Mục tiêu học tập • Phần 1 Bối cảnh Công nghiệp • Phần 2 sân bay Kế hoạch • • • • • Hệ thống sân bay Mỹ • Cải thiện sân bay Capitol Kinh phí sân bay Quy hoạch sân bay Gió bố trí kế hoạch Rose Phân tích Chỉ Runway (Bài tập về nhà vấn đề) • Phần 3 Thiết kế Hướng dẫn • Phần 4 Xây dựng | 8 Baggage and cargo handling Eqn. 8 9 Operational items See Section . 10 Paint See Section . Step 6i The following list itemizes all required input data for estimating the weight items listed in steps 2 and 5. WT0 127 000 lbs nult s 1 296 ft2 vc 295 kts VD - 369 kts nult A 10 X -A 1 4 35 deg. A 2- 33. 5 deg Mn 0. 85 n t c ra b ft fcr ft sh 254 ft2 b. ft n trh ft c ft lh ft sv 200 ft2 zh bv - 0 v - ft s _ S r V s - A 1 . 8 - 1 4 45 đeg. If ft Wf hf ft qD 461 psf WT 7 505 lbs n 14. 1 d ft Jj Ulu X X p 20 psi 1 ft A. ft 2 2 c n ini Dinl - 6- ft Notes 1 The value for n . follows from the v-n diagram of Figure . 2 Most data were obtained from Ourania data listed in Part II. The reader is reminded that a detailed geometric definition may be found in Part II as Table a Class I weight statement as Table . Detailed definitions of layouts of fuselage powerplant wing high lift system empennage and landing gear may be found in Chapters 4 5 6 7 8 and 9 respectively. Step 7 Tables - list all weights computed as part of the Class II weight estimation process. Part V Chapter 4 Page 54 step 8 The Class II empty weight of the Ourania is 72 622 lbs. This compares with 68 450 lbs for the Class I weight estimate. This represents a difference of 4 172 lbs which is percent of the Class I empty weight. Several comments are in order 1. an iteration through the equations of step 7 should be performed to determine the convergence empty weight. 2. several weight savings can be made in the Ourania a the empennage can be manufactured from composites which would yield a weight saving of about 15 percent or 359 lbs. b the nacelles can be manufactured partially from composites which would yield a weight saving of about 10 percent or 264 lbs. c by manufacturing the low stress areas of the wing and fuselage from composites a weight saving of about 5 percent should be .