Glider Handbook: Glossary and Index
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Fog and Low Clouds As Troublemakers During Wildfi Res
When Our Heads Are in the Clouds Sometimes water droplets do not freeze in below- Detecting fog from space Up to 60,000 ft (18,000m) freezing temperatures. This happens if they do not have Weather satellites operated by the National Oceanic The fog comes a surface (like a dust particle or an ice crystal) upon and Atmospheric Administration (NOAA) collect data on on little cat feet. which to freeze. This below-freezing liquid water becomes clouds and storms. Cirrus Commercial Jetliner “supercooled.” Then when it touches a surface whose It sits looking (36,000 ft / 11,000m) temperature is below freezing, such as a road or sidewalk, NOAA operates two different types of satellites. over harbor and city Geostationary satellites orbit at about 22,236 miles Breitling Orbiter 3 the water will freeze instantly, making a super-slick icy on silent haunches (34,000 ft / 10,400m) Cirrocumulus coating on whatever it touches. This condition is called (35,786 kilometers) above sea level at the equator. At this and then moves on. Mount Everest (29,035 ft / 8,850m) freezing fog. altitude, the satellite makes one Earth orbit per day, just Carl Sandburg Cirrostratus as Earth rotates once per day. Thus, the satellite seems to 20,000 feet (6,000 m) Cumulonimbus hover over one spot below and keeps its “birds’-eye view” of nearly half the Earth at once. Altocumulus The other type of NOAA satellites are polar satellites. Their orbits pass over, or nearly over, the North and South Clear and cloudy regions over the U.S. -
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. -
Ff 89/6 Copy
$3 vol libre • free flight 6/89 Dec - Jan POTPOURRI SAC was informed by Sport Canada on the 10th of July that we are not eligible for funding for 1989-90 and until further notice. Thus we are now totally on our own. The average yearly grant from 1979 to 1988 in 1989 dollars was $14,000, or $16 per person. Perhaps it’s a good thing as planning in an atmosphere of doubt is not conducive to good health and efficient use of funds. The cutback was not unexpected and steps were taken early on to ease the effects of this loss of revenue. Imaginative planning in our small store and a good response from our members through the use of the “Soaring Stuff” inserts resulted in in- creased sales. We will also receive higher than projected invest- ment income essentially due to careful cash management and short-term interest rates, which have remained higher for longer than generally expected. In addition, a small gain in projected receipts from an unexpected increase in membership – now at 1423 – which is the first time since 1982 that we have passed 1400. Total expenditures should come in well below budget projection, primarily as a result of scaling back meetings and travel expenditures. On balance it seems fair to say that a combination of some tight fistedness on the expenditure side and a bit of luck on the revenue side will leave SAC in a financially stronger position than was expected at the beginning of the season, despite the cutting off of govern- ment funding. -
Aviation Glossary
AVIATION GLOSSARY 100-hour inspection – A complete inspection of an aircraft operated for hire required after every 100 hours of operation. It is identical to an annual inspection but may be performed by any certified Airframe and Powerplant mechanic. Absolute altitude – The vertical distance of an aircraft above the terrain. AD - See Airworthiness Directive. ADC – See Air Data Computer. ADF - See Automatic Direction Finder. Adverse yaw - A flight condition in which the nose of an aircraft tends to turn away from the intended direction of turn. Aeronautical Information Manual (AIM) – A primary FAA publication whose purpose is to instruct airmen about operating in the National Airspace System of the U.S. A/FD – See Airport/Facility Directory. AHRS – See Attitude Heading Reference System. Ailerons – A primary flight control surface mounted on the trailing edge of an airplane wing, near the tip. AIM – See Aeronautical Information Manual. Air data computer (ADC) – The system that receives and processes pitot pressure, static pressure, and temperature to present precise information in the cockpit such as altitude, indicated airspeed, true airspeed, vertical speed, wind direction and velocity, and air temperature. Airfoil – Any surface designed to obtain a useful reaction, or lift, from air passing over it. Airmen’s Meteorological Information (AIRMET) - Issued to advise pilots of significant weather, but describes conditions with lower intensities than SIGMETs. AIRMET – See Airmen’s Meteorological Information. Airport/Facility Directory (A/FD) – An FAA publication containing information on all airports, seaplane bases and heliports open to the public as well as communications data, navigational facilities and some procedures and special notices. -
Glider Handbook, Chapter 2: Components and Systems
Chapter 2 Components and Systems Introduction Although gliders come in an array of shapes and sizes, the basic design features of most gliders are fundamentally the same. All gliders conform to the aerodynamic principles that make flight possible. When air flows over the wings of a glider, the wings produce a force called lift that allows the aircraft to stay aloft. Glider wings are designed to produce maximum lift with minimum drag. 2-1 Glider Design With each generation of new materials and development and improvements in aerodynamics, the performance of gliders The earlier gliders were made mainly of wood with metal has increased. One measure of performance is glide ratio. A fastenings, stays, and control cables. Subsequent designs glide ratio of 30:1 means that in smooth air a glider can travel led to a fuselage made of fabric-covered steel tubing forward 30 feet while only losing 1 foot of altitude. Glide glued to wood and fabric wings for lightness and strength. ratio is discussed further in Chapter 5, Glider Performance. New materials, such as carbon fiber, fiberglass, glass reinforced plastic (GRP), and Kevlar® are now being used Due to the critical role that aerodynamic efficiency plays in to developed stronger and lighter gliders. Modern gliders the performance of a glider, gliders often have aerodynamic are usually designed by computer-aided software to increase features seldom found in other aircraft. The wings of a modern performance. The first glider to use fiberglass extensively racing glider have a specially designed low-drag laminar flow was the Akaflieg Stuttgart FS-24 Phönix, which first flew airfoil. -
Solar Energy Generation Model for High Altitude Long Endurance Platforms
Solar Energy Generation Model for High Altitude Long Endurance Platforms Mathilde Brizon∗ KTH - Royal Institute of Technology, Stockholm, Sweden For designing and evaluating new concepts for HALE platforms, the energy provided by solar cells is a key factor. The purpose of this thesis is to model the electrical power which can be harnessed by such a platform along any flight trajectory for different aircraft designs. At first, a model of the solar irradiance received at high altitude will be performed using the solar irradiance models already existing for ground level applications as a basis. A calculation of the efficiency of the energy generation will be performed taking into account each solar panel's position as well as shadows casted by the aircraft's structure. The evaluated set of trajectories allows a stationary positioning of a hale platform with varying wind conditions, time of day and latitude for an exemplary aircraft configuration. The qualitative effects of specific parameter changes on the harnessed solar energy is discussed as well as the fidelity of the energy generation model results. Nomenclature δ Solar declination ({) EQE Quantum efficiency (%) η Efficiency (%) hg Altitude of the aircraft (m) ◦ Γ Day angle ( ) hO3 Height of max ozone concentration(m) ◦ −2 −1 λg Longitude aircraft ( ) Id Direct irradiance (W:m .µm ) ◦ −2 −1 ! Hour angle ( ) Is Diffuse irradiance (W:m .µm ) ◦ −2 −1 φg Latitude of the aircraft ( ) Itot Total irradiance (W:m .µm ) ◦ −1 ◦ τ Rayleigh optical depth ({) kPmax;T Temperature Coefficient (%: C ) 2 A Solar cell -
