Thermal Soaring Flight of Birds and Uavs
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Soaring Weather
Chapter 16 SOARING WEATHER While horse racing may be the "Sport of Kings," of the craft depends on the weather and the skill soaring may be considered the "King of Sports." of the pilot. Forward thrust comes from gliding Soaring bears the relationship to flying that sailing downward relative to the air the same as thrust bears to power boating. Soaring has made notable is developed in a power-off glide by a conven contributions to meteorology. For example, soar tional aircraft. Therefore, to gain or maintain ing pilots have probed thunderstorms and moun altitude, the soaring pilot must rely on upward tain waves with findings that have made flying motion of the air. safer for all pilots. However, soaring is primarily To a sailplane pilot, "lift" means the rate of recreational. climb he can achieve in an up-current, while "sink" A sailplane must have auxiliary power to be denotes his rate of descent in a downdraft or in come airborne such as a winch, a ground tow, or neutral air. "Zero sink" means that upward cur a tow by a powered aircraft. Once the sailcraft is rents are just strong enough to enable him to hold airborne and the tow cable released, performance altitude but not to climb. Sailplanes are highly 171 r efficient machines; a sink rate of a mere 2 feet per second. There is no point in trying to soar until second provides an airspeed of about 40 knots, and weather conditions favor vertical speeds greater a sink rate of 6 feet per second gives an airspeed than the minimum sink rate of the aircraft. -
5.2 Drag Reduction Through Higher Wing Loading David L. Kohlman
5.2 Drag Reduction Through Higher Wing Loading David L. Kohlman University of Kansas |ntroduction The wing typically accounts for almost half of the wetted area of today's production light airplanes and approximately one-third of the total zero-lift or parasite drag. Thus the wing should be a primary focal point of any attempts to reduce drag of light aircraft with the most obvious configuration change being a reduction in wing area. Other possibilities involve changes in thickness, planform, and airfoil section. This paper will briefly discuss the effects of reducing wing area of typical light airplanes, constraints involved, and related configuration changes which may be necessary. Constraints and Benefits The wing area of current light airplanes is determined primarily by stall speed and/or climb performance requirements. Table I summarizes the resulting wing loading for a representative spectrum of single-engine airplanes. The maximum lift coefficient with full flaps, a constraint on wing size, is also listed. Note that wing loading (at maximum gross weight) ranges between about 10 and 20 psf, with most 4-place models averaging between 13 and 17. Maximum lift coefficient with full flaps ranges from 1.49 to 2.15. Clearly if CLmax can be increased, a corresponding decrease in wing area can be permitted with no change in stall speed. If total drag is not increased at climb speed, the change in wing area will not adversely affect climb performance either and cruise drag will be reduced. Though not related to drag, it is worthy of comment that the range of wing loading in Table I tends to produce a rather uncomfortable ride in turbulent air, as every light-plane pilot is well aware. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Guide to the Paul Maccready Innovative Lives Presentation
Guide to the Paul MacCready Innovative Lives Presentation NMAH.AC.0842 Alison Oswald 2003 Archives Center, National Museum of American History P.O. Box 37012 Suite 1100, MRC 601 Washington, D.C. 20013-7012 [email protected] http://americanhistory.si.edu/archives Table of Contents Collection Overview ........................................................................................................ 1 Administrative Information .............................................................................................. 1 Scope and Contents........................................................................................................ 2 Biographical / Historical.................................................................................................... 2 Names and Subjects ...................................................................................................... 2 Container Listing ............................................................................................................. 3 Series : Original Videos (OV 842.1-9), 2002-11-08................................................. 3 Series : Reference Videos, 2002-11-08................................................................... 4 Series 3: Digital images, 2002-11-08....................................................................... 5 Paul MacCready Innovative Lives Presentation NMAH.AC.0842 Collection Overview Repository: Archives Center, National Museum of American History Title: Paul MacCready Innovative Lives Presentation Identifier: -
