aerodynamics homework help

Boost your journey with 24/7 access to skilled experts, offering unmatched aerodynamics homework help

Trusted by 1.1 M+ Happy Students

4.4Trust Pilot

4.4Edu Reviewer

5App Review

4.8Student

WhatsApp Support

Get Instant
Online Homework Help
via WhatsApp

Get instant homework help from top tutors—just a WhatsApp message away. 24/7 hw help support for all your academic needs!

★★★★★

2M+ students trust TutorBin

Your WhatsApp Number

⚡ Instant reply

🔒 100% private

👨‍🏫 Top tutors

🌍 All subjects

^*Get instant homework help from top tutors—just a WhatsApp message away. 24/7 support for all your academic needs!

2M+ Students Helped24/7 Live SupportExpert TutorsAll Subjects CoveredInstant Response100% ConfidentialTop Rated ServiceMoney-back Guarantee2M+ Students Helped24/7 Live SupportExpert TutorsAll Subjects CoveredInstant Response100% ConfidentialTop Rated ServiceMoney-back Guarantee

Recently Asked aerodynamics Questions

Expert help when you need it

Q1: AERO 480 Assignment Problem Consider a jet trainer with following characteristics: Weight & Dimensions • Max weight - 7600 kg Wing Span -9.72 m • Wing Area - 23.52 m² Power plant • 2 Honeywell F124-GA-200 (twin engine) Maximum Thrust - 2* 2850 kg Aerodynamic CD 0.25 0.2 0.15 0.1 0.05 хо Y 0.003 0 -2 -1.5 -0.5 0 C -M-0.3 0.5 1 1.5 2 Using the data given above Plot the following: CL vs CD for M= 0.5 & 0.7 using the data given in the graph (Use compressibility correction) Thrust required at (a) sea level; (b) 10000 ft. • Power required at (a) sea level; (b) 10000 ft. • Excess power at (a) sea level; (b) 10000 ft. • . Excess power at (a) sea level; (b) 10000 ft. (if one engine failed & rudder has sufficient yawing control) Plot CL | CD' C1/2 C³/2 !²/CD' 12/CD vs Speed at (a) sea level; (b) 20000 ft. Calculate: • The Maximum speed at (a) sea level; (b) 10000 ft. • • The Maximum speed at (a) sea level; (b) 10000 ft. (if one engine failed & rudder has sufficient yawing control) The Stall Velocity (a) sea level; (b) 10000 ft. if CL,max = 2.0 The Maximum rate of climb at (a) sea level; (b) 10000 ft. The Maximum rate of climb at (a) sea level; (b) 10000 ft. (if one engine failed & rudder has sufficient yawing control) The Speeds at maximum rate of climb at (a) sea level; (b) 10000 ft. • • Service Ceiling of the aircraft Service Ceiling of the aircraft (if one engine failed & rudder has sufficient yawing control) • The minimum sink rate at (a) sea level; (b) 10000 ft. • The Speeds at minimum sink rate at (a) sea level; (b) 10000 ft.See Answer
Q2: CIVL 321 LABORATORY Spring 2023 Objective: Fluid Mechanics Lab #11 Aerodynamic Drag and Lift To determine the drag and lift coefficients of a model using the closed-loop wind tunnel with 28"x20" test section in LANG 122. Specifically, determine the drag and lift coefficients of a NACA 4412 airfoil- shaped wing model at relatively high Reynolds number(s) as a function of the angle of attack (a) and compare with published data. Theory: The total drag force of an immersed body consists of viscous drag (skin friction) and pressure (form) drag. Lift is solely due to pressure effects. The drag and lift coefficients and Reynolds number for airfoil- shaped wings are normally defined as: CD = 2FD PAU² CL = 2F PAU² Uc Re= V where FD is the measured drag force, FL the measured lift force, p is the fluid density, U the upstream fluid velocity (relative to a stationary body), A, is the planform area of the body (i.e., the area seen from above at zero angle-of-attack), c is the chord length of the airfoil-shaped wing, and v is the fluid kinematic viscosity. Refer to Sections 9.3 and 9.4 of your textbook for more information. Procedure: 1. If necessary, install airfoil mount and secure airfoil-shaped wing with screws with the help of the instructor. 2. Turn power to Force Balance Pitch/Yaw Control system ON. Release locking bolts on the wind tunnel force balance (do NOT lean on the frame) and then tare lift and drag displays. 3. The RP240 PITCH and YAW control panel should now be displaying a short prompting message. Re- tare the lift and drag displays if necessary. 4. Start the wind tunnel by performing steps 1 through 8 of the closed loop wind tunnel start-up procedure shown below. 