Propellant mass fraction - Revision history

en>K6ka: Reverted to revision 574679645 by Brockert (talk): Rv/v. (TW)

2015-01-08T21:22:10Z

Reverted to revision 574679645 by Brockert (talk): Rv/v. (TW)

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	~~The '''lift coefficient''' (''C''<sub>L</sub>~~, ~~''C''<sub>~~a~~</sub> or ''C''<sub>z</sub>) is a [[dimensionless]] coefficient that relates the [[Lift (force)\|lift]] generated by a lifting body to the [[density]] of the fluid around the body~~, ~~its velocity~~ and ~~an associated reference area. A lifting body is a [[foil (fluid mechanics)\|foil]] or~~ a ~~complete foil-bearing body such as a [[fixed-wing aircraft]]~~. ~~''C''<sub>L</sub> is a function of the angle of the body to the flow~~, ~~its [[Reynold number]]~~ and ~~its [[Mach number]]~~. ~~The lift coefficient ''c''~~<~~sub~~>l<~~/sub~~> ~~is refers~~ to the dynamic lift characteristics of a [[two-dimensional]] foil section, with the reference area replaced by the foil [[Chord (aircraft)\|chord]].<ref name=Clancy>{{cite book\|last=Clancy\|first=L. J.\|title=Aerodynamics\|year=1975\|publisher=John Wiley & Sons\|location=New York\|at=Sections 4.15 & 5.4}}</ref><ref name=TWS1.2>[[Ira H. Abbott\|Abbott, Ira H.~~]], and Von Doenhoff, Albert E.:~~ ''~~Theory~~ of ~~Wing Sections''. Section 1.2</ref>~~		For your offense, you might attain Gunboats which can handily shoot at enemy rights coming from a range and Landing Crafts which you must fill up when you train equipment for example Rifleman, Heavy, Zooka, Warrior and Takes a dive. To your village defenses, you might have structures like Mortar, Vehicle Gun, Sniper Tower, Cannon, Flamethrower, Mine, Tank Mine, Boom Cannon and Drive Launcher to assist your entire family eradicate enemies.<br><br>Beginning nearly enough rocks to get another general contractor. Don''t waste a lot of of the gems from any way on rush-building anything, as if they can save you consumers you are going to actually eventually obtain enough freely available extra gems to produce that extra builder without even cost. Particularly, you can get free gemstones for clearing obstructions for example , rocks and trees, after you clear them out and about they come back and also you may re-clear items to get more gems.<br><br>The effects displayed in the information are too apparent for you to become ignored. Even a child could work out that the nationwide debt has always relied upon clash of clans compromise tool no survey any certain extent, but individuals need to that ever. Tons of analysts fear a subsequent depression.<br><br>In case you are searching for a particular game into buy but want to purchase it at the main best price possible, depend on the "shopping" tab there on many search engines. When you liked this information along with you want to obtain more details concerning [http://circuspartypanama.com code triche clash of clans] generously visit our own internet site. This will allocate you to immediately compare the prices of the specific game at all the major retailers online. You can also see ratings for the seller in question, helping that you determine who you should always buy the game with.<br><br>Plan not only provides complete tools, there is perhaps Clash of Clans chop no survey by anyone else. Strict anti ban system allow users to utilize the program and play without nearly any hindrance. If people are interested in best man program, they are just required to visit amazing site and obtain the most important hack tool trainer so now. The name of the website is Amazing Cheats. A number of web-sites have different types out of software by which most people can get past unpleasant stages in the video game.<br><br>It looks like computer games are everywhere these times. Carbohydrates play them on your telephone, boot a games consoles in the home and not to mention see them through social media on your personal personal computer. It helps to comprehend this associated with amusement to help they benefit from the pretty offers which are online.<br><br>You don''t necessarily need one of the [http://www.Alexa.com/search?q=cutting+edge&r=topsites_index&p=bigtop cutting edge] troops to win wins. A mass volume of barbarians, your first-level troop, could totally destroy an attacker village, and strangely it''s quite enjoyable to take a the virtual carnage.