Download the BHPA Training Guide
VERSION 1.7 JOE SCHOFIELD, EDITOR body, and it has for many years been recognised and respected by the Fédération Aeronautique Internationale, the Royal Aero Club and the Civil Aviation Authority. The BHPA runs, with the help of a small number of paid staff, a pilot rating scheme, airworthiness schemes for the aircraft we fly, a school registration scheme, an instructor assessment and rating scheme and training courses for instructors and coaches. Within your membership fee is also provided third party insurance and, for full annual or three-month training members, a monthly subscription to this highly-regarded magazine. The Elementary Pilot Training Guide exists to answer all those basic questions you have such as: ‘Is it difficult to learn to fly?' and ‘Will it take me long to learn?' In answer to those two questions, I should say that it is no more difficult to learn to fly than to learn to drive a car; probably somewhat easier. We were all beginners once and are well aware that the main requirement, if you want much more than a ‘taster', is commitment. Keep at it and you will succeed. In answer to the second question I can only say that in spite of our best efforts we still cannot control the weather, and that, no matter how long you continue to fly for, you will never stop learning. Welcome to free flying and to the BHPA’s Elementary Pilot Training Guide, You are about to enter a world where you will regularly enjoy sights and designed to help new pilots under training to progress to their first milestone - experiences which only a few people ever witness. -
Hang Glider: Range Maximization the Problem Is to Compute the flight Inputs to a Hang Glider So As to Provide a Maximum Range flight
Hang Glider: Range Maximization The problem is to compute the flight inputs to a hang glider so as to provide a maximum range flight. This problem first appears in [1]. The hang glider has weight W (glider plus pilot), a lift force L acting perpendicular to its velocity vr relative to the air, and a drag force D acting in a direction opposite to vr. Denote by x the horizontal position of the glider, by vx the horizontal component of the absolute velocity, by y the vertical position, and by vy the vertical component of absolute velocity. The airmass is not static: there is a thermal just 250 meters ahead. The profile of the thermal is given by the following upward wind velocity: 2 2 − x −2.5 x u (x) = u e ( R ) 1 − − 2.5 . a m R We take R = 100 m and um = 2.5 m/s. Note, MKS units are used through- out. The upwind profile is shown in Figure 1. Letting η denote the angle between vr and the horizontal plane, we have the following equations of motion: 1 x˙ = vx, v˙x = m (−L sin η − D cos η), 1 y˙ = vy, v˙y = m (L cos η − D sin η − W ) with q vy − ua(x) 2 2 η = arctan , vr = vx + (vy − ua(x)) , vx 1 1 L = c ρSv2,D = c (c )ρSv2,W = mg. 2 L r 2 D L r The glider is controlled by the lift coefficient cL. The drag coefficient is assumed to depend on the lift coefficient as 2 cD(cL) = c0 + kcL where c0 = 0.034 and k = 0.069662. -
IGC Plenary 2005
Agenda of the Annual Meeting of the FAI Gliding Commission To be held in Lausanne, Switzerland on 5th and 6th March 2010 Agenda for the IGC Plenary 2010 Day 1, Friday 5th March 2010 Session: Opening and Reports (Friday 09.15 – 10.45) 1. Opening (Bob Henderson) 1.1 Roll Call (Stéphane Desprez/Peter Eriksen) 1.2 Administrative matters (Peter Eriksen) 1.3 Declaration of Conflicts of Interest 2. Minutes of previous meeting, Lausanne, 6th-7th March 2009 (Peter Eriksen) 3. IGC President’s report (Bob Henderson) 4. FAI Matters (Mr.Stéphane Desprez) 4.1 Update by the Secretary General 5. Finance (Dick Bradley) 5.1 2009 Financial report 5.2 Financial statement and budget 6. Reports not requiring voting 6.1 OSTIV report (Loek Boermans) Please note that reports under Agenda items 6.2, 6.3 and 6.4 are made available on the IGC web-site, and will not necessarily be presented. The Committees and Specialists will be available for questions. 6.2 Standing Committees 6.2.1 Communications and PR Report (Bob Henderson) 6.2.2 Championship Management Committee Report (Eric Mozer) 6.2.3 Sporting Code Committee Report (Ross Macintyre) 6.2.4 Air Traffic, Navigation, Display Systems (ANDS) Report (Bernald Smith) 6.2.5 GNSS Flight Recorder Approval Committee (GFAC) Report (Ian Strachan) 6.2.6 FAI Commission on Airspace and Navigation Systems (CANS) Report (Ian Strachan) Session: Reports from Specialists and Competitions (Friday 11.15 – 12.45) 6.3 Working Groups 6.3.1 Country Development Report (Alexander Georgas) 6.3.2 Grand Prix Action Plan (Bob Henderson) 6.3.3 History Committee (Tor Johannessen) 6.3.4 Scoring Working Group (Visa-Matti Leinikki) 6.4 IGC Specialists 6.4.1 CASI Report (Air Sports Commissions) (Tor Johannessen) 6.4.2 EGU/EASA Report (Patrick Pauwels) 6.4.3 Environmental Commission Report (Bernald Smith) 6.4.4 Membership (John Roake) 6.4.5 On-Line Contest Report (Axel Reich) 6.4.6 Simulated Gliding Report (Roland Stuck) 6.4.7 Trophy Management Report (Marina Vigorita) 6.4.8 Web Management Report (Peter Ryder) 7. -
