For high strength applications ____ is widely used.(a) 7075 aluminum alloy(b) 7089 magnesium zinc(c) 1098 gallium(d) Ge-Zn alloyThe question was posed to me by my college professor while I was bunking the class.I'd like to ask this question from Structures topic in section Structures and Loads of Aircraft Design

For high strength applications ____ is widely used.(a) 7075 aluminum a

1.	For high strength applications ____ is widely used.(a) 7075 aluminum alloy(b) 7089 magnesium zinc(c) 1098 gallium(d) Ge-Zn alloyThe question was posed to me by my college professor while I was bunking the class.I'd like to ask this question from Structures topic in section Structures and Loads of Aircraft Design
Answer» The CORRECT answer is (a) 7075 aluminum ALLOY Explanation: For HIGH STRENGTH application 7075 aluminum alloy is widely used. 7075 is alloyed with zinc, copper and magnesium. Corrosion resistance is lessened by alloying. Aluminum sheet is FREQUENTLY clad with a thin layer of pure aluminum.

Discussion

No Comment Found

Related InterviewSolutions

Following diagram represents _________(a) whisker reinforced composite(b) matrix only(c) fiber only(d) aluminum alloyI have been asked this question in final exam.I want to ask this question from Structures in chapter Structures and Loads of Aircraft Design
A column has effective length as 20unit. Determine Euler load of EI = 1000 unit.(a) 24.67 unit(b) 10 unit(c) 40 unit(d) 50.99 unitThe question was posed to me in final exam.This interesting question is from Structural-Analysis Fundamentals in portion Structures and Loads of Aircraft Design
Which of the following is an example of air load?(a) Gust(b) Taxi(c) Wheel stress(d) LandingThis question was posed to me in quiz.Enquiry is from Loads Categories topic in section Structures and Loads of Aircraft Design
The largest load that is expected to be experienced by aircraft is called __________(a) limit load(b) normal stress(c) normal strain(d) shear stressI have been asked this question in quiz.I need to ask this question from Loads Categories topic in portion Structures and Loads of Aircraft Design
Column has length of 1.2 m and radius of gyration as 1.5m. Determine slenderness ratio. Consider column is fixed at one end free at other end.(a) 1.6(b) 7.8(c) 98(d) 12.45I had been asked this question by my school principal while I was bunking the class.My question is taken from Structural-Analysis Fundamentals in division Structures and Loads of Aircraft Design
Determine the actual length of the column which has slenderness ratio of 2.9 and radius of gyration as 1.6. Consider column is fixed at both ends.(a) 9.28(b) 0.0045(c) 2.3674(d) 4.862The question was posed to me during a job interview.My doubt is from Structural-Analysis Fundamentals topic in chapter Structures and Loads of Aircraft Design
Following diagram represents ___________(a) v-n diagram combined of gust and Maneuver(b) v-n diagram landing(c) takeoff speed(d) drag coefficient vs liftThe question was asked in an interview for internship.The doubt is from Air Loads in division Structures and Loads of Aircraft Design
Magnesium is used for ________(a) control hinges(b) highest strength application(c) lofting(d) draftingI had been asked this question in class test.This interesting question is from Structures topic in division Structures and Loads of Aircraft Design
Composite material has only one material.(a) True(b) FalseI had been asked this question in quiz.The doubt is from Structures in division Structures and Loads of Aircraft Design
An object is subjected to some force. As a result of the force object undergoes in the deformation. If deformation of length is 0.28mm and Actual length is 20 mm then, find simple strain.(a) 0.014(b) 10.0014(c) 23.002(d) 0.00215The question was asked in my homework.The question is from Structures Fundamentals topic in chapter Structures and Loads of Aircraft Design

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment