Rogers Supervisor: Dr. G. M. Gregorek Assistant: R. L. Reuss Department of Aeronautical & Astronautical Engineering Universities Space Research Association Houston, Texas 77058 Subcontract Dated November 17, 1989 Final Report RF Project 767919/722941 May 1990 ABSTRACT (Gary Huff0rd} A preliminary design for an unmanned hypersonic research vehicle to test scramjet engines is presented. The aircraft will be launched from a carrier aircraft at an altitude of 4Q,0QQ feet at Mach 0.8. The vehicle will then accelerate to Mach 6 at an altitude of 100,000 feet. At this stage the prototype scramjet will be employed to accelerate the vehicle to Mach 10 and maintain Mach IQ flight for 2 minutes. The aircraft will then decelerate and safely land, presumably at NASA Dryden F[i_ht Test Center. ii TABLE OF CONTENTS ABSTRACT ............................ ii TABLE OF CONTENTS ....................... iii LIST OF FIGURES ......................... v INTRODUCTION .......................... vi CONFIGURATION .......................... WEIGHTS ANALYSIS ........................ 12 PURPOSE ............................. 12 METHOD ........................... 12 SYSTEMS .......................... 14 AERODYNAMIC SURFACES .................... 14 BODY STRUCTURE ....................... 15 THERMAL PROTECTION SYSTEM ................. 15 LAUNCH AND LANDING SYSTEM ................ -
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. -
Some Supersonic Aerodynamics
Some Supersonic Aerodynamics W.H. Mason Configuration Aerodynamics Class Grumman Tribody Concept – from 1978 Company Calendar The Key Topics • Brief history of serious supersonic airplanes – There aren’t many! • The Challenge – L/D, CD0 trends, the sonic boom • Linear theory as a starting point: – Volumetric Drag – Drag Due to Lift • The ac shift and cg control • The Oblique Wing • Aero/Propulsion integration • Some nonlinear aero considerations • The SST development work • Brief review of computational methods • Possible future developments Are “Supersonic Fighters” Really Supersonic? • If your car’s speedometer goes to 120 mph, do you actually go that fast? • The official F-14A supersonic missions (max Mach 2.4) – CAP (Combat Air Patrol) • 150 miles subsonic cruise to station • Loiter • Accel, M = 0.7 to 1.35, then dash 25nm – 4 ½ minutes and 50nm total • Then, head home or to a tanker – DLI (Deck Launch Intercept) • Energy climb to 35K ft., M = 1.5 (4 minutes) • 6 minutes at 1.5 (out 125-130nm) • 2 minutes combat (slows down fast) After 12 minutes, must head home or to a tanker Very few real supersonic airplanes • 1956: the B-58 (L/Dmax = 4.5) – In 1962: Mach 2 for 30 minutes • 1962: the A-12 (SR-71 in ’64) (L/Dmax = 6.6) – 1st supersonic flight, May 4, 1962 – 1st flight to exceed Mach 3, July 20, 1963 • 1964: the XB-70 (L/Dmax = 7.2) – In 1966: flew Mach 3 for 33 minutes • 1968: the TU-144 – 1st flight: Dec. 31, 1968 • 1969: the Concorde (L/Dmax = 7.4) – 1st flight, March 2, 1969 • 1990: the YF-22 and YF-23 (supercruisers) – YF-22: 1st flt. -
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. -
Congress and the Supersonic Transport, 1960-1971 by John
Congress and the supersonic transport, 1960-1971 by John Marion Bell A thesis submitted in partial fulfillment of the requirements for the degree of MASTER OF ARTS in History Montana State University © Copyright by John Marion Bell (1974) Abstract: Aviation state-of-the-art advances in the 1940's and 1950's paved the way for development of a commercial SST in the 1960's. Military aviation advances were translated directly into subsonic transports and it was felt that the next step in progress would be the SST. Through military programs and basic research by NACA, the United States government aided the development of a commercial SST even before undertaking an active SST program in the 1960's. Foreign governments were also at work on SST's and when the British and French merged their development programs in 1962 the United States was spurred by their competition. President Kennedy announced an active program in June, 1963 a day following Pan Am's order of Anglo-French SST's. There was little opposition to the airplane at first; what little there was was based on the aircraft's unavoidable sonic boom. A design competition was conducted by the FAA to select the best possible American design. Boeing was selected the winner in 1966 on the basis of a radical, swing-wing design. The program then entered a two-prototype development stage. Boeing soon ran into development problems and in 1968 abandoned its swing-wing in favor of a conventional fixed-wing. The airplane's problems were also complicated by the great increase in cost of development as well as a growing opposition based on the possible negative environmental impact of the SST. -