DR. PAUL MACCREADY September 29, 1925 - August 28, 2007 AMA #626304
The AMA History Project Presents: Biography of DR. PAUL MACCREADY September 29, 1925 - August 28, 2007 AMA #626304 Transcribed & Edited by SS (08/2002); Update by JS (02/2017) Career: . Set many model airplane records . First soloed in a powered plane at age 16 . Flew in the U.S. Navy flight-training program during World War II . 1947: Graduated with a Bachelor of Science degree in physics from Yale University . Won second place in the National Soaring Contest at Wichita Falls, Texas, at age 21 . 1948, 1949, 1953: Won the U.S. National Soaring Championships . Pioneered high-altitude wave soaring in the U.S. 1956: Became the first American to be an international sailplane champion at a meet in France; represented the U.S. in Europe four times . Invented the MacCready speed ring used worldwide by glider pilots . Earned his master’s degree in physics in 1948 and his doctorate degree in aeronautics in 1952, both from the California Institute of Technology . 1971: Started AeroVironment, Inc. Won a few Henry Kremer Prizes for his cutting-edge designs of planes, such as planes powered by human power only . Early 1980s: Developed solar-powered planes . Received various honors and awards and is affiliated with the National Academy of Engineering, the American Academy of Arts and Sciences, the American Institute of Aeronautics and Astronautics and the American Meteorological Society . Served as the international president of the International Human Powered Vehicle Association . Wrote many articles, papers and reports dealing with physics and aeronautics . 2016 AMA Model Aviation Hall of Fame inductee This biography, written in 1986, is stored in the AMA History Project (at the time called the AMA History Program) files. -
Gliding Flight
Gliding Flight Whenever an airplane is flying such that the power required is larger than the power available, it will descend rather than climb. In the ultimate situation, there is no power at all; in this case, the airplane will be in gliding. This will occur for a conventional airplane when the engine quits during flight (e.g., engine failure). Also, this is the case for gliders and sailplanes. The force diagram is the higher the L/D, the shallower the glide angle. The smallest equilibrium glide angle occurs at (L/D)max. The equilibrium glide angle does not depend on altitude or wing loading, it simply depends on the lift-to-drag ratio. However, to achieve a given L/D at a given altitude, the aircraft must fly at a specified velocity V, called the equilibrium glide velocity, and this value of V, does depend on the altitude and wing loading, as follows: it depends on altitude (through rho) and wing loading. The value of CL and L/D are aerodynamic characteristics of the aircraft that vary with angle of attack. A specific value of L/D, corresponds to a specific angle of attack which in turn dictates the lift coefficient (CL). If L/ D is held constant throughout the glide path, then CL is constant along the glide path. However, the equilibrium velocity along this glide path will change with altitude, decreasing with decreasing altitude (because rho increases). SERVICE AND ABSOLUTE CEILINGS The highest altitude achievable is the altitude where (R/C)max=0. It is defined as the absolute ceiling that altitude where the maximum rate of climb is zero is in steady, level flight. -
THE INFRARED CLOUD IMAGER by Brentha Thurairajah a Thesis Submitted in Partial Fulfi
