A rectangular wing is allowed to pitch about the leading edge at a frequency of $5$ Hz$.$ ZONA ZAERO program was used to generate the M$=0\mathrm{.}8$ Sea Level Generalized Forces. Real part of the Generalized Force, GF$\_$R $=-10\mathrm{.}9524820000000$

$-21\mathrm{.}4181750000000$

$-31\mathrm{.}8162630000000$

$-38\mathrm{.}7254750000000$

$-39\mathrm{.}3938600000000$

$-39\mathrm{.}4562110000000$

$-38\mathrm{.}4562650000000$

$-36\mathrm{.}2788050000000$

$-33\mathrm{.}3785250000000$

$-30\mathrm{.}6563800000000$

$-28\mathrm{.}9980680000000$

$-29\mathrm{.}0667650000000$

$-32\mathrm{.}1658170000000$

$-32\mathrm{.}8102070000000$

$-33\mathrm{.}5445400000000$

$-34\mathrm{.}3667830000000$

$-35\mathrm{.}2765350000000$

$-36\mathrm{.}2538150000000$

$-37\mathrm{.}2721520000000$

$-38\mathrm{.}2709580000000$

$-39\mathrm{.}1778600000000$

$-39\mathrm{.}8644940000000$ Imaginary part of the Generalized Force, GF$\_$I $=-268\mathrm{.}830383000000$

$-198\mathrm{.}631744000000$

$-130\mathrm{.}907013000000$

$-68\mathrm{.}0170670000000$

$-62\mathrm{.}5342750000000$

$-57\mathrm{.}6190150000000$

$-52\mathrm{.}8577540000000$

$-47\mathrm{.}5177920000000$

$-40\mathrm{.}8664860000000$

$-32\mathrm{.}6154590000000$

$-23\mathrm{.}0496290000000$

$-12\mathrm{.}6825140000000$

$-2\mathrm{.}18306900000000$

$-1\mathrm{.}23560800000000$

$-0\mathrm{.}358705000000000$

$0\mathrm{.}422297000000000$

$1\mathrm{.}06744200000000$

$1\mathrm{.}54552100000000$

$1\mathrm{.}80138000000000$

$1\mathrm{.}80820000000000$

$1\mathrm{.}49676600000000$

$0\mathrm{.}884520000000000$ Generalized Stiffness from NASTRAN F$06$ Normal Mode Solution, k $=5\mathrm{.}40838800000000$ Reference length for the ZONA AICs based on semi chord, L $=1$ Generalized Mass from NASTRAN F$06$ Normal Mode Solution, m $=0\mathrm{.}00547666400000000$ QQ $=$ GF$\_$R $+$ GF$\_$I$*$sqrt$(-1)=-10\mathrm{.}9524820000000-268\mathrm{.}830383000000$i

