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Topic: Thrust to weight ratio

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	Thrust to Weight Ratio (Site not responding. Last check: 2007-10-09)
		The weight of an airplane is determined by the size and materials used in the airplane's construction and on the payload and fuel that the airplane carries.
		The weight is directly proportional to the mass, and the thrust is the major component of the external force.
		Thrust to weight ratios for engines are often quoted at sea level static conditions, which give the maximum value that the engine will produce.
	www.grc.nasa.gov /WWW/K-12/cdtemp/airplane/fwrat.html (383 words)

	Thrust-to-weight ratio - Wikipedia, the free encyclopedia
		Thrust-to-weight ratio (where weight means weight at the Earth’s surface) is a dimensionless parameter characteristic of rocket and jet engines, and of vehicles propelled by such engines (typically space launch vehicles and jet aircraft).
		Many factors affect a thrust-to-weight ratio, and for valid comparison, thrust should be measured under controlled conditions (STP).
		Depending on the engine or vehicle under consideration, effective weight may be affected by progressive fuel consumption, buoyancy, and local gravitational field strength.
	en.wikipedia.org /wiki/Thrust-to-weight_ratio (218 words)

	Thrust-to-weight ratio -- Facts, Info, and Encyclopedia article (Site not responding. Last check: 2007-10-09)
		Many factors affect a thrust-to-weight ratio, and for valid comparison, thrust should be measured under controlled conditions ((Standard temperature and pressure) STP).
		Factors that affect thrust include freestream air (The degree of hotness or coldness of a body or environment (corresponding to its molecular activity)) temperature, (The force applied to a unit area of surface; measured in pascals (SI unit) or in dynes (cgs unit)) pressure, (The amount per unit size) density, and composition.
		Depending on the engine or vehicle under consideration, effective weight may be affected by progressive fuel consumption, (Cheerfulness that bubbles to the surface) buoyancy, and local gravitational field strength.
	www.absoluteastronomy.com /encyclopedia/t/th/thrust-to-weight_ratio.htm (236 words)

	Air Combat 1
		Thrust and Lift are essential for flight, but are forced to overcome Drag and Weight.
		Thrust is the force that causes an aircraft to move through the air.
		Weight is the effect of the gravitational pull of the earth on the aircraft.
	www.saunalahti.fi /fta/chap1.htm (983 words)

	Thrust to Weight Ratio (Site not responding. Last check: 2007-10-09)
		Thrust is normally directed forward along the center-line of the aircraft.
		where W is the weight and g is the gravitational constant equal to 32.2 ft/sec^s in English units and 9.8 m/sec^s in metric units.
		F/W is the thrust to weight ratio and it is directly proportional to the acceleration of the aircraft.
	www.grc.nasa.gov /WWW/K-12/airplane/fwrat.html (486 words)

	OtherSpace: Projectile: Rocket-Assisted
		Thrust is the force that the rocket engine generates to move the rocket forward.
		The ability of a rocket to accelerate itself and its warhead depends on its thrust-to-weight ratio; that is, the ratio of the rocket's thrust to the weight of the rocket and its load.
		The thrust-to-weight ratio constantly changes during powered flight as the weight of the rocket is reduced through the consumption of fuel.
	web.wt.net /~dmqpw/osmunitions/projectile-rocket.html (1777 words)

	Technical Reports
		The average initial thrust used with Equations 3 and 4 is defined (by the author) as the thrust averaged over the period of time that the rocket is accelerating up the launch rod, rail, or tower.
		The average initial thrust is usually not the same as the average thrust (which is averaged over the entire burn time of the motor).
		With thrust profiles like these, the average initial thrust is several times higher than the average thrust, to give the rocket good acceleration off the launcher.
	www.tripoli.org /tra_ca/tech_reports.html (3580 words)

	ch11-7
		If maximum speed were the only requirement, wing loading and thrust loading (thrust-to-weight ratio) might be expected to increase with time in a fashion closely related to the increase in maximum speed.
		The corresponding reduction in wing loading and increase in thrust loading are clearly shown by the trends in figures 11.45 and 11.46 and indicate how new requirements can change these two important aircraft design parameters.
		The corresponding thrust loading for the P-80 was 0.33; by comparison, the thrust loading of the contemporary McDonnell Douglas F-15C is 1.07 at design gross weight.
	www.hq.nasa.gov /office/pao/History/SP-468/ch11-7.htm (1177 words)