THERMAL INFRARED IMAGING OF THE ATMOSPHERE: THE INFRARED CLOUD IMAGER by Brentha Thurairajah A thesis submitted in partial fulfillment of the requirements of the degree of Master of Science in Electrical Engineering MONTANA STATE UNIVERSITY Bozeman, Montana April 2004 © COPYRIGHT by Brentha Thurairajah 2004 All Rights Reserved ii APPROVAL of a thesis submitted by Brentha Thurairajah This thesis has been read by each member of the thesis committee and has been found to be satisfactory regarding content, English usage, format, citations, bibliographic style, and consistency, and is ready for submission to the college of graduate studies. Dr. Joseph A. Shaw, Chair of Committee Approved for the Department of Electrical and Computer Engineering Dr. James N. Peterson, Department Head Approved for the College of Graduate Studies Dr. Bruce R. McLeod, Graduate Dean iii STATEMENT OF PERMISSION TO USE In presenting this thesis in partial fulfillment of the requirements for a master’s degree at Montana State University, I agree that the Library shall make it available to borrowers under the rules of the Library. If I have indicated my intention to copyright this thesis by including a copyright notice page, copying is allowable only for scholarly purposes, consistent with “fair use” as prescribed in the U.S Copyright Law. Requests for permission for extended quotation from or reproduction of this thesis in whole or in parts may be granted only by the copyright holder. Brentha Thurairajah April 2nd, 2004 iv ACKNOWLEDGEMENT I would like to thank my advisor Dr. Joseph Shaw for always being there, for guiding me with patience throughout the project, for helping me with my course and research work through all these three years, and for providing helpful comments and constructive criticism that helped me complete this document. -
Thermal Equilibrium of the Atmosphere with a Convective Adjustment
jULY 1964 SYUKURO MANABE AND ROBERT F. STRICKLER 361 Thermal Equilibrium of the Atmosphere with a Convective Adjustment SYUKURO MANABE AND ROBERT F. STRICKLER General Circulation Research Laboratory, U.S. Weather Bureau, Washington, D. C. (Manuscript received 19 December 1963, in revised form 13 April 1964) ABSTRACT The states of thermal equilibrium (incorporating an adjustment of super-adiabatic stratification) as well as that of pure radiative equilibrium of the atmosphere are computed as the asymptotic steady state ap proached in an initial value problem. Recent measurements of absorptivities obtained for a wide range of pressure are used, and the scheme of computation is sufficiently general to include the effect of several layers of clouds. The atmosphere in thermal equilibrium has an isothermal lower stratosphere and an inversion in the upper stratosphere which are features observed in middle latitudes. The role of various gaseous absorbers (i.e., water vapor, carbon dioxide, and ozone), as well as the role of the clouds, is investigated by computing thermal equilibrium with and without one or two of these elements. The existence of ozone has very little effect on the equilibrium temperature of the earth's surface but a very important effect on the temperature throughout the stratosphere; the absorption of solar radiation by ozone in the upper and middle strato sphere, in addition to maintaining the warm temperature in that region, appears also to be necessary for the maintenance of the isothermal layer or slight inversion just above the tropopause. The thermal equilib rium state in the absence of solar insolation is computed by setting the temperature of the earth's surface at the observed polar value. -
ESSENTIALS of METEOROLOGY (7Th Ed.) GLOSSARY
ESSENTIALS OF METEOROLOGY (7th ed.) GLOSSARY Chapter 1 Aerosols Tiny suspended solid particles (dust, smoke, etc.) or liquid droplets that enter the atmosphere from either natural or human (anthropogenic) sources, such as the burning of fossil fuels. Sulfur-containing fossil fuels, such as coal, produce sulfate aerosols. Air density The ratio of the mass of a substance to the volume occupied by it. Air density is usually expressed as g/cm3 or kg/m3. Also See Density. Air pressure The pressure exerted by the mass of air above a given point, usually expressed in millibars (mb), inches of (atmospheric mercury (Hg) or in hectopascals (hPa). pressure) Atmosphere The envelope of gases that surround a planet and are held to it by the planet's gravitational attraction. The earth's atmosphere is mainly nitrogen and oxygen. Carbon dioxide (CO2) A colorless, odorless gas whose concentration is about 0.039 percent (390 ppm) in a volume of air near sea level. It is a selective absorber of infrared radiation and, consequently, it is important in the earth's atmospheric greenhouse effect. Solid CO2 is called dry ice. Climate The accumulation of daily and seasonal weather events over a long period of time. Front The transition zone between two distinct air masses. Hurricane A tropical cyclone having winds in excess of 64 knots (74 mi/hr). Ionosphere An electrified region of the upper atmosphere where fairly large concentrations of ions and free electrons exist. Lapse rate The rate at which an atmospheric variable (usually temperature) decreases with height. (See Environmental lapse rate.) Mesosphere The atmospheric layer between the stratosphere and the thermosphere.