1 the Atmosphere of Pluto As Observed by New Horizons G
The Atmosphere of Pluto as Observed by New Horizons G. Randall Gladstone,1,2* S. Alan Stern,3 Kimberly Ennico,4 Catherine B. Olkin,3 Harold A. Weaver,5 Leslie A. Young,3 Michael E. Summers,6 Darrell F. Strobel,7 David P. Hinson,8 Joshua A. Kammer,3 Alex H. Parker,3 Andrew J. Steffl,3 Ivan R. Linscott,9 Joel Wm. Parker,3 Andrew F. Cheng,5 David C. Slater,1† Maarten H. Versteeg,1 Thomas K. Greathouse,1 Kurt D. Retherford,1,2 Henry Throop,7 Nathaniel J. Cunningham,10 William W. Woods,9 Kelsi N. Singer,3 Constantine C. C. Tsang,3 Rebecca Schindhelm,3 Carey M. Lisse,5 Michael L. Wong,11 Yuk L. Yung,11 Xun Zhu,5 Werner Curdt,12 Panayotis Lavvas,13 Eliot F. Young,3 G. Leonard Tyler,9 and the New Horizons Science Team 1Southwest Research Institute, San Antonio, TX 78238, USA 2University of Texas at San Antonio, San Antonio, TX 78249, USA 3Southwest Research Institute, Boulder, CO 80302, USA 4National Aeronautics and Space Administration, Ames Research Center, Space Science Division, Moffett Field, CA 94035, USA 5The Johns Hopkins University Applied Physics Laboratory, Laurel, MD 20723, USA 6George Mason University, Fairfax, VA 22030, USA 7The Johns Hopkins University, Baltimore, MD 21218, USA 8Search for Extraterrestrial Intelligence Institute, Mountain View, CA 94043, USA 9Stanford University, Stanford, CA 94305, USA 10Nebraska Wesleyan University, Lincoln, NE 68504 11California Institute of Technology, Pasadena, CA 91125, USA 12Max-Planck-Institut für Sonnensystemforschung, 37191 Katlenburg-Lindau, Germany 13Groupe de Spectroscopie Moléculaire et Atmosphérique, Université Reims Champagne-Ardenne, 51687 Reims, France *To whom correspondence should be addressed. -
The Expected Wave-Off by Richard Carlson SSF Chairman
The Expected Wave-Off by Richard Carlson SSF Chairman The February morning was bright and clear, just as the forecast had predicted. It was a perfect day to go out to the glider school and knock some rust off and beat those Chicago winter blues. With the forecast for temperatures in the low 40’s and no snow on the grass runway, a group of us made arrangements to meet Saturday morning for some winter flying. Nobody expected thermals, and we were not disappointed flying only sled rides in our trusty Blanik L-13. We all pitched in to ready the glider for flight, doing the pre-flight inspection and securing the rear seat belts as everyone was going solo to get current. Today our Green Citrabria would be doing the towing duties. It was pre-heated, started and test flown, all systems go. My turn finally arrived and I eagerly climbed into the front seat, buckled up , ran the flow, and conducted the checklist. The lack of an electrical system meant no radio or audio vario, just basic analog gauges for Airspeed, Altitude, and Vario - Check. Belts on and adjusted, rear seat belts fastened to avoid any fouling of the controls - Check. No ballast installed and none required – Check. Flaps and Dive brakes closed and handles in the lock detent, stick and rudder pedals free travel in all directions, trim set for take-off – Check. Towplane in position, no knots in the rope, proper towring attached and verified – Check. Canopy close and locked, vents open to keep it from fogging over – Check. -
20150014387.Pdf
General Disclaimer One or more of the Following Statements may affect this Document • This document has been reproduced from the best copy furnished by the organizational source. It is being released in the interest of making available as much information as possible. • This document may contain data, which exceeds the sheet parameters. It was furnished in this condition by the organizational source and is the best copy available. • This document may contain tone-on-tone or color graphs, charts and/or pictures, which have been reproduced in black and white. • This document is paginated as submitted by the original source. • Portions of this document are not fully legible due to the historical nature of some of the material. However, it is the best reproduction available from the original submission. Produced by the NASA Center for Aerospace Information (CASI) MR No. I.6F25 . 1' I FILE NJ.TIO AL ADVIS' c~e FYAEBJJNAUTICS • I DBE AODR ED MEMORANDUY REPORT f ~. S1 'i; T, . ·, FO AE O Aur, ~~r'N1£"lt"1'2S;,-' D', • 'hA for the 1 J lo Qf.;t~Ol '.) \ ec \o H' ~ e 'J Ctars if,(" t> Air Materiel Command, Army Air Forces 0 ~ Le,._ \2.(, r e,uvikl TF.STS OF A 1/S-SCALE MODEL OF THE REPUBLIC . ~ Le..\-W c~u J . XP-84 AIRPLANE (ARMY PROJECT MX-$78) IN THE (sco 0 /\cl \C()~{ ~ 'f"u/\.L I~ > .... r u... '1 rro~ -r , v" u LAWLEY 300 MPH 7- BY 10-Foor TUNNEL S:. n By Warren A.. Tucker a:rxi Kenneth W. -
Oxygen Systems
OXYGEN SYSTEMS AEROX HIGH-DURATION AVIATION AEROX PRO-O2 EMERGENCY OXYGEN SYSTEMS HANDHELD OXYGEN SYSTEMS Add to your flying comfort by using oxygen Provides oxygen until the aircraft can reach a lower at altitudes as low as 5000 ft. Aerox Oxygen altitude. And because Pro-O2 is refillable, there is no CM Systems include lightweight aluminum cyl in- need to purchase replacement O2 cartridges. During ders, regulators, all hardware, flow meter, short flights at altitudes between 12,500ft. MSL and and nasal cannulas (masks available as 14,000ft. MSL where maneuvering over mountains or turbulent weather option). Oxysaver oxygen saving cannulas is necessary, the Pro-O2 emergency handheld oxygen system provides & Aerox Flow Control Regulators increase oxygen to extend these brief legs. Included with the refillable Pro-O2 is WP the duration of oxygen supply about 4 times, a regulator with gauge, mask and a refillable cylinder. and prevent nasal irritation and dryness. Pro-O2-2 (2 Cu. Ft./1 mask)........................P/N 13-02735 .........$328.00 Aerox 2D Aerox 4M Complete brochure available on request. Pro-O2-4 (2 Cu. Ft./2 masks) ......................P/N 13-02736 .........$360.00 system system AEROX EMT-3 PORTABLE 500 SERIES REGULATOR – AN AIRCRAFT SPRUCE EXCLUSIVE! OXYGEN SYSTEM ME A small portable system designed for the occasional user • Low profile who wants something smaller and less costly than a full • 1, 2, & 4 place portable system. The EMT-3 is also ideal for use as an • Standard Aircraft filler for easy filling emergency oxygen system. The system lasts 25 minutes at • Convenient top mounted ON/OFF valve 2.5 LPM @ 25,000 FT. -
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 -
F—18 Navy Air Combat Fighter
74 /2 >Af ^y - Senate H e a r tn ^ f^ n 12]$ Before the Committee on Appro priations (,() \ ER WIIA Storage ime nts F EB 1 2 « T H e -,M<rUN‘U«sni KAN S A S S F—18 Na vy Air Com bat Fighter Fiscal Year 1976 th CONGRESS, FIRS T SES SION H .R . 986 1 SPECIAL HEARING F - 1 8 NA VY AIR CO MBA T FIG H TER HEARING BEFORE A SUBC OMMITTEE OF THE COMMITTEE ON APPROPRIATIONS UNITED STATES SENATE NIN ETY-FOURTH CONGRESS FIR ST SE SS IO N ON H .R . 9 8 6 1 AN ACT MAKIN G APP ROPR IA TIO NS FO R THE DEP ARTM EN T OF D EFEN SE FO R T H E FI SC AL YEA R EN DI NG JU N E 30, 1976, AND TH E PE RIO D BE GIN NIN G JU LY 1, 1976, AN D EN DI NG SEPT EM BER 30, 1976, AND FO R OTH ER PU RP OSE S P ri nte d fo r th e use of th e Com mittee on App ro pr ia tio ns SPECIAL HEARING U.S. GOVERNM ENT PRINT ING OFF ICE 60-913 O WASHINGTON : 1976 SUBCOMMITTEE OF THE COMMITTEE ON APPROPRIATIONS JOHN L. MCCLELLAN, Ark ans as, Chairman JOH N C. ST ENN IS, Mississippi MILTON R. YOUNG, No rth D ako ta JOH N O. P ASTORE, Rhode Island ROMAN L. HRUSKA, N ebraska WARREN G. MAGNUSON, Washin gton CLIFFORD I’. CASE, New Je rse y MIK E MANSFIEL D, Montana HIRAM L.