	preliminary sizing: second segment climb
		Therefore, the thrust of the remaining engine(s) has to be enough to climb as required.
		With given values of takeoff lift-coefficient, wing aspect ratio and the number of engines it is now possible to calculate the takeoff trust to weight ratio.
		The takeoff thrust to weight ratio of the aircraft must be above the green line to fulfil the requirement for the second segment condition.
	www.haw-hamburg.de /pers/Scholz/dimensionierung/2seg_ie.htm (283 words)

	Space Future - Design Study on Propulsion Systems for Space Tourist Carrier Vehicle (Site not responding. Last check: 2007-10-09)
		Thus, the chamber pressure was determined to be 10 MPa at a mixture ratio of 6.
		If the actual weight of the extendible nozzles of sustainer engines are heavier than the estimated value, dominant position of the case C will be break.
		The maximum payload is about 7.5 ton when thrust /weight is 1.5, which is 1.1 ton larger than when the thrust-to-weight ratio is 1.3.
	www.spacefuture.com /archive/design_study_on_propulsion_systems_for_space_tourist_carrier_vehicle.shtml (2912 words)

	An approximate method of assessing the performance of propellant transfer spaceplanes
		Landing gear weights are traditionally parameterized as a percentage l of the landed weight, varying between 2 and 3 percent.
		The landed weight of a propellant transfer spaceplane should be the takeoff weight, which consists of the injected weight, the weight of the fuel (not the oxidizer), and the weight of whatever additional propellant is needed to climb and rendezvous with the tanker and to stay on the tanker during the transfer.
		The gross weight for this case is 330,000 lbs, the empty weight is 30,929 lbs, the fixed weight is 8,250 lbs, and the payload is about 6,000 lbs assuming the same avionics and crew systems weights as above.
	www.risacher.org /bh/dfh.html (1328 words)

	Propulsion
		This combination shows a high thrust power (the thrust times the airplane velocity) with respect to fuel consumption, but because of its limitations, it is used primarily to power medium-speed, moderate-size aircraft.
		There are essentially 2 exhaust streams contributing to the thrust: a stream of high pressure air generating a high velocity around the engine and a stream of high temperature air generating another high velocity from inside the engine.
		The total thrust is the sum of the 2 velocities minus the original velocity of the airplane times the very large rate of air flowing through each stream.
	wings.avkids.com /Book/Propulsion/instructor/types-01.html (1663 words)

	Jet engine (Site not responding. Last check: 2007-10-09)
		The engine generates thrust because of the acceleration of the air through it—the equal and opposite force this acceleration produces (by Newton's third law) is thrust.
		These compression ratios are not comparable to those in a piston engine because the combustion process is continuous, as explained below.
		The bypass ratio (the ratio of bypassed air mass to combustor air mass) is an important parameter for turbofans.
	hallencyclopedia.com /Jet_engine (4752 words)

	What is Thrust?
		THRUST is one of the four forces acting on an aircraft.
		Thrust is the force necessary to move the aircraft forward and lift is the force acting in the upward direction required to keep the aircraft aloft.
		A F-15E can accomplish this when the weight of the F-15E is less than the 58,200 pounds of thrust produced by the engines (commonly referred to as a thrust-to-weight ratio of greater than 1.0).
	www.allstar.fiu.edu /aero/thrust.htm (231 words)

	Power of this Motor - UK Rocketry & Pyro forums (Site not responding. Last check: 2007-10-09)
		The 5:1 ratio is concerned with thrust at any given moment, not the total thrust over the motors burn time.
		Thus to get the 5:1 thrust to weight ratio of the I357 you divide 357 by 4.45, this is the number of Newton's in a pound.
		The key thing is that the average thrust the motor provides is more than the gravitational force the motor and payload mass creates.
	www.ukrocketry.co.uk /forum/index.php?showtopic=1165 (1534 words)