5. Set the speed control to a value indicated by the instructor and record 1) the pitot-static tube deflection in inches of H2O; 2) the local static pressure in inches of H₂O; 3) the barometric pressure in kPa, and 4) the temperature in °C. The difference between the local static pressure and barometric pressure is a measure of how much the static pressure in the wind tunnel is below atmospheric pressure. This will allow you to calculate the air density in the wind tunnel using the Ideal Gas Law. Watch your units!!! 6. Select the PITCH axis (Press F1 on the RP240) and enter -12° (angle of attack). Record the drag and lift forces (lbs) indicated on the meters. 7. Increase the airfoil/wing angle of attack in increments of 2° up to +20°, recording lift and drag values for each angle. Return the airfoil to 0° angle of attack when finished. 8. To obtain lift and drag for other velocities, repeat steps 5 through 7 and record the necessary data. 9. Return airfoil to 0° angle of attack and follow the shutdown procedure for the wind tunnel below. 10. Press EXIT (F6) on the RP240 PITCH and YAW control panel. 11. Carefully secure all four locking bolts. Pay close attention to the load cell displays - try to keep displayed loads <2 lbs. as the bolts are being tightened. 12. Turn power to force balance control system OFF. Operating Procedure for Closed-Loop Wind Tunnel: Start-up: 1. Make a visual inspection to ensure no loose objects were inadvertently left in the wind tunnel and latch the door(s) shut. Scanned with CamScanner 2. Turn on the Test Section Lights. 3. Turn on the wind tunnel Master Power switch. The Wind Tunnel Speed Control should illuminate and control should initialize to the stopped condition. 4. Open (if not already) the Magnetic Clutch Water Valve (ball valve on left) and press the Clutch Cooling On button. Make sure water is circulating by checking the drain valve in the Southeast corner of the lab. 5. SLOWLY open the heat exchanger water inlet valve (it is the ball valve on the right) 6. Press the Motor Start button. The clutch output will slowly reach an idle speed of 250-300 RPM 7. Press P1 on the Wind Tunnel Speed Control to access manual control on the Run potentiometer. 8. Set the Run to desired RPM by adjusting the potentiometer and press Run. This initiates live control of the fan motor. For the first test use 800 RPM. When ready for the second test, SLOWLY adjust the potentiometer to 1100 RPM. Shut-down: 1. Press the Stop button on the Wind Tunnel Speed Control. 2. Allow the motor to coast to idle speed of 250-300 RPM. 3. Press the Motor Stop button. 4. SLOWLY close the heat exchanger water inlet valve (located on right) 5. When motor has coasted to a stop, push the Clutch Cooling Off button to stop the motor/clutch cooling water. 6. If the Magnetic Clutch Cooling Valve (ball valve on the left) was open when you started, then leave it open. Otherwise close it. 7. Turn off Master Power switch. 8. Turn off the Test Section Lights. 9. Turn off Main Electrical Cutoff Box. Velocity Measurement with the Pitot Tube: The Pitot tube, when properly connected to a manometer or pressure transducer, measures the difference between the stagnation pressure and static pressure of a fluid flow (AP). The velocity of the fluid at the static pressure tap, which is essentially the freestream velocity (U); can be determined from the Bernoulli equation: U = 2AP P = 2pmgh P where p is the density of the flowing fluid, pm is the density of the manometer liquid at standard conditions, and h is the deflection of the manometer liquid level read from the inclined scale. This scale is calibrated to read inches of H2O, so pm is the density of water at room temperature. The measured drag force includes both the drag on the wing and the vertical mounting strut. The drag on the mount was determined independently as: Fam = 1.4604×10-5V2.281, where V is measured in ft/s. Subtracting Fam from the measured drag force will correct for the additional drag on the strut so you obtain just the drag force on the wing. Material to be Included in Report in Addition to Normal Requirements: 1. Prepare an Excel graph of the lift coefficient (CL) versus angle of attack (a). Indicate the angle of attack at the point of stall (acmax) and the zero-lift angle of attack (ac=0). Compare with published results and discuss any differences. Compare the plots for the data collected at 70 mph versus 100 mph (you can plot both data on the same graph). Why does this result occur even though they are collected at different speeds? 