Concorde Is a Museum Piece, but the Allure of Speed Could Spell Success
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A Nation of Aviation Pioneers
ICAO TIE-INS By Albert Pelsser Romania - A nation of aviation pioneers At the beginning of the 20th century, Romania was among the few nations in the world which brought essential contributions to aviation and flying because there were people who dedicated their life and work to fulfilling the human desire to fly and developing aviation. Among the most well-known inventors who contributed to the flight development by means of apparatuses heavier than the air, Traian Vuia, Aurel Vlaicu and Henri Coanda played a distinct role. In parallel to the above developments, schools of piloting were established and airships from other countries were purchased, with provision for specially designed workshops for the maintenance and repairing of aircraft. The first school of piloting was initiated by the Romanian lawyer Mihail Cerchez, after his return from Paris in the summer of 1909. It started its activity in the spring of 1910, on the field near Chitila, where the first aerodrome of the Romanian aviation was settled. Once the infrastructure for the construction and repair of the airships had been completed, Mihail Cerchez purchased four aircraft from France: two biplane Farman aircraft that were intended to carrying out the training flights of the future pilots, one Demoiselle aircraft and a Wright aircraft for the ground instruction. Second Lieutenants Ştefan Protopopescu and Gheorghe Negrescu were among the first six military pilots trained. Cerchez also obtained that the Farman aircraft be assembled in his workshops. Chitila’s infrastructure in 1911. Farman IV biplane. Having obtained their Pilot Licences in July 2011, Protopopescu and Negrescu, along with other pilots, participated in military maneuvers on Farmans in the fall of 1911 and carried out a series of raids to popularize aviation among youth and to maintain a high degree of readiness among pilots. -
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 ................ -
Flight International – July 2021.Pdf
FlightGlobal.com July 2021 RISE of the open rotor Airbus, Boeing cool subsidies feud p12 Home US Air Force studies advantage resupply rockets p28 MC-21 leads Russian renaissance p44 9 770015 371327 £4.99 Sonic gloom Ton up Investors A400M gets pull plug a lift with on Aerion 100th delivery 07 p30 p26 Comment All together now Green shoots Irina Lavrishcheva/Shutterstock While CFM International has set out its plan to deliver a 20% fuel saving from its next engine, only the entire aviation ecosystem working in concert can speed up decarbonisation ohn Slattery, the GE Aviation restrictions, the RISE launch event governments have a key role to chief executive, has many un- was the first time that Slattery and play here through incentivising the doubted skills, but perhaps his Safran counterpart, Olivier An- production and use of SAF; avia- the least heralded is his abil- dries, had met face to face since tion must influence policy, he said. Jity to speak in soundbites while they took up their new positions. It He also noted that the engine simultaneously sounding natural. was also just a week before what manufacturers cannot do it alone: It is a talent that politicians yearn would have been the first day of airframers must also drive through for, but which few can master; the Paris air show – the likely launch aerodynamic and efficiency im- frequently the individual simply venue for the RISE programme. provements for their next-genera- sounds stilted, as though they were However, out of the havoc tion products. reading from an autocue. -
Feeling Supersonic
FlightGlobal.com May 2021 How Max cuts hurt Boeing backlog Making throwaway Feeling aircraft aff ordable p32 Hydrogen switch for Fresson’s Islander p34 supersonic Will Overture be in tune with demand? p52 9 770015 371327 £4.99 Big worries Warning sign We assess A380 Why NOTAM outlook as last burden can delivery looms baffl e pilots 05 p14 p22 Comment Prospects receding Future dreaming Once thought of as the future of air travel, the A380 is already heading into retirement, but aviation is keenly focused on the next big thing Airbus t has been a rapid rise and fall for on who you ask. As we report else- Hydrogen is not without its the Airbus A380, which not so where