On the Ballistic Wave from Projectiles and Vehicles of Simple Geometry Jean Varnier, Marie-Claire Le Pape, Frédéric Sourgen
On the ballistic wave from projectiles and vehicles of simple geometry Jean Varnier, Marie-Claire Le Pape, Frédéric Sourgen To cite this version: Jean Varnier, Marie-Claire Le Pape, Frédéric Sourgen. On the ballistic wave from projectiles and vehicles of simple geometry. AIAA Journal, American Institute of Aeronautics and Astronautics, 2018, 56 (7), pp.2725-2742. 10.2514/1.J056239. hal-01852518 HAL Id: hal-01852518 https://hal.archives-ouvertes.fr/hal-01852518 Submitted on 1 Aug 2018 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. On the ballistic wave from projectiles and vehicles of simple geometry Jean Varnier*, Marie-Claire Le Pape° ONERA, 92320 Châtillon, France Frédéric Sourgen°° ONERA, 31400 Toulouse, France The ballistic wave is a shock wave generated by a solid body moving at supersonic speed in the atmosphere. It sounds like the crack of a whip for small projectiles, like a detonation (sonic boom) for large-sized objects. Their common signature is a N-shaped pressure profile, the formalism of which is well-known but presents a practical difficulty, namely the calculation of the “shape factor” which characterizes the aerodynamic behavior of the object flying at supersonic speed. -
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.. -
Examining Explanations for the Strange Phenomena Encountered by U.S
AIRCRAFT DESIGN 14 LUNAR SPACESUITS 18 SUPERSONICS 36 Perlan 2 glider — explained More fl exibility for astronauts Listening for X-59’s sonic thump Mystery sightings Examining explanations for the strange phenomena encountered by U.S. Navy pilots. PAGE 26 NOVEMBER 2019 | A publication of the American Institute of Aeronautics and Astronautics | aerospaceamerica.aiaa.org The Premier Global, Commercial, Civil, Military and Emergent Space Conference Where Ideas Launch • Connections Are Made • Business Gets Done! SpaceSymposium.org SAVE $600 – Register Today for Best Savings! Special Military Rates! +1.800.691.4000 Share: FEATURES | November 2019 MORE AT aerospaceamerica.aiaa.org The Premier Global, Commercial, Civil, Military and Emergent Space Conference 14 18 36 26 Aiming for Exploring the Planning for 90,000 feet moon in new the sound of Mystery phenomena spacesuits Designers of Perlan 2 supersonic fl ight We look at possible explanations for those overcame formidable Former astronaut How NASA’s Low Boom fast and agile objects zipping across F/A-18 engineering Tom Jones examines Flight Demonstrator screens. challenges to NASA’s plans to give will test the public’s create a glider that explorers suits that tolerance for sonic By Jan Tegler and Cat Hofacker has reached the will let them walk, thumps. stratosphere and will lope, crouch and even try to beat its own kneel. By Jan Tegler record next year. Where Ideas Launch • Connections Are Made • Business Gets Done! By Tom Jones By Keith Button SpaceSymposium.org SAVE $600 – Register Today for -
A High-Fidelity Approach to Conceptual Design John Thomas Watson Iowa State University
Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2016 A high-fidelity approach to conceptual design John Thomas Watson Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Aerospace Engineering Commons, and the Art and Design Commons Recommended Citation Watson, John Thomas, "A high-fidelity approach to conceptual design" (2016). Graduate Theses and Dissertations. 15183. https://lib.dr.iastate.edu/etd/15183 This Thesis is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. A high-fidelity approach to conceptual design by John T. Watson A thesis submitted to the graduate faculty in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Major: Aerospace Engineering Program of Study Committee: Richard Wlezien, Major Professor Thomas Gielda Leifur Leifsson Iowa State University Ames, Iowa 2016 Copyright © John T. Watson, 2016. All rights reserved. ii TABLE OF CONTENTS Page LIST OF FIGURES ................................................................................................... iii LIST OF TABLES ..................................................................................................... v NOMENCLATURE .................................................................................................