2. Prepare an Excel graph of the drag coefficient (CD) versus lift coefficient (CL) and label each data point with the corresponding angle of attack. This is called a drag polar diagram (Figure 9.35b). Find the angle of attack where lift- to-drag ratio is maximum. Compare with published results given in your lab manual and discuss any differences. Note: Drag polar plots in many aerodynamics books are plotted with the drag coefficient on the y-axis and the lift coefficient on the x-axis. 2 Scanned with CamScanner Airfoil Designation: NACA 4412 chord: 5 in. span: 16 in. 800RPM 1100RPM Settings Test 1 Test 2 Yaw: 0 0 degrees Initial Pitch: 0 0 degrees Pitch increment: 2 2 degrees Pitot-static Pressure: 2,67 4.61 in. H₂O Local Static Pressure: 387 .710 in. H₂O Barometric Pressure: 10016 100.6 kPa Air Temperature:| 22.2 22.9 °C Tunnel Static Pressure: units Air Density units Air Speed units units Kinematic viscosity (air)| Reynolds No. (chord length): Test 1 Test 2 Angle of Attack, a Drag Force (degrees) (lbs) Lift Force (lbs) Drag Force Lift Force (lbs) (lbs) -12 1.212 2. h 2.242 4.47 -10 1.033 -1.33 1.874 -3.19 -8 0.831 1.20 1.438 -1.79 -6 2.723 10.48 1.298 -0.19 -4 0.677 0.32 1.262 1.50 -2 0.665 1.17 1.277 3.88 0 9.653 1.97 1. 330 5.68 2 0.708 3.10 1.447 7.45 4 0.776 4.01 1.597 9.13 6 0.854 4,84 1.776 10.58 8 0.972 5.61 1.998 11.97 10 1.101 6.26 2.235 13.12 12 1.224 6.79 2.532 14.99 14 1.350 7.10 2.353 14.73 16 1.541 7.39 4.210 11.09 18 1.729 7.43 4.592 11.10 20 2.338 5.37 4.803 11.17 Scanned with CamScannerSee Answer
Q3:3) Calculate the free rudder neutral point for the aircraft whose characteristics are given below. Determine its longitudinal static stability. dɛ = 0.4, 0.4, n=1.0 спос = -0.005 [1/º] (CL)=0.09 [1/º], (c) = 0.08 [1/º], =-0.003 [1/9], da Спо = 0.0, Cha x. ac = 0.5 0.8 Xcg x 0.3, S₁ = 3.5 m² S₁ = 10 m² 0.55 0 τ 0.35 0.7 Control Surface Area Lift Surface AreaSee Answer
Q4:1) Given a rectangular wing of aspect ratio 6 and area of 600 ft². The wing section employed is an NACA-4412 airfoil with an aerodynamic center at 0.24c and Cm ac= -0.088. If the wing is balanced so that the c.g. lies on the wing chord but 6 in. ahead of the a.c., calculate the lift/lift coefficient for which the wing would be in equilibrium (Cmcg=0). Is this lift coefficient useful? Is the equilibrium statically stable? Calculate the position of the c.g. for equilibrium at CL=0.4. Is this equilibrium statically stable?See Answer
Q5:Part 2: Written Project This assessment involves the final submission of your completed Written Project. This assessment makes up 50% of your overall module mark. Guidance: In your written project you should: Appropriately cover the topic of the extended project. Address the question(s) you set out to investigate, by researching, analysing and using information from relevant sources. Represent the complexities of the project topic. Analyse project outcomes and draw conclusions. Include a complete list of references used in producing the project. Please note: Kaplan International Pathways 1 kaplanpathways.com Both parts of this assessments are individual tasks, which means that you are expected to complete them by yourself. Before you submit your final written project, please make sure you carefully consider feedback you have received on your draft written project submission from your teacher. The suggestions made by your teacher will help you make your final submission more effective./nPart 2 Written Project You must choose a structure for your project which will best suit your topic and the question(s) you are investigating. Your project should be structured as follows: 1. Introduction (300 - 400 words) 2. Main part of project: exploration of sources through description of key issues/discussion/development/analysis Please note: this part of your project should have more than one section. The way you structure this should be decided by you, with support from your tutor. Your structure will depend on the topic you have chosen and the 'story you want to tell' (2350 words) 3. Conclusion (200-250 words) 4. References (not included in word count) 5. Appendices (if applicable) e.g.: any data sets you have used (not included in word count)/nPart 2 Written Project Your grade for Part 2 will contribute 50% of your overall module mark. It will be marked using the following areas and weightings: 5. Task achievement (25%) Have you followed the instructions for producing your Written Project? Have you chosen an appropriate topic for your project? Have you investigated the topic in sufficient detail? Have you addressed all the research questions? Have you considered the topic/questions from a variety of angles? Have you formatted your project appropriately and submitted it correctly, as specified in the instructions? 