in this issue, there are those issues, of course, but nonethe- long ago was being hailed as the banking on supersonic speeds be- less it appears more feasible as a future of long-haul air travel. ing the answer. power source for large transport IThe superjumbo would be, The likes of Aerion and Boom Su- aircraft than batteries do at pres- forecasts said, the perfect tool for personic view the ability to shave ent, even allowing for improving airlines operating into mega-hubs significant time from journeys as a energy densities. such as Dubai that were beginning unique selling point. However, there are others who to spring up. While projects are likely to be see hydrogen through a differ- But the planners at Airbus failed technologically feasible, to be able ent filter. They argue that so- to take into consideration the to sell these new aircraft in signif- called sub-regional aircraft – the efficiency gains available from icant volumes their manufacturers Britten-Norman Islander, among a new generation of widebody will have to ensure that supersonic others – can be given fresh impetus twinjets that allowed operators to flight is not merely the domain of if a fuel source can be found that is open up previously uneconomical the ultra-rich. -
The Economics of the UK Aerospace Industry: a Transaction Cost Analysis
The economics of the UK aerospace industry: A transaction cost analysis of defence and civilian firms Ian Jackson PhD Department of Economics and Related Studies University of York 2004 Abstract The primaryaim of this thesisis to assessvertical integration in the UK aerospace industrywith a transactioncost approach. There is an extensivetheoretical and conceptualliterature on transactioncosts, but a relativelack of empiricalwork. This thesisapplies transaction cost economics to the UK aerospaceindustry focusing on the paradigmproblem of the make-or-buydecision and related contract design. It assesses whetherthe transactioncost approachis supported(or rejected)by evidencefrom an originalsurvey of theUK aerospaceindustry. The centralhypothesis is that UK aerospacefirms are likely to makecomponents in- housedue to higherlevels of assetspecificity, uncertainty, complexity, frequency and smallnumbers, which is reflectedin contractdesign. The thesismakes these concepts operational.The empiricalmethodology of the thesisis basedon questionnairesurvey dataand econometric tests using Ordinary Least Squares (OLS) andlogit regressions to analysethe make-or-buy decision and the choiceof contracttype. The resultsfrom this thesisfind limited evidencein supportof the transactioncost approachapplied to the UK aerospaceindustry, in spiteof a bespokedataset. The empiricaltests of verticalintegration for both make-or-buyand contracttype as the dependentvariable yield insufficientevidence to concludethat the transactioncost approachis an appropriateframework -
W Oltoria Di Un Uo Non Man at Taman Antonio La D
W OLTORIA DI UN USUO NON20180134382A1 MAN AT TAMAN ANTONIOLA D ( 19) United States (12 ) Patent Application Publication ( 10) Pub . No. : US 2018 /0134382 A1 Scholl et al. (43 ) Pub . Date : May 17 , 2018 ( 54 ) COMMERCIAL SUPERSONIC AIRCRAFT Publication Classification AND ASSOCIATED SYSTEMS AND (51 ) Int. Cl. METHODS B64C 30 / 00 (2006 .01 ) B64D 13 /08 ( 2006 . 01) ( 71) Applicant: Boom Technology, Inc. , Englewood , B64D 43 / 00 (2006 . 01 ) CO (US ) B64D 11 /06 ( 2006 .01 ) (72 ) Inventors : Nathaniel Blake Scholl, Englewood , (52 ) U . S . CI. CO (US ) ; Joe Wilding, Englewood , CO CPC . .. .. B64C 30 / 00 ( 2013 .01 ) ; B64D 13 / 08 (US ) ; Josh Krall, Englewood , CO (2013 .01 ) ; B64D 2013 /0618 (2013 .01 ) ; B64D (US ) ; Andy Berryann , Englewood , CO 11 / 064 (2014 . 12 ); B64D 43 / 00 ( 2013 .01 ) (US ) ; Michael Reid , Englewood , CO (US ) (57 ) ABSTRACT Commercial supersonic aircraft and associated systems and ( 21 ) Appl. No. : 15 /811 ,327 methods . A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between ( 22 ) Filed : Nov . 13 , 2017 20 and 60 passengers, a delta wing mounted to the fuselage , and a propulsion system carried by at least one of the wing Related U . S . Application Data and the fuselage , the propulsion system including a plurality (60 ) Provisional application No . 62 /421 , 870 , filed on Nov . of engines , at least one variable - geometry inlet , and at least 14 , 2016 . one variable - geometry nozzle . 101 103 100 102 51216 Chen 110 - - - - 000000 - - -
