Hello,

I need help to solve those questions.. I don't need you to create the presentation.

Please solve with explanations:

1-6 or A-F

Please see the instructor input with the required info - about the numbers to the definitions.

3.2 Narrated Presentation Assignment: Drag 100 Points Possible Due: Sun Apr 7, 2024 11:59pm In Progress NEXT UP: Submit Assignment ETJ A camment Attempt 1 Rt Unlimited Attempts Allowed v Details P32 Drag Narrated Presentation Assignment Overview For this assignment, you will solve versions of problems from your textbook and create a narrated presentation to report your findings. Present the topic as if you are explaining it to someone unfamiliar with aviation. Details The problems you will solve are similar to those at the end of Chapter 5; however, the values will be changed (see below) to keep the problems unigue. You can practice with the questions in the book; answer keys are located after the final chapter to check your work. Solve these problems: 1. A 10xxx-Ib aircraft has an (L/D)MAX value of 9.8; find its minimum drag. For aircraft weight, enter the first three numbers of your phone number after "10" (For example, if your phone number starts with 412, enter aircraft weight as 10,412 Ib). To find minimum drag, use equation 5.12 from the textbook, also provided here: w Dmin = TIx (5 maz 2. If the aircraft in Problem 11 has a wing area 5=2xx ft? and the value of C,=0.5 at L/Dmax, find the sea level airspeed where Dy occurs. (We will call this V] .) For wing area, enter your age after "2" (for example, if you are 30, then you would enter $=230 ft). Note: To solve for V7, reference Table 2.1 Standard atmosphere table and Equation 4.4 (Velocity equation derived from the Lift equation). 3. For the aircraft in Problem 11, find D; and D, at (L/D)max- 4. For the aircraft in Problem 11, complete the following table and plot D;, Dy, and Dy in Excel. (Vs + V)2 Dy = 1Din (V2 + W) (W1 + V32 D; = 1Dpin(Vi = V2)?|Dr = D, + D; Use Excel to create the table and your total drag curve for question 14. Review the following tutorials: ASCI 309 Excel tutorial (9:51/ERAU) Bookl - Excel CHART TOOLS FILE HOME INSERT PAGE LAYOUT FORMULAS DATA REVIEW VIEW DEVELOPER ACROBAT DESIGN FORMAT . . . Add Chart Quick Change Switch Row/ Select Element - Layout * Colors . Column Data Chart Typ Chart Layouts Chart Styles Data Type Chart 1 I X Vf A C D E G H N 0 P Q 1 Starting Para 1 15 2 Starting Para 2 3 Starting Para 3 4 sum 100 400 Chart Title + 900 35000 55 1600 2500 30000 75 3600 85 4900 6400 20000 90 105 8100 15000 100 115 10000 101 10201 10000 102 117 10404 5DOO 103 118 10609 104 119 10816 125 12100 100 150 200 250 120 135 14400 9:35 / 9:51 180 195 32400 190 205 36100 ASCI 309 Excel Tutorial Transcript (DOCX) & ASCI 309 Excel Diagram work (4:58/ERAU) eck2 - Excel CHART POOLS THE HOME INSERT PAGE LAYOUT FORMULAS DATA REVIEW VIEW DEVELOPER ACROBAT DESIGN FORMAT Weinke, Stefan 14 0 .- Add Chart Quick . . Chart Layouts Chant Styles Chart 1 . : X v f N P Format Axis Title TITLE OPTIONS * | TEXT OPTIONS WKTAS) qipsf) Dp(1b) DI(1b) DT(1b] PR(hp) 7.179 1 582 0.00547 0 0.1395 0.13897 11.9835 5.76774 140.77 146.537 20.7407 12.203 0.931 0.00547 0.04624 0.05171 18.0057 9.81231 8 82 94 92.7523 17.1235 80 21.695 0.524 0.00547 0.01465 0.02012 26.0476 17.4447 46.7116 64.1563 15.7923 FILL 0 33.896 0.335 0.00547 0.00599 0.01146 29.2423 27.257 29.8283 57.0853 17.5647 Chart Title BORDER 120 48.814 0.233 0.00547 0.0029 0.00837 2 7 27 8508 39.2509 20.7807 60.0316 22.1655 140 66.441 0.171 0.00547 0.00156 0.00703 24.3278 53.4245 15.2265 68.651 29.5728 30 No line 150 88.781 0.131 0.00547 Solid line 180 109.831 0.103 0.00547 0.00057 0.00604 17.0643 Gradient line 200 135.593 0.084 0.00547 0. Automatic 220 164.068 240 195.254 bokor 260 229.153 Transparency 280 265.763 69 229.467 750 " Width Compound type Zach type Cap type Join type Begin Atraw type Begin Arrow gue End Agrow type End Arrow size 4:25 / 4:58 Sheetl ASCI 