6. Use of sources (25%) Have you selected relevant sources for your project and used them in your project to support your claims? Have you synthesised information from a range of sources in your project? Have you analysed the information from the sources thoroughly and linked it with your project topic? Kaplan International Pathways 7. Structure (20%) Have you organised your project clearly into sections and arranged them in a logical order? Have you linked the ideas in your paragraphs? Do you use signposting language effectively? 8. Academic Integrity (15%) kaplanpathways.com Is your paraphrasing/summarising successful in terms of retention of meaning? Have you included an accurate citation with each paraphrase/summary? Are all quotes (if used) correctly marked? Do you have a full list of matching references which are correctly formatted (including organisation in alphabetical order and NO bullet points or numbering)? Are all facts/data presented genuine, accurate and precise? 9. Clarity of expression (15%) Have you checked the accuracy of your written language? Have you explained complicated concepts to help your reader? Have you used topic-specific vocabulary accurately? You will receive a % mark in each of these categories. The overall mark will be a percentage (0-100%)./n2 Introduction Over a century, important turning points in the history of aerospace innovation have transformed the skies above industry below. Presently, the industry is at the forefront of technological innovation, emphasizing the improvement of performance, efficiency, and safety through state-of-the-art innovations. The purpose of this report is to investigate how aerospace advancements can be applied to shape the future. We investigate how advances in materials science, manufacturing processes, and artificial intelligence (Al) are transforming the aerospace sector and beyond. Background Information on Aerospace Innovations There have been several significant historical tuming points in the intriguing journey of aerospace developments. The Wright brothers' successful powered flight in 1903 is considered the beginning of aviation. But it wasn't until the middle of the 20th century that the aerospace industry saw several notable breakthroughs that opened up new possibilities. Aerospace technology underwent a boom of improvements following the end of World War II. In order to increase speed and efficiency, military aircraft powered by piston engines were switched to jet engines during the conflict. This change paved the way for improvements in civilian aviation. In the 1950s, the military began developing small jet-powered aircraft for VIP transport. Learjet and Dassault Falcon were among the pioneering companies introducing private jets in the early 1960s, revolutionizing executive transportation. The introduction of the Boeing 747 in the 1970s marked a turning point in private and commercial air travel. With its expansive size and luxurious amenities, the 747 offered unprecedented comfort and convenience for private fliers, including heads of state and celebrities. Aerospace technology has undergone remarkable advancements over the decades, enhancing safety, efficiency, and comfort in private flying. The introduction of jet engines, which provide simplicity, dependability, and improved performance over piston engines, changed aircraft propulsion. The creation and broad application of GPS technology transformed aviation navigation. GPS replaced traditional ground- based navigation by improving aircraft safety, efficiency, and precision with pinpoint accuracy and real-time positional data Grady (2018)./nAerospace Innovations & Applications In order to improve performance, efficiency, and safety, the aerospace industry is at the forefront of technical innovation, continuously pushing the limits of materials and production processes. Two main areas of interest have surfaced in recent years: the investigation of lightweight materials for improved fuel efficiency and the use of additive manufacturing for quick prototyping and customization. Not only can lightweight materials save gasoline, but they also improve performance and payload capacity. High strength and stiffness CFRP composite materials are among the cutting-edge materials being investigated; these properties make them perfect for use in