Report on Structural Optimization of Aircraft Delta Wings

Added on - 21 Apr 2020

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Structural optimization of aircraft delta wings1STRUCTURAL OPTIMIZATION OF AIRCRAFT DELTA WINGSBy NameCourseInstructorInstitutionLocationDate
Structural optimization of aircraft delta wings2IntroductionAirplane wings refer to an appendage having a surface which is responsible for producinga lift that sequentially helps in the lift.The delta wing can be described d as a wing that when itis viewed from an aerial position, it has the shape of a triangle usually with the tip chopped off.The tip sharply sweeps in the backward direction with the front angle usually at sixty degreeswhereas the rear angle being at ninety degrees. These type of wings do not have the horizontalstabilizers and they are most preferred in the supersonic aircraft due to their high-performanceefficiency.The aim of this experiment is to give better structural parameters for the betterairplane performance and safety of fighter aircrafts. Besides, the objective of the research is toperform structural optimization of the delta wing design by varying the elements and theirproperties[ CITATION Fed09 \l 1033 ].RoadmapThere is a different type of aircraft wings. They includeSwept wingDelta wingStraight wingBesides, the wings can be positioned differently, for instance, we have parasol positioning, highmount positioning, and mid mount positioning and low mount positioning as illustrated
Structural optimization of aircraft delta wings3Delta wingsThere are various types of delta wings which includesThe tailless delta which is the type of delta wing having the wings in fell out a position asa result of undesired features and high drag effects. They are generally best for highaltitude, high speed, and interceptor rolesThe tailed delta – this has an additional horizontal tail surface for the purposes ofenhancing the performance[ CITATION Dir15 \l 1033 ]Cropped delta – this has its tip chopped off to help in avoiding effects of drag at highangles of attackOther types of delta wings include the compound delta, ranked arrow and the oval delta. Thesehave their inner parts possessing enhanced sweepback than the outer parts to help in developinga high lit vortex and minimize the drag as shown below
Structural optimization of aircraft delta wings4Benefits of the delta wingsI.The delta wings are physically attractive more so for the supersonic aircrafts. This isbecause the delta wings have a bigger root chord wing which is able to combine both thethick wing spar and relatively low thin wing spar which overall maintains the wave dragdon and make the wing attractiveII.The delta wing possesses a high internal volume of fuel as a result to the large root chordespecially during low thickness[ CITATION Tom09 \l 1033 ]III.Besides the belt wing helps in lessening the speed of the aircraft due to its large surfacearea which is provided by the big sized root chordIV.Also, the delta wing produces a sufficient amount of edge sweep thereby resulting invortex liftV.Naturally, the stability of the delta wing is desirable thereby eliminating the need for aseparate tail surfaceVI.The delta wings are able to fly at very high angles of attack, thereby they are ideal to beused in the fighter jetsVII.The delta wingshave low-speed characteristics hence they are the best in terms of theiroverall performance when compared to others thereby being suitable for application inthe supersonic airplanes
Structural optimization of aircraft delta wings5VIII.Finally, the delta wings offer a desirable amount of drag during the landing of thesupersonic aircraft. During incidences of landing, there is need for increasing the dragaround the aircraft helps the delta wings aids in this more than the other types of wingsResearch gaps and limitationsWhile delta wings are critical to achieving high lift for supersonic flight, they have some gapsand limitations which should be keenly taken care of. These research gaps includeInsufficient stability at high angles of attackProduction of excessive drag[CITATION DIA06 \l 1033 ]LimitationsThe delta wings necessitate for high landing takeoff speeds which is extremelydangerousUsually, the delta wings produces excess viscous drag at the same amount of lift whencompared against the wing aspect ratio this is not desirable and in most cases, the sweptwings are better in this aspectIt is not possible to incorporate some devices which pose high lift characteristics such asfowler flaps into the delta wings. This is because the increased thickness of consistentairliner wings provides for easy integration of the flaps, while the backward edge of thedelta wing creates unbearable pitching moments when such wing flaps get deflected
Structural optimization of aircraft delta wings6Evolution of the delta wingsThe delta wing can be described d as a wing that when it is viewed from an aerial position, it hasthe shape of a triangle usually with the tip chopped off. The tip sharply sweeps in the backwarddirection with the front angle usually at sixty degrees whereas the rear angle being at ninetydegrees. These type of wings do not pose the horizontal stabilizers and they are most preferred inthe supersonic aircraft due to their high-performance efficiency[ CITATION Tim09 \l 1033 ].The evolution of delta wings traces back in the year 1867 where we have the first designpatented by two Englishmen J.W. Butler and E. Edwards. The design of the aircrafts would haveflown if it ever took into account some components including the thrust, propulsion system,steam, gunpowder, steam, and jet. However, this design was not taken seriously until the start ofthe Second World WarLater in the year 1940, a German professor by the name Alexander began doing a research onsupersonic airplanes and took the delta shape as a case study .together with other researchers,they later developed a glider system and sent it to the United States for further research.
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