309 Excel Diagram Work Transcript (DOCX) +Once created, utilize your derived table and diagram data to answer the following associated questions: A. What are the minimum drag parameters for your aircraft? e Minimum drag value D(min) Speed VD (min) at which minimum drag occurs Relationship between Dp and Di at D (min) B. What are the maximum lift to drag ratio CL/CD parameters for your aircraft? (CL/CD)max value Speed at which (CL/CD)max occurs C. Compare answers in A and B and comment on the findings. D. Explain which of your derived values will allow glide performance predictions for your aircraft and quantify best glide conditions with specific values. E. Explain the origin and effects of aircraft design and operating influences on induced drag. F. Explain sources of parasite drag and methods to reduce it. When doing any math, round to the nearest hundredth value (0.01), always include your units, and show your work for full credit. Requirements Support your work with equations, diagrams, and dialogue as appropriate, and include an explanation of what you are presenting. There is no minimum or maximum number of slides. You should utilize tools such as Math Type to help with the overall presentation rather than inserting photos of handwritten work. Include an APA-formatted reference slide. Please visit the Field Exercises and Presentation Resources page for pertinent spreadsheets, resources, and websites that may assist you in completing this assignment. Please review the Media Hub, a multimedia resource guide/ERAU, B for suggested software tools and resources you can use for your course activity. Save your assignment using a naming convention that includes your first and last name and the activity number (or description). Do not add punctuation or special characters. Students, Sorry for the confusing instructions for mod 3 (I did not make up these instructions, someone else did!) 1- You do not use your aircraft from Mod 2 presentation- 2-Go to Chapter 5 in the text book and go to the questions at the end of the chapter- look at question 11 and it gives you the weight {10,000ibs) and it says the L/D Max is 9.8 - So you use this data to find DT Min. So everyone just use a different weight by adding or subtracting whatever you want. 3- Just use a wing area of 240- Aspect ratio of 5- Temp Standard- sigma 1 (sea level), Cdp of .021-Clmax at stall 1.5 4-now go to the Drag Excel Spread sheet- "Course Specific Information/ Field and presentation Resources" You will find a Drag Excel Spreadsheet you can use to do the work- 5-put in the above data to create a drag table and insert that in the presentation (don't use the one in the instructions). 6-In the same area you found the Spreadsheets, find the tutorial on how to create a drag curve and then put that in your presentation- Now answer the following questions in your presentation- Once you have created your table, answer these questions. 1. What are the minimum drag parameters for your aircraft? 1. Minimum drag value D(min) 2. Speed VD (min) at which minimum drag occurs 3. Relationship between Dp and Di at D (min) 2. What are the maximum lift to drag ratio CL/CD parameters for your aircraft? 1. (CL/CD)max value 2. Speed at which (CL/CD)max occurs 3. Compare answers in A and B and comment on the findings. 4., Explain which of your derived values will allow glide performance predictions for your aircraft and quantify best glide conditions with specific values. 5. Explain the origin and effects of aircraft design and operating influences on induced drag. 6. Explain sources of parasite drag and methods to reduce it. Although this is supposed to be a narrated presentation | don't put much value to it in your grade- Do not put added information in your presentation that is not asked for (mod 2 some of you had 3-5 slides about how an airplane flys (lift) yet it was not asked for or required. Please feel free to use fun pictures and humor in your presentation