aeronautical applications. They are lighter than traditional materials like aluminum and offer excellent fatigue resistance. MMCs combine lightweight metals with ceramic reinforcements, resulting in materials that are both strong and lightweight. Intermetallic compounds offer superior strength and corrosion resistance compared to conventional alloys (Portolabs Manufacturing Accelerated 2021). The aircraft sector has experienced a change because of additive manufacturing (AM), sometimes referred to as 3D printing, which offers quick prototype and customization options. Engineers may design complicated interior structures and intricate geometries with additive manufacturing (AM) that are hard or impossible to accomplish with conventional manufacturing techniques. Engineers may test ideas and iterate designs more quickly with additive manufacturing (AM) before moving forward with full-scale production. Additionally, AM makes it possible to produce bespoke parts on demand that are suited to certain aircraft configurations or mission requirements. By leveraging lightweight materials and additive manufacturing technologies, aerospace companies can achieve significant improvements in fuel efficiency, performance, and operational flexibility, ensuring a sustainable and competitive future for the industry (Crawford, 2017). Autonomous drones represent a significant advancement in aviation technology, leveraging Al integration to achieve various objectives across industries. Autonomous drones equipped with Al integration are revolutionizing surveillance and security operations. These drones can autonomously patrol predefined areas, analyze live video feeds in real-time using computer vision algorithms, and identify potential security threats or anomalies. Al algorithms play a critical role in predictive/nmaintenance strategies with in the aviation industry, enabling proactive identification of potential equipment failures or maintenance issues before they occur. By analyzing vast amounts of sensor data and historical maintenance records, these algorithms can predict component failures, optimize maintenance schedules, and prevent costly unplanned downtime (Shah, Trivedi, & Tank, 2022). By detecting early warning signs such as abnormal vibrations, temperature fluctuations, or wear and tear, these algorithms can alert maintenance teams to take preemptive action, thereby reducing the likelihood of unscheduled maintenance events and optimizing asset reliability. Conclusion Aeronautics manufacturing faces significant challenges and ethical considerations. Ethical dilemmas emerge with Al integration, posing questions about accountability, and data privacy. The aerospace industry continues to soar on wings of innovation, driven by material advancements, manufacturing techniques & Al integration. From lightweight materials to additive manufacturing drones, each innovation reshapes the future of flight, promising enhanced efficiency, safety & sustainability.See Answer
Q6: 1. Introduction The Final Year Project (FYP) gives you a unique opportunity to study an area related to your course in depth. It also enables you to develop and demonstrate a range of transferable skills. The FYP is an important element of your Engineering degree programme. It represents 25% of the marks (30 credits) allocated for the 3rd year. Unlike other modules, the FYP cannot be compensated, so you must successfully pass in order to achieve an accredited Honours Degree. 1.1. Basis of the FYP Extended projects like the FYP permit the development of many of the generic skills that the graduate engineer may be expected to have. Included in this are: ● ● meeting deadlines and working within other externally defined constraints, tackling work which lacks a well-defined outcome, or which has a wide range of possible answers, ● opportunities to be creative, putting technical work in a social and commercial context, presentation of technical information in various ways, searching published sources of information, applying technical knowledge to unfamiliar problems. ● ● FINAL YEAR PROJECT ● ● 1.2. Objectives of the FYP In general, the FYP objectives are to demonstrate the ability to plan, execute and report on a significant, individual project under the guidance of a supervisor. In particular, the project objectives include: the planning and management of their own work over an extended period of time, ● ● ● To undertake practical, theoretical, simulation and/or design work in