	~~==Definition~~ of the ~~lift coefficient ''C''<sub>L</sub>==~~

	~~The lift coefficient ''C''<sub>L</sub> is defined by<ref name=TWS1.2/><ref>Clancy~~, L. ~~J.: ''Aerodynamics''. Section 4.15</ref>~~

	~~:<math>C_\mathrm L = {\frac{L}{\frac{1}{2}\rho v^2S}} = {\frac{2 L}{\rho v^2S}} = \frac{L}{q S}</math>~~ ,
	~~where~~
	~~<math>L\~~,~~</math> is the [[Lift (force)\|lift force]]~~, ~~<math>\rho\,</math> is [[fluid]] [[density]], <math>v\,</math> is [[true airspeed]], <math>S\,</math> is [[planform]] area~~ and <~~math~~>~~q\,~~<~~/math~~> ~~is the fluid [[dynamic pressure]].~~

	The ~~lift coefficient can be approximated using~~ the ~~[[lifting-line theory]],<ref>Clancy, L. J.: ''Aerodynamics''. Section 8~~.~~11</ref> numerically calculated or measured in~~ a ~~[[wind tunnel]] test~~ of ~~a complete aircraft configuration.~~

	~~== Section lift coefficient ==~~
	~~[[Image:Lift curve~~.~~svg\|thumb\|300px\|right\|A typical curve showing section lift coefficient versus angle~~ of ~~attack for~~ a ~~cambered airfoil]]~~
	~~Lift coefficient may also be used as a characteristic of a particular shape (or cross-section) of an [[airfoil]]~~. ~~In this application it is called the '''section lift coefficient'''~~ <~~math~~>~~c_\text{l}~~<~~/math~~>~~. It is common to show,~~ for a particular ~~airfoil section,~~ the ~~relationship between section lift coefficient and [[angle of attack]].<ref>Abbott~~, ~~Ira H., and Von Doenhoff, Albert E.: ''Theory of Wing Sections''. Appendix IV</ref> It is also useful to show~~ the ~~relationship between section lift coefficient and [[drag coefficient]].~~

	~~The section lift coefficient is based~~ on two-dimensional flow over a wing of infinite span and non-varying cross-section so the lift is independent of spanwise effects and is defined in terms of <math>l</math>, the lift force per unit span of the wing. ~~The definition becomes~~

	:~~<math>c_\text{l} = \frac{l}{\frac{1}{2}\rho v^2c},<~~/~~math>~~

	~~where <math>c\,<~~/~~math> is the [[chord (aircraft)\|chord]] of the airfoil~~.

	~~For a given angle~~ of ~~attack, ''c''<sub>l</sub> can be calculated approximately using the [[thin airfoil theory~~]~~],<ref>Clancy, L~~. ~~J.: ''Aerodynamics''. Section 8.2</ref> calculated numerically or determined from wind tunnel tests on a finite-length test piece, with end-plates designed~~ to ~~ameliorate~~ the ~~three-dimensional effects. Plots~~ of ~~''c''<sub>l</sub> versus angle of attack show~~ the ~~same general shape for~~ all ~~[[airfoil]]s, but~~ the ~~particular numbers will vary~~. ~~They show an almost linear increase~~ in ~~lift coefficient~~ with ~~increasing [[angle of attack]] with a gradient known as the lift slope~~. ~~For a thin airfoil of any shape the lift slope is π~~<~~sup~~>2<~~/sup~~>~~/90 ≃ 0~~.~~11 per degree~~. ~~At higher angles a maximum point is reached~~, ~~after which~~ the ~~lift coefficient reduces~~. The ~~angle at which maximum lift coefficient occurs is the [[Stall (flight)\|stall]] angle~~ of the ~~airfoil~~.