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. -
Make America Boom Again: How to Bring Back Supersonic Transport,” Eli Dourado and Samuel Hammond Show That It Is Time to Revisit the Ban
MAKE AMERICA BOOM AGAIN How to Bring Back Supersonic Transport _____________________ In 1973, the Federal Aviation Administration (FAA) banned civil supersonic flight over the United States, stymieing the development of a supersonic aviation industry. In “Make America Boom Again: How to Bring Back Supersonic Transport,” Eli Dourado and Samuel Hammond show that it is time to revisit the ban. Better technology—including better materials, engines, and simulation capabilities—mean it is now possible to produce a supersonic jet that is more economical and less noisy than those of the 1970s. It is time to rescind the ban in favor of a more modest and sensible noise standard. BACKGROUND Past studies addressing the ban on supersonic flight have had little effect. However, this paper takes a comprehensive view of the topic, covering the history of supersonic flight, the case for supersonic travel, the problems raised by supersonic flight, and regulatory alternatives to the ban. Dourado and Hammond synthesize the best arguments for rescinding the ban on supersonic flights over land and establish that the ban has had a real impact on the development of supersonic transport. KEY FINDINGS The FAA Should Replace the Ban on Overland Supersonic Flight with a Noise Standard The sonic boom generated by the Concorde and other early supersonic aircraft was very loud, and as a result the FAA banned flights in the United States from going faster than the speed of sound (Mach 1). This ban should be rescinded and replaced with a noise standard. A noise limit of 85–90 A-weighted decibels would be similar to noise standards for lawnmowers, blenders, and motorcy- cles, and would therefore be a reasonable standard during daytime hours. -
2. Afterburners
2. AFTERBURNERS 2.1 Introduction The simple gas turbine cycle can be designed to have good performance characteristics at a particular operating or design point. However, a particu lar engine does not have the capability of producing a good performance for large ranges of thrust, an inflexibility that can lead to problems when the flight program for a particular vehicle is considered. For example, many airplanes require a larger thrust during takeoff and acceleration than they do at a cruise condition. Thus, if the engine is sized for takeoff and has its design point at this condition, the engine will be too large at cruise. The vehicle performance will be penalized at cruise for the poor off-design point operation of the engine components and for the larger weight of the engine. Similar problems arise when supersonic cruise vehicles are considered. The afterburning gas turbine cycle was an early attempt to avoid some of these problems. Afterburners or augmentation devices were first added to aircraft gas turbine engines to increase their thrust during takeoff or brief periods of acceleration and supersonic flight. The devices make use of the fact that, in a gas turbine engine, the maximum gas temperature at the turbine inlet is limited by structural considerations to values less than half the adiabatic flame temperature at the stoichiometric fuel-air ratio. As a result, the gas leaving the turbine contains most of its original concentration of oxygen. This oxygen can be burned with additional fuel in a secondary combustion chamber located downstream of the turbine where temperature constraints are relaxed. -
A Statistical Analysis of Commercial Aviation Accidents 1958-2019
Airbus A Statistical Analysis of Commercial Aviation Accidents 1958-2019 Contents Scope and definitions 02 1.0 2020 & beyond 05 Accidents in 2019 07 2020 & beyond 08 Forecast increase in number of aircraft 2019-2038 09 2.0 Commercial aviation accidents since the advent of the jet age 10 Evolution of the number of flights & accidents 12 Evolution of the yearly accident rate 13 Impact of technology on aviation safety 14 Technology has improved aviation safety 16 Evolution of accident rates by aircraft generation 17 3.0 Commercial aviation accidents over the last 20 years 18 Evolution of the yearly accident rate 20 Ten year moving average of accident rate 21 Accidents by flight