order to achieve a specified objective. To work on problems for which there may be no unique solution. To plan and manage a project in order to achieve the required objectives. To present your project process and outcomes in a professional manner. To individually and independently learn and gain knowledge and experience in a specified subject area. 1.3. About this document This Handbook document represents your FYP guide for the 2022-2023 Academic Year. It contains information concerning the running and assessment of the project { ² } 2 FINAL YEAR PROJECT which will help you to successfully complete your project. Please read this document carefully, and consult its contents as often as required throughout the duration of the project. ( ³ ) 2. General Structure The FYP is carried out in two parts, as part of two different modules: Part 1 (Trimester 1), worth 10 credits, which represents 50% the Industrial Management and Project Preparation module. Part 2 (Trimester 2), worth 20 credits, which is a standalone module. ● ● FINAL YEAR PROJECT Marks you receive for Part 1 represent 50% of the final mark for the Industrial Management and Project Preparation module. Marks you receive for Part 2 represent 100% of the Level 3.2 Project module. There is no final, aggregate mark for the FYP but you will work on the same project topic throughout Trimesters 1 and 2. Trimester 1 Industrial Management and Project Preparation module Industrial Management FYP Part 1 (50%) component (50%) Module mark: 50% Industrial Management 50% FYP Part 1 (10 credits + 10 credits) {4} Trimester 2 Level 3.2 Project module FYP Part 2 (100%) Module mark: 100% FYP Part 2 (20 credits) FINAL YEAR PROJECT 3. Assessment and Deadlines 3.1. Part 1 submission and deadline For Part 1 of the project, you will need to prepare and submit an electronic copy of a report. The structure and content of the Part 1 report are detailed in Section 8 of the Handbook. The submission of the electronic copy of the report (in PDF or Word formats only) will be made on Blackboard, via a portal on the Industrial Management and Project Preparation module page. 3.2. Part 2 submission and deadline For Part 2 of the project, you will need to prepare and submit an electronic copy of a report, as well as prepare and deliver a 15-minute presentation. The structure and content of the Part 2 report are detailed in Section 9 of the Handbook, while guidance on how to prepare the presentation is provided in Section 12 of the Handbook. The submission of the electronic copy of the report (in PDF or Word formats only) will be made on Blackboard, via a portal on the Level 3.2 Project module page. 3.3. Breakdown of assessment marks Your Part 1 and 2 reports, as well as the Part 2 presentation will be assessed not only by your supervisor, but also by an independent moderator. The moderator is an academic who is not familiar with your project and who will be able to provide a second, objective evaluation of your academic performance. The following table summarises the breakdown of assessment marks. Note that the marks awarded by your supervisor and the independent moderator carry equal weight. The Part 1 mark is 100% determined based on the report. The Part 2 mark is determined 90% based on the report mark and 10% based on the presentation mark. The detailed marking schemes your supervisor and moderator will use to assess your work are detailed in Appendices F, G and H of the Handbook. {5} ● ● ● ● Part ● Part 1 Part 2 Credits 10 credits 20 credits FINAL YEAR PROJECT Assessment Type and Weighting Report 100% Report 90% Presentation 10% Marks Given By Supervisor 50% Moderator 50% Supervisor 50% Moderator 50% 3.4. Late submissions, non-submissions, and RAPS The FYP submissions are subject to the university's standard penalties for late submission: Joint mark by supervisor and moderator Overall 50% of Industrial Management module mark 100% of Level 3.2 Project module mark The late submission period is 7 consecutive days following the original deadline. If the work is submitted within this 7-day late submission period, and the work is at least of pass standard, then the mark is capped at 40%. If the work is below pass standard, then no late submission penalties apply. If you have an accepted PMC for late submission, then the late submission penalty is not applied. You must ensure you submit before the 7 days have passed, or your work will be recorded as a non-submission (see next point). If the work