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For this week’s assignment you will research a historic or current fighter type aircraft ofyour choice(options for historic fighter jets include, but are not limited to:

For this week’s assignment you will research a historic or current fighter type aircraft ofyour choice(options for historic fighter jets include, but are not limited to: Me262, P-59, MiG-15, F-86, Hawker Hunter, Saab 29, F-8, Mirage III, MiG-21, MiG-23, Su-7, Electric Lightning,Electric Canberra, F-104, F-105, F-4, F-5, A-6, A-7, Saab Draken, Super Etendard, MiG-25,Saab Viggen, F-14, and many more).As previously mentioned and in contrast to formal research for other work in youracademic program at ERAU, Wikipedia may be used as a starting point for thisassignment. However, DO NOT USE PROPRIETARY OR CLASSIFIED INFORMATION evenif you happen to have access in your line of work.Notice also that NASA has some great additional information at:http://www.hq.nasa.gov/pao/History/SP-468/contents.htm.1. Selected Aircraft:2. Aircraft Gross Weight[lbs]:3. Aircraft Wing Area[ft2]:4. Positive Limit Load Factor (LLF – i.e. the max positive G) for your aircraft:5. Negative LLF (i.e. the max negative G) for your aircraft:6. Maximum Speed[kts]of your aircraft. If given as Mach number, convert by using Eq. 17.2relationships with a sea level speed of sound of 661 kts.For simplification, assume the CLmaxfor your aircraft was 1.5 (unless you can find adifferent CLmaxin your research).A. Find the Stall Speed[kts]at 1G under sea level standard conditions for your aircraft (similarto all of our previous stall speed work, simply apply the lift equation in its stall speed form frompage 44 to the above data):B. Find the corresponding Stall Speeds for 2G, 3G, 4G, and so on for your selected aircraft (upto the positive load limit from 4. above), using the relationship of Eq. 14.5. You can use thetable below to track your results.C. Add the corresponding Stall Speeds for -1G, -2G, and so on for your selected aircraft (up tothe negative load limit from 5. above) to your table.Assume that your fighter wing hassymmetrical airfoil characteristics, i.e. that the negative maximum CL value is equal butopposite to the positive one.(Feel free to use specific airfoil data for your aircraft, but pleasemake sure to use the correct maximum positive and negative Lift Coefficients in the c

 
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