	Beginner's Guide to Propulsion/EngnineSim: Thrust to Weight Ratio- Answers (Site not responding. Last check: 2007-10-09)
		Change the plane type to Airliner and record weight and thrust in the data table for Airliner 1.
		Calculate the thrust to weight ratios in the data table.
		Compare the thrust to weight ratios in airliners, fighter jets, and executive jets.
	www.lerc.nasa.gov /WWW/K-12/cdtemp/BGP/Sheri_Z/thrustwtrat_ans.htm (496 words)

	DOCTOR ROCKET HOME PAGE (Site not responding. Last check: 2007-10-09)
		A motor with a total impulse of 80 pound-seconds can put out 80 pounds of thrust for 1 second, or 40 pounds of thrust for 2 seconds, or 20 pounds of thrust for 4 seconds.
		What this means is you can get a large average thrust out of a short burn time or a small average thrust over a long burn time.
		Check your thrust to weight ratio carefully to insure the average thrust of the motor is at least 5 times the weight of the fully loaded rocket.
	www.drrocket.com /RELOADTC.asp (587 words)

	Thrustweightratio (Site not responding. Last check: 2007-10-09)
		One of the most important factors in gas turbine engine designs for heavier than air craft, is the engines thrust to weight ratio.
		Turbine engines are most suited to aircraft propulsion primarily because of their excellent thrust to weight ratio compared with IC piston engines.
		One of the reasons for this is that gas turbine engines burn fuel constantly, while a piston engine burns its fuel for only a short proportion of the of the cycle, so it must be larger and heavier to produce the same magnitude of power.
	www.bath.ac.uk /~en0nd/Thrustweightratio.htm (241 words)

	Thrust
		The ratio between these two values is called the thrust-to-weight ratio of the booster.
		At liftoff, the Atlas IIA thrust-to-weight ratio is 1.2, enough to accelerate a payload to speeds of 8 kilometers per second (18,000 miles per hour), sending the Atlas IIA to targets or orbits many thousands of miles away.
		As propellants burn, the thrust-to-weight ratio increases, and the booster continues to accelerate at higher rates.
	www.aero.org /education/primers/space/thrust.html (755 words)

	ch11-2
		Because of the limited thrust capability of jet engines available at that time, both aircraft were necessarily of twin-engine design to meet desired mission and performance objectives.
		The unswept wing was mounted in the shoulder position and had a constant airfoil thickness ratio of 14 percent, which was significantly greater than that used on the wings of the Me 262 and the Meteor.
		Although the P-80 was conventional in appearance, the aircraft was the result of a careful synthesis of weight, size, and thrust parameters, as well as close attention to aerodynamic refinement.
	www.hq.nasa.gov /office/pao/History/SP-468/ch11-2.htm (4117 words)

	Chapter 4: Areas Needing Continued Technical Development Commercial Supersonic Technology: The Way Ahead \| Committee on ...
		At cruise Mach numbers of about 1.2 to 2.0, engine cycles with high bypass ratios (1.5 to 3.0), including variable cycle engines, can be used to reduce community noise while still meeting thrust requirements during takeoff and climb and propulsion efficiency requirements during cruise.
		Aircraft designs with low aspect ratios and low wing loading are compatible with steep approaches to landing and have a large ground effect when the airplane is about a wingspan from the ground, increasing lift by about 20 percent.
		The aerodynamic weight and propulsion characteristics of a previously established design for a Mach 2.7 supersonic cruise vehicle fueled by liquid hydrogen were critically reviewed and updated.
	www.nap.edu /html/commercial_supersonic/ch4.html (8570 words)

	Propulsion
		Some aircraft, such as fighter jets need a lot of thrust and are not as concerned about the amount of fuel used, if the mission requires it.
		It had a much higher thrust per unit weight ratio than the piston-driven engines, which led directly to longer ranges (flight distances) and higher payloads (more passengers and baggage).
		(This is the second thrust, after the propeller) Because only a small part of the air flow is actually burned inside the engine, the turboprop engine can generate a lot of thrust with a low fuel consumption compared to a turbojet engine.
	wings.avkids.com /Book/Propulsion/advanced/types-01.html (1262 words)