phase 22 Distribution of accidents by accident category 24 Evolution of the main accident categories 25 Controlled Flight Into Terrain (CFIT) accident rates 26 Loss Of Control In-flight (LOC-I) accident rates 27 Runway Excursion (RE) accident rates 28 List of tables & graphs 29 A Statistical Analysis of Commercial Aviation Accidents 1958 / 2019 02 Scope and definitions This publication provides Airbus’ a flight in a commercial aircraft annual analysis of aviation accidents, is a low risk activity. with commentary on the year 2019, Since the goal of any review of aviation as well as a review of the history of accidents is to help the industry Commercial Aviation’s safety record. further enhance safety, an analysis This analysis clearly demonstrates of forecasted aviation macro-trends that our industry has achieved huge is also provided. These highlight key improvements in safety over the factors influencing the industry’s last decades. -
For the Full Potential Equation of Transonic Flow*
MATHEMATICS OF COMPUTATION VOLUME 44, NUMBER 169 JANUARY 1985, PAGES 1-29 Entropy Condition Satisfying Approximations for the Full Potential Equation of Transonic Flow* By Stanley Osher, Mohamed Hafez and Woodrow Whitlow, Jr. Abstract. We shall present a new class of conservative difference approximations for the steady full potential equation. They are, in general, easier to program than the usual density biasing algorithms, and in fact, differ only slightly from them. We prove rigorously that these new schemes satisfy a new discrete "entropy inequality", which rules out expansion shocks, and that they have sharp, steady, discrete shocks. A key tool in our analysis is the construction of an "entropy inequality" for the full potential equation itself. We conclude by presenting results of some numerical experiments using our new schemes. I. Introduction. The full potential equation is a common model for describing supersonic and subsonic flow close to the speed of sound. The flow is assumed to be that of a perfect gas, and the assumptions of irrotationality and constant entropy are made. The resulting equation is a single nonlinear partial differential equation of second order, which changes type from hyperbolic to elliptic, as the flow goes from supersonic to subsonic. Flows with a supersonic component generally have solutions with shocks, so the conservation form of the equation is important. This formulation, (FP), is one of three conservative formulations used for inviscid transonic flows. The other two are transonic small-disturbance equation, (TSD), and Euler equation, (EU), which is the exact inviscid formulation. The FP formulation is the most efficient of the three in terms of accuracy-to-cost ratio for a wide range of inviscid transonic flow applications for real geometries. -
Mathematical Problems in Transonic Flow
Canad. Math. Bull. Vol. 29 (2), 1986 MATHEMATICAL PROBLEMS IN TRANSONIC FLOW BY CATHLEEN SYNGE MORAWETZ ABSTRACT. We present an outline of the problem of irrotational com pressible flow past an airfoil at speeds that lie somewhere between those of the supersonic flight of the Concorde and the subsonic flight of commercial airlines. The problem is simplified and the important role of modifying the equations with physics terms is examined. The subject of my talk is transonic flow. But before I can talk about transonics I must talk about flight in general. There are two ways of staying off the ground -— by rocket propulsion (the Buck Rogers mode) or by using the forces that permit gliding or for that matter sailing. Every form of man's flight is some compromise between these two extremes. The one that most mathematicians begin their learning on is incompressible, steady (no time dependence), irrotational, flow governed by (i) Conservation of mass with q the velocity, (what goes in comes out) div q = 0, (ii) Irrotationality, curl q = 0. The pressure is given by Bernoulli's law, p = p(\q\). These equations are equivalent to the Cauchy-Riemann equations and so lots of problems can be solved. But there is an anomaly — there is no drag and for that matter often no lift i.e. no net force on the object which for our purposes and from here on is a cross section of a wing. By taking a nonsymmetric cross section that has a cusp at the end and requiring that the flow has a finite velocity we obtain a flow with lift but still no drag.