	~~Symmetric airfoils necessarily~~ have ~~plots~~ of ~~c<sub>l</sub> versus angle of attack symmetric about~~ the ~~''c''~~<~~sub~~>l<~~/sub~~> ~~axis, but for any airfoil with positive [[camber (aerodynamics)\|camber]], i~~.~~e. asymmetrical, convex from above~~, ~~there is still~~ a ~~small but positive lift coefficient~~ with ~~angles of attack less than zero. That is,~~ the ~~angle at~~ which ~~''c''~~<~~sub~~>l<~~/sub~~> ~~= 0 is negative. On such airfoils at zero angle~~ of ~~attack~~ the ~~pressures on the upper surface are lower than on the lower surface~~.

	== ~~See also~~ ==
	* [[Lift-to~~-drag ratio]]~~
	* [[Drag coefficient]]
	* [[Foil (fluid mechanics)]]
	* [[Pitching moment]]
	* [[Circulation control wing]]
	* [[Zero lift axis]]

	~~== Notes ==~~
	~~{{reflist}}~~

	~~== References ==~~
	* Clancy, L. ~~J. (1975): ''Aerodynamics''. Pitman Publishing Limited~~, ~~London, ISBN 0-273-01120~~-0
	* Abbott, ~~Ira H.~~, and ~~Von Doenhoff, Albert E. (1959): ''Theory of Wing Sections~~''. ~~Dover Publications Inc., New York, Standard Book Number 486-60586-8~~

	~~[[Category:Aerodynamics]]~~
	~~[[Category:Aircraft wing design]]~~
	~~[[Category:Dimensionless numbers of fluid mechanics]]~~

en>Brockert: /* Formulation */ adding one more follows

2013-09-27T00:57:15Z

Formulation: adding one more follows

← Older revision		Revision as of 02:57, 27 September 2013
Line 1:		Line 1:
	~~Catrina Le is what~~'~~s constructed on her [http:~~//~~Answers~~.~~Yahoo~~.~~com~~/~~search~~/~~search_result?p~~=~~birth+credentials~~&~~submit-go~~=~~Search+Y!+Answers birth credentials~~] ~~though she doesn't significantly like being called just like that. Her job happens to be a cashier but very quickly her husband~~ and ~~her will start their own family based business~~. ~~To drive is something why she~~'~~s been doing best. For years she~~'~~s been living when Vermont~~. ~~Go to your sweetheart website to find as well as more: http://circuspartypanama~~.~~com~~<~~br><br~~>		The '''lift coefficient''' (''C''<sub>L</sub>, ''C''<sub>a</sub> or ''C''<sub>z</sub>) is a [[dimensionless]] coefficient that relates the [[Lift (force)\|lift]] generated by a lifting body to the [[density]] of the fluid around the body, its velocity and an associated reference area. A lifting body is a [[foil (fluid mechanics)\|foil]] or a complete foil-bearing body such as a [[fixed-wing aircraft]]. ''C''<sub>L</sub> is a function of the angle of the body to the flow, its [[Reynold number]] and its [[Mach number]]. The lift coefficient ''c''<sub>l</sub> is refers to the dynamic lift characteristics of a [[two-dimensional]] foil section, with the reference area replaced by the foil [[Chord (aircraft)\|chord]].<ref name=Clancy>{{cite book\|last=Clancy\|first=L. J.\|title=Aerodynamics\|year=1975\|publisher=John Wiley & Sons\|location=New York\|at=Sections 4.15 & 5.4}}</ref><ref name=TWS1.2>[[Ira H. Abbott\|Abbott, Ira H.]], and Von Doenhoff, Albert E.: ''Theory of Wing Sections''. Section 1.2</ref>

	~~Visit my web page~~ :: [~~http~~://~~circuspartypanama~~.~~com code triche clash~~ of ~~clans~~]		==Definition of the lift coefficient ''C''<sub>L</sub>==

			The lift coefficient ''C''<sub>L</sub> is defined by<ref name=TWS1.2/><ref>Clancy, L. J.: ''Aerodynamics''. Section 4.15</ref>

			:<math>C_\mathrm L = {\frac{L}{\frac{1}{2}\rho v^2S}} = {\frac{2 L}{\rho v^2S}} = \frac{L}{q S}</math> ,
			where
			<math>L\,</math> is the [[Lift (force)\|lift force]], <math>\rho\,</math> is [[fluid]] [[density]], <math>v\,</math> is [[true airspeed]], <math>S\,</math> is [[planform]] area and <math>q\,</math> is the fluid [[dynamic pressure]].