	Jet engine Article, Jetengine Information (Site not responding. Last check: 2007-10-09)
		Theengine generates thrust because of the acceleration of the air through it - the equal and opposite force thisacceleration produces (Newton 's third law) is thrust.
		A simplification is to compare the pressure of gas taken in towhen it is burned, the so-called compression ratio.
		The bypass ratio (the ratio of bypassed air mass to combustor air mass) is an important parameter for turbofans.Early turbofans (and most modern jet fighter engines) arelow-bypass turbofans with bypass ratios less than 1.
	www.anoca.org /air/design/jet_engine.html (2909 words)

	Pakistani Defence Forum -> Thrust-to-weight Ratio (Site not responding. Last check: 2007-10-09)
		I know that the minimum thrurst to weight ratio of a plane is 1:4 this is to make it fly.
		The thing is, we know the JF-17's thrust to weight ratio is only 95:100 which means it can't fly straight up 90 degrees...
		The thrust to weight ratio increases with speed and decreases with the weight of the plane.
	www.pakistanidefenceforum.com /index.php?showtopic=20234 (1681 words)

	Basic Flight
		The second is thrust, the force produced by engines that propels the plane through the air.
		Although thrust is the force behind airspeed, the angle of attack (AoA) greatly affects airspeed.
		At higher gross weights, the g-limit is reduced to keep from overstressing the airframe, such that at the aircraft's maximum gross weight (66,000 Ibs.) the g-limit is only +4.
	www.fortunecity.com /underworld/straif/85/id80_bf.htm (2783 words)

	thrust to weight ratio - RC Groups
		In the progress of learning this hobby I am very curious in the thrust to weight ratio.
		Static thrust to weight is an imperfect way to judge plane performance but pretty useful on slow flying models.
		Ounce per square feet is simply the weight divided by your wing area in square inches divided by 144.
	www.rcgroups.com /forums/showthread.php?t=53148 (565 words)

	Chapter 6 -- Rockets and Rocket Science (Site not responding. Last check: 2007-10-09)
		The greater excess thrust means greater rocket acceleration in a unit known as g's or numbers of times the norm al acceleration due to gravity at 9.8 meters/second2.
		Therefore at one g a 100 pound woman weighs 100 pounds; at 2 g's she weighs 200 pounds; 3 g's she weighs 300 pounds; etc. As more fuel and oxidizer are used the rocket's weight (mass) decreases and its thrust to weight ratio increases.
		If thrust is to be either reduced or increased it must be done in the design of the grain.
	www.space.edu /projects/book/chapter6.html (2268 words)

	Code One Magazine: Harry Hillaker — Father of the F-16 — July 1991
		The airplane's exceptional maneuverability is a consequence of that lower drag and a higher thrust-to-weight ratio.
		Our early work was purely and simply an analysis of the relationships of wing loading and thrust loading and fuel fraction (the ratio of fuel capacity to the weight of the airplane).
		You can also get a higher thrust-to-weight ratio by leaving the thrust alone and reducing the weight, which is what we did on the lightweight fighter.
	www.codeonemagazine.com /archives/1991/articles/jul_91/july2a_91.html (2568 words)

	Boeing 707 - 767 Comparison
		Since the Boeing 707 had a higher thrust to weight ratio, it would be traveling faster on take-off and on landing.
		The thrust to weight ratio for a Boeing 707 is 4 x 18,000/336,000 = 0.214286.
		The thrust to weight ratio for a Boeing 767 is 2 x 31,500/395,000 = 0.159494.
	www.whatreallyhappened.com /boeing_707_767.html (353 words)

	FitnessManagement.com Home
		And body composition is calculated according to a ratio known as percentage of body fat.
		The difference between the two is that the physiologist compares a passive element (fat) to the overall body weight of the human being (it's effectively a fat-to-weight ratio), while the aeronautical engineer compares an active element (pounds of thrust) to the overall weight of the plane.
		Interestingly enough, pilots are acutely aware of their TWR, figure it regularly and must stay within certain guidelines to stay airborne.
	www.fitnessworld.com /FM/tmpl/genPage.asp?p=/information/articles/library/strength/guested0201.html (898 words)

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