is submitted more than 7 days late, then it will be recorded as a non- submission and no marks will be awarded. If you know you will submit more than 7 days late (due to various reasons), you will need to get an accepted PMC for non-submission. Applying for a non- submission PMC must be carefully considered however, because you will only be allowed to submit again during the resit period (see point 3.6 below). This means that you will graduate late. For Part 2 of the project, in which you submit both a report and deliver a presentation, the above points apply to each component independently (e.g., you can submit your report on time, but fail to attend the presentation, and the presentation will be recorded as a non-submission). If you have a Reasonable Adjustment Plan (RAP) or Carer Plan (CP) which grants you an extra calendar week, this applies the FYP as well. All your submission deadlines will be one week later compared to what is officially published. Since with a RAP or CP your deadline is extended by one calendar week, the late submission period is 7 consecutive days following the extended deadline. VERY IMPORTANT NOTE: as part of your project, you will be expected to think on how to deal with unexpected problems (e.g., equipment failure, software problems, etc.) and have some mitigation strategies in place (see Section 6.2 of {6}See Answer
Q7:2. Using the website, airfoiltools.com, draw NACA 4420. Show your drawing process.See Answer
Q8:Question 11. An aircraft with a stall speed of V m s¹ in straight, steady and level flight performs a horizontal turn of radius R m. What is the slowest speed at which the turn can be performed if the turn is limited by stall? The answer should have units of m s.¹. [4 Marks]See Answer
Q9:Question 8. A jet engine aircraft is required to cruise for 3000 km at a constant altitude of 8 km. At the end of cruise the aircraft will weigh W KN. The wing area of the aircraft is 80 m², Co for the flight is 0.04, CL is 0.3 and the aircraft's thrust specific fuel consumption is 105 kg N-¹ s¹. How much fuel will be used in the cruise? The answer should have units of KN. [4 Marks]See Answer
Q10:Question 7. A propeller-driven aircraft has a maximum endurance of E hours when flying according to cruise climb conditions. What is the range of the flight if the aircraft's speed is V m s¹¹, the propeller efficiency is 0.85 and the specific fuel consumption is 10-7 kg W-¹ s-¹? The answer should have units of km. [2 marks]See Answer
Q11:Question 2 = Take quiz Question 5: An aircraft climbs at an angle of 15°. The weight of the aircraft is 115 kN and its wing area is 78 m². The aircraft's drag equation is given by CD 0.035 0.025 C². If the engines of the aircraft produce 47 kN of thrust during the climb what is the fastest equivalent airspeed the aircraft could be climbing at? The answer should have units of m s´¹. Question 3 4 pts Exit 2 pts Question 6: The thrust required for a cargo aircraft to fly straight, leveld steady we ured. In eachSee Answer
Q12:D Question 1 Take quiz not see the correct answer until the deadline. The questions states, when necessary, the units the answers should be expressed in. The answer you should enter is only the value, a number. You should not include the units in your answer. D Question 2 Question 4: A glider weighs 49 kN and has a drag equation of Cp = 0.023 +0.024 C². What is the minimum glide angle of the glider? Your answer should be in degrees. 2 pts Exit 4 pts Question 5: An aircraft climbs at an angle of 15°. The weight of the aircraft is 115 kN and its wing area is 78 m² he airer The aircraft's drag equation isSee Answer
Q13:D Question 3 Take quiz Exit 2 pts Question 6: The thrust required for a cargo aircraft to fly straight, level and steady was measured. In each measurement the speed and altitude of the aircraft was the same but the weight changed. When the weight was 130 kN, empty weight with no cargo and little fuel, the thrust required was T = 18.3 kN. When the weight was 30 kN above the empty weight the thrust required increased by dT = 0.41 kN (Total thrust in this case is T+dT kN). What (total) thrust would be required to fly at the same speed and altitude if the weight was 50 kN above the empty weight? The answer should have units of kN. No new data to save. Last checked at 20:19 Submit quizSee Answer