$-21\mathrm{.}4181750000000-198\mathrm{.}631744000000$i

$-31\mathrm{.}8162630000000-130\mathrm{.}907013000000$i

$-38\mathrm{.}7254750000000-68\mathrm{.}0170670000000$i

$-39\mathrm{.}3938600000000-62\mathrm{.}5342750000000$i

$-39\mathrm{.}4562110000000-57\mathrm{.}6190150000000$i

$-38\mathrm{.}4562650000000-52\mathrm{.}8577540000000$i

$-36\mathrm{.}2788050000000-47\mathrm{.}5177920000000$i

$-33\mathrm{.}3785250000000-40\mathrm{.}8664860000000$i

$-30\mathrm{.}6563800000000-32\mathrm{.}6154590000000$i

$-28\mathrm{.}9980680000000-23\mathrm{.}0496290000000$i

$-29\mathrm{.}0667650000000-12\mathrm{.}6825140000000$i

$-32\mathrm{.}1658170000000-2\mathrm{.}18306900000000$i

$-32\mathrm{.}8102070000000-1\mathrm{.}23560800000000$i

$-33\mathrm{.}5445400000000-0\mathrm{.}358705000000000$i

$-34\mathrm{.}3667830000000+0\mathrm{.}422297000000000$i

$-35\mathrm{.}2765350000000+1\mathrm{.}06744200000000$i

$-36\mathrm{.}2538150000000+1\mathrm{.}54552100000000$i

$-37\mathrm{.}2721520000000+1\mathrm{.}80138000000000$i

$-38.2709580000000+1.80820000 Step by Step Solution There are 3 Steps involved in it 1 Expert Approved Answer Step: 1 Unlock Question Has Been Solved by an Expert! Get step-by-step solutions from verified subject matter experts Step: 2 Unlock Step: 3 Unlock Students Have Also Explored These Related Mechanical Engineering Questions! Q: Figure la shows the lifting curves from a lifting line analysis of 2D airfoil, elliptical wing with aspect ra) Whic-S and elliptical wing with aspect ratio AR=10 all with the same cambered airfoil.... Q: Figure 1b shows the induced drag coefficient (CDi) versus lifting coefficient (CL) results from lifting line analysis of three finite wings all with the same, airfoil and no geometric twist. Three... Q: In MATLAB please! + File: NE 2700 - Aircraft Sophomore D x C Part 1 Using The Approach Outli X C Get Homework Help With Chege x c File C:/Users/baltz/Downloads/AE2780_SP21_RK Project Assignment.pdf... Q: Figure 2 shows an uncambered, rectangular wing with span b, chord c and aspect ratio AR-b/c=10. Model this wing using a single horseshoe vortex with a constant strength F and its bound vortex at Ine... Q: Consider an aircraft with a rectangular wing and a rectangular horizontal stabilizer as shown in the diagrams below. Three different horizontal stabilizer locations are being considered: a low tail,... Q: For this assignment, you will use the same aircraft from the Module 1 and 3 homework assignments. You may work in either the SI or BGS system, but you must be consistent. 1. Using the same aircraft... Q: Consider a rectangular wing with an aspect ratio of 6, an induced drag coefficient = 0.055, and a zero-lift angle of attack of 2. When the angle of attack is 3.4, the induced drag coefficient of the... Q: Effects of different wing shapes on aerodynamic performance of an Aircraft. i mean, based on the shape of the wing like:- Rectangular wing Tapered straight wing Elliptical wing Swept wing Delta wing... Q: 1.36. 1.37. 1.38. Write a computer program that uses the numerical lifting-line method presented in Sec. 1.9 to predict the lift and induced drag for a tapered wing with linear geometric and... Q: Can I get the solution for this? Thank you 20 points A 200-kg experimental glider with a semi-span of 7 m and chord of 1m (rectangular wing) was released at a standard altitude where the temperature... Q: Accounting for conversion of bonds. Symantec has convertible bonds outstanding with a face value of $10,000,000 and a carrying value of $10,255,000. Holders of the bonds convert them into 100,000... Q: Yoda pic specialises in the manufacture and distribution of action figures of popular movie characters. It operates under two divisions, Luke (manufacturing) and Leia (distribution). The financial... Q: Question 4 8 2 pts If 1 buys $ 1 . 3 5 , then the reciprocal states that $ 1 buys what? Q: When Crossett Corporation was organized in January Year 1, It Immediately Issued 4,200 shares of $51 par, 6 percent, cumulative preferred stock and 9,500 shares of $6 par common stock. Its earnings... Previous Question Next Question Recommended Textbook More Books Vector Mechanics For Engineers Statics Authors: R.C.Hibbeler 7th Edition 978-0072931105, 0072931108 Ask a Question and Get Instant Help! Study Help Services Sitemap Fun Definitions Become Tutor Used Textbooks Study Help Categories Recent Questions Expert Questions Campus Wear Sell Your Books Company Info Security Copyrights Privacy Policy Terms & Conditions SolutionInn Fee Scholarship Online Quiz Give Feedback, Get Rewards Get In Touch About Us Contact Us Career Jobs FAQ Student Discount Campus Ambassador Secure Payment Download Our App © 2026 SolutionInn. All Rights Reserved $