Help
Options
Didn't know it?
click below
click below
Knew it?
click below
click below
Don't Know
Remaining cards (0)
Know
retry
shuffle
restart
0:00
Embed Code - If you would like this activity on your web page, copy the script below and paste it into your web page.
Normal Size Small Size show me how
Normal Size Small Size show me how
MAE 4350 Exam 1
UTA Aerospace Senior Design 1: Exam 1: Study Set
| Term | Definition |
|---|---|
| Project Initiation (Left Side of Ladder) | System Selection |
| Parametric Sizing (Left Side of Ladder) | Design Sizing & Screening |
| Configuration Layout (Left Side of Ladder) | System Definition |
| Configuration Evaluation (Left Side of Ladder) | Design Convergence & Baseline Selection |
| Project Initiation (Right Side of Ladder) | 1.) Mission(s) Selection 2.) Design Family Selection |
| Parametric Sizing (Right Side of Ladder) | 1.) Sizing Process 2.) Solution Space Generation 3.) Screening & Sized Vehicle Selection |
| Configuration Layout (Right Side of Ladder) | 1.) Mission & Operation Definition 2.) Configuration Definition |
| Configuration Evaluation (Right Side of Ladder) | 1.) Reconvergence Process (Time Permitting) 2.) Solution Space Generation 3.) Design Risk Assessment 4.) Baseline Selection |
| The 7 Steps to the "Standard - to - Design Ladder"? | 1.) Analyze 2.) Integrate 3.) Iterate 4.) Converge 5.) Screen 6.) Visualize 7.) Assess Risk |
| What were the lessons learned from the Foa-Sears Flying Wing Debate | 1.) Still not Resolved 2.) Design theory alone is insufficient 3.) Design Capability vs. Design Requirement Mismatch 4.) Technology can reverse an earlier conclusion 5.) Loss of knowledge is a major problem 6.) Form follows function |
| What two brothers created the first flying wing? | The Horton Brothers |
| What is the most accurate aerodynamic modeling approach currently in use? | Computational Fluid Dynamics (CFD) |
| What is neglected in Potential Flow Theory? | Viscosity and rotation |
| Why are simplified models used in conceptual design? | Fast turn around, less data required, and sufficient accuracy |
| What is the ideal lift distribution? | Elliptical |
| What are the key tradeoffs in aerodynamic modeling? | Accuracy vs. Computational time |
| What determines maximum range? | Maximum L/D |
| What determines maximum endurance? | Minimum power/thrust required to remain airborne. |
| What conditions give steady, level, flight? | Lift = Weight Thrust = Drag |
| What determines climb and acceleration capability? | Thrust - to - Weight ratio |
| What is a flight envelope? | The allowable, and safe combinations of speed, altitude and load factor given an aircrafts structural limits. |
| What is takeoff weight composed of? | - Empty Weight - Fuel Weight - Payload |
| Why is takeoff weight iterative in design? | Weight affects fuel -> Fuel affects weight |
| What is wing loading? | W/S = Weight / Wing Area |
| What does a high wing loading imply? | - Higher Speed - Worse maneuverability - High Stall Speed (Low aspect ratio case) |
| What does a low wing loading imply? | - Better maneuverability - Low stall speed |
| What defines a final design point in a solution space? | Intersection of all performance constraints? |
| What does a high aspect ratio do? | - Reduce induced drag - Gets 3D Lift Coefficient closer to 2D lift coefficient |
| What does wing sweep do? | Delay compressibility effects (Higher mach numbers) |
| What is the definition of taper ratio? | Tip Chord / Root Chord |
| What is the danger of highly swept wings? | - High stall speeds - Tip stall |
| What is the best type of airfoil for subsonic flight? | Thick, cambered airfoils |
| What is the best type of airfoil for supersonic flight? | Thin, sharp airfoils? |
| What is convergence? | Narrowing toward a final, feasible design/ |
| What is the LOFTIN Method used for? | Determining feasible combinations of W/S and T/W using performance constraints |
| What four distinct speed related regimes are there? | - Subsonic (0 < M < 0.8) - Transonic (0.8 < M < 1.2) - Supersonic (1.2 < M < 5) - Hypersonic (5 > M) |