			The lift coefficient can be approximated using the [[lifting-line theory]],<ref>Clancy, L. J.: ''Aerodynamics''. Section 8.11</ref> numerically calculated or measured in a [[wind tunnel]] test of a complete aircraft configuration.

			== Section lift coefficient ==
			[[Image:Lift curve.svg\|thumb\|300px\|right\|A typical curve showing section lift coefficient versus angle of attack for a cambered airfoil]]
			Lift coefficient may also be used as a characteristic of a particular shape (or cross-section) of an [[airfoil]]. In this application it is called the '''section lift coefficient''' <math>c_\text{l}</math>. It is common to show, for a particular airfoil section, the relationship between section lift coefficient and [[angle of attack]].<ref>Abbott, Ira H., and Von Doenhoff, Albert E.: ''Theory of Wing Sections''. Appendix IV</ref> It is also useful to show the relationship between section lift coefficient and [[drag coefficient]].

			The section lift coefficient is based on two-dimensional flow over a wing of infinite span and non-varying cross-section so the lift is independent of spanwise effects and is defined in terms of <math>l</math>, the lift force per unit span of the wing. The definition becomes

			:<math>c_\text{l} = \frac{l}{\frac{1}{2}\rho v^2c},</math>

			where <math>c\,</math> is the [[chord (aircraft)\|chord]] of the airfoil.

			For a given angle of attack, ''c''<sub>l</sub> can be calculated approximately using the [[thin airfoil theory]],<ref>Clancy, L. J.: ''Aerodynamics''. Section 8.2</ref> calculated numerically or determined from wind tunnel tests on a finite-length test piece, with end-plates designed to ameliorate the three-dimensional effects. Plots of ''c''<sub>l</sub> versus angle of attack show the same general shape for all [[airfoil]]s, but the particular numbers will vary. They show an almost linear increase in lift coefficient with increasing [[angle of attack]] with a gradient known as the lift slope. For a thin airfoil of any shape the lift slope is π<sup>2</sup>/90 ≃ 0.11 per degree. At higher angles a maximum point is reached, after which the lift coefficient reduces. The angle at which maximum lift coefficient occurs is the [[Stall (flight)\|stall]] angle of the airfoil.

			Symmetric airfoils necessarily have plots of c<sub>l</sub> versus angle of attack symmetric about the ''c''<sub>l</sub> axis, but for any airfoil with positive [[camber (aerodynamics)\|camber]], i.e. asymmetrical, convex from above, there is still a small but positive lift coefficient with angles of attack less than zero. That is, the angle at which ''c''<sub>l</sub> = 0 is negative. On such airfoils at zero angle of attack the pressures on the upper surface are lower than on the lower surface.

			== See also ==
			* [[Lift-to-drag ratio]]
			* [[Drag coefficient]]
			* [[Foil (fluid mechanics)]]
			* [[Pitching moment]]
			* [[Circulation control wing]]
			* [[Zero lift axis]]

			== Notes ==
			{{reflist}}

			== References ==
			* Clancy, L. J. (1975): ''Aerodynamics''. Pitman Publishing Limited, London, ISBN 0-273-01120-0
			* Abbott, Ira H., and Von Doenhoff, Albert E. (1959): ''Theory of Wing Sections''. Dover Publications Inc., New York, Standard Book Number 486-60586-8

			[[Category:Aerodynamics]]
			[[Category:Aircraft wing design]]
			[[Category:Dimensionless numbers of fluid mechanics]]

en>MenteMagica at 21:21, 31 October 2011

2011-10-31T21:21:07Z

New page

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