Q14:Question 6: The thrust required for a cargo aircraft to fly straight, level and steady was measured. In each measurement the speed and altitude of the aircraft was the same but the weight changed. When the weight was 130 kN, empty weight with no cargo and little fuel, the thrust required was T = 18.3 kN. When the weight was 30 kN above the empty weight the thrust required increased by dT = 0.43 kN (Total thrust in this case is T+ dT kN). What (total) thrust would be required to fly at the same speed and altitude if the weight was 50 kN above the empty weight? The answer should have units of kN.See Answer
Q15:Question 5: An aircraft climbs at an angle of 15°. The weight of the aircraft is 114 kN and its wing area is 68 m². The aircraft's drag equation is given by CD 0.035 +0.025 C. If the engines of the aircraft produce 55 kN of thrust during the climb what is the fastest equivalent airspeed the aircraft could be climbing at? The answer should have units of m s 1. =See Answer
Q16:Question 4: A glider weighs 52 kN and has a drag equation of CD = 0.023 +0.021 C. What is the minimum glide angle of the glider? Your answer should be in degrees.See Answer
Q17:Question 3: A 1/12th scale model of an aircraft was tested in a wind tunnel under sea level standard conditions. The following data was obtained. Air Speed (m s ¹) 10 15 20 Angle of attack (degrees) 0 2 4 Lift (N) 9.9225 37.20938 92.61 Drag (N) 0.8153723 2.156077 4.690329 Pitching moment (Nm) -2.20813 -5.86508 -12.0209 The wing area of the full sized aircraft is 97.9 m² and the wing aspect ratio is 6.5. What value does the coefficient of moment about the aerodynamic centre have?See Answer
Q18:Question 2 4 pts Question 2: An aircraft weighs 91 kN and it has a maximum coefficient of lift of 1.51. Its drag equation is given by: CD = 0.03 +0.042 C How much drag will the aircraft create is it flies at stall speed with lift equal to weight? The answer should have units of kN.See Answer
Q19:Question 1 2 pts Question 1: In a wind tunnel test of flow over a wing section, air enters the test section at a speed of 54 m s1 and a pressure of 942 kPa. Assuming Bernoulli's principle applies to the flow, what is the pressure at the stagnation point on the wing surface if the air density is 1.16 kg m 3? The answer should have units of kPa.See Answer
Q20:5. Format of the report The report has a strict 4-page limit. Anything above four pages will be penalised according to the marking guidance. The report should contain a front sheet (which will not count towards the page limit), containing the following information only: Name Student ID Module Code Module Title • Coursework Name The report should be written as a formal lab report with appropriate headings. Do not include a table of contents or appendix. Do not repeat large sections from this handout in relation to the background or the procedures. As a rough guide, approximately three pages should cover the raw and processed data, with one page to cover a discussion of the flow physics. Note that the raw data should be presented to you in the units it was. Appropriate references are essential to show that you have engaged with and understood the data and the theory. The required format is single-spaced Times New Roman font, size 12 pt. The page margins should be set to normal, i.e. 2.54 cm at Top/Bottom/Left/Right.See Answer

TutorBin Testimonials

I found TutorBin Aerodynamics homework help when I was struggling with complex concepts. Experts provided step-wise explanations and examples to help me understand concepts clearly.

Rick Jordon

TutorBin experts resolve your doubts without making you wait for long. Their experts are responsive & available 24/7 whenever you need Aerodynamics subject guidance.

Andrea Jacobs

I trust TutorBin for assisting me in completing Aerodynamics assignments with quality and 100% accuracy. Experts are polite, listen to my problems, and have extensive experience in their domain.

Lilian King

I got my Aerodynamics homework done on time. My assignment is proofread and edited by professionals. Got zero plagiarism as experts developed my assignment from scratch. Feel relieved and super excited.

Joey Dip

Popular Subjects for aerodynamics

You can get the best rated step-by-step problem explanations from 65000+ expert tutors by ordering TutorBin aerodynamics homework help.

TutorBin helping students around the globe

TutorBin believes that distance should never be a barrier to learning. Over 500000+ orders and 100000+ happy customers explain TutorBin has become the name that keeps learning fun in the UK, USA, Canada, Australia, Singapore, and UAE.