| What are the four conceptual design phases in AVDS methodology and what are their objectives? | Project Initiations - Determine mission selection and design family Parametric Sizing - Initial Sizing of vehicle parameters Configuration Layout - Determine internal and external configuration Configuration Evaluation - Final convergence |
| What rulebook documentation sets the standards for civil, commercial, and military aircraft? | Federal Aviation Regulation (FAR) Civil - Part 23 Commercial - Part 25 Military Aircraft - MIL - STD |
| List two aerodynamic derivatives for the following: 1.) Longitudinal 2.) Directional 3.) Lateral | 1.) CL_alpha, Cm_alpha 2.) Cn_beta, CY__beta 3.) Cl_beta, Cl_r |
| What is on the x and y axis of a AVDS-EDU PS solution space respectively? | Planform area TOGW (Take Off Gross Weight() |
| What limits the LOFTIN method when compared to the AVDS method | Loft - Propeller only, subsonic only, uniterative, no convergence, only concerns T/W & W/S. Constraints: Field Performance, Speed Performance, Climb Performance |
| What are the advantages of the AVDS method when compared to the LOFTIN method | Gas convergence, is iterative, uses a multitude of inputs with limited constraints such as performance metrics and DCFC |
| What are the inputs and outputs of the LOFTIN Method? | |
| What is the purpose of the horizontal tail volume coefficients? | It measures the effectiveness of the horizontal tail in producing a pitching moment utilizing horizontal tail area multiplied by the tail moment arm, divided by the wing area times mean aerodynamic chord. |
| What is the purpose of the vertical tail volume coefficients? | It measures the effectiveness of the vertical tail in producing a yawing moment utilizing vertical tail area multiplied by the tail moment arm, divided by the wing area times mean aerodynamic chord. |
| Why is there no weathercock type stability in roll? | Roll does not naturally create a restoring moment from asymmetric side forces like yawing weathercock stability. |
| How do aircraft designers create stability in roll? | Introduce dihedral which - Creates a sideslip when a/c rolls - One wing produced more lift than the other when a/c rolls Wing sweep - Advancing wing sees higher effective velocity High wing config Vert tail contribution |
| What was the purpose of the TU-144 retractable canard in terms of stability and control, flight performance. | Purpose - Increase lift & pitch control on take off and landing approach s&c - Provides additional nose-up pitching moment and enhances trim capability Flight Performance - Higher effective lift - Lower Stall Speed - Shorter takeoff/landing |
| Summarize the Project Initiation Phase | In this phase, mission and design parameters are identified and justified. |
| Summarize the Parametric Sizing Phase | In this phase, the design solution space is generated, screened, and a sized vehicle is selected. |
| Summarize the Configuration Layout Phase | In this phase, the internal and external geometry is defined to suit the refined mission. |
| Summarize the Configuration Evaluation Phase | In this phase, higher fidelity tools are utilized to reconverge the fully configured designs, leading to a baseline design. |
| What is the Sears Haack Body? | The optimal fuselage geometry for transonic + flight Minimizes wave drag Uses area ruling |
| Define the area rule | Area rule states that for minimum transonic wave drag, an aircrafts total cross-section area distribution along its length must vary smoothly, avoiding abrupt changes that generate strong shockwaves. |
| Discuss the aerodynamic and stability & control, and geometry affects of a forward swept wing | Airflow travels from tip to root, reducing tip stall at high AoA Increased transonic efficiency NP is often ahead of the CG, increasing maneuverability but is unstable. Aeroelastic Divergence causes twist, often leading to structural failure |
Created by:
user-2032739
Popular Engineering sets