#1. Consider a Boeing 747-700 in straight-and-level cruise flight on a standard day. The aircraft has a wing area of 525 m and is flying geometric altitude of hc = 10,000 m. At a certain time during the flight, its mass is 3.5 x 105 kg and each of the four engines produces 50 kN of thrust. C was calculated as 0.4. a) Determine the cruise airspeed. b) Determine the total drag coefficient.

#1. Consider a Boeing 747-700 in straight-and-level cruise flight on a standard day. The aircraft has a wing area of 525 m and is flying geometric altitude of hc = 10,000 m. At a certain time during the flight, its mass is 3.5 x 105 kg and each of the four engines produces 50 kN of thrust. C was calculated as 0.4. a) Determine the cruise airspeed. b) Determine the total drag coefficient.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Related questions

Q: A student wants to estimate drag force on a golf ball of diameter D moving in air at a speed of U at…

A: GivenFor golf balldiameter D speed Urepilcadiameter d=D5speed u=5U

Q: What average net thrust must a17-ton airplane have to reach an altitude of 5,000 ft and a speed of…

Q: for a wind farm is observed to have steady winds at a speed of 5.5 m/s. Determine the wind energy:…

Q: Cd=1.4 (coefficient of drag) ¥=10 ft/sec (velocity) Ƴ=62.4 #/ft3 g=32.3 ft/sec2 a. What is the…

A: givencoefficient of drag CD=1.4velocity of water V=10ft/sdensity of water γ=62.4 lb/ft3g=32.3…

Q: e lift slope for a straight wing is

A: Given: Aspect ratio= 5 Lift slope for airfoil section = 0.1/degree To find Lift slope for straight…

Q: Suppose at certain speed, your car has the air drag force of 290 N and the rolling resistance of 370…

Q: A surface buoy is located in 180 ft of water and is moored with a wire rope weighing 3 lb/ft. The…

Q: Question 2 A lightweight parachute of diameter, D is designed for military use as shown in the…

A: A dimensional relationship is needed to be established between aerodynamic drag with properties of…

Q: 400 200 100 Determine the form drag experiences by a truck traveling at a speed of 80 miles/hr with…

A: Reynold number is calculated. Which gives Cd from graph Drag force is subsequently calculated.…

Q: A 70 kg bicyclist is riding her 15 kg bicycle downhill on a road with a slope of 8° without pedaling…

Q: A wing has an elliptical load distribution across its wingspan that totals a lift of 2,500.0 N.…

A: Given DataCL=0.8Total Lift (L)=2500NA.R=11

Q: Strictly don't use Artificial intelligence tools. The answer must be correct at any cost

A: Level Turn Analysis for Lift Coefficient CalculationWe can solve this problem using the principles…

Q: A flight enthusiast is designing a man-powered single wing aircraft. According to her calculations,…

A: Part (a) Write the given value using suitable variables. Here CL signifies lift coefficient, CD…

Q: 1. Suppose you are flying a 7,784 kilograms aircraft at 14,630 meters where the air density is…

Q: Consideld mite wIng with dll aspect Iadtio dil elliptiIcal mt distibution1. me mt Slope foI Lhe…

Q: A blimp is designed to move in air at "C at 7 m/s. If a 1:20 scale model is tested in water at 20…

Q: The Air Force's new experimental jet, the X - 9001, is a perfectly flat, rectangular wing. It has a…

Q: A ship weighing 7200 tons has a KG of 5.20 m, a KB of 3.12 m and a KM of 5.35 m. In the voyage, has…

Q: If a pilot encounters wind shear on approach and fails to adjust for sudden increasing head wind or…

Question

#1. Consider a Boeing 747-700 in straight-and-level cruise flight on a standard day. The aircraft
has a wing area of 525 m and is flying geometric altitude of he = 10,000 m. At a certain time
during the flight, its mass is 3.5 x 105 kg and each of the four engines produces 50 kN of
thrust. C was calculated as 0.4.
a) Determine the cruise airspeed.
b) Determine the total drag coefficient.

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1: Given

VIEW

Step 2: Calculation of air speed and drag coefficient

VIEW

Solution

VIEW

Trending now

This is a popular solution!

Step by step

Solved in 3 steps with 11 images

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

please give me detail, i need to understand i still blur
Ign, McGraw-Hill, this chapter) and by New York, 1999, for more information. EXAMPLE 6.18 Estimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal = 0. The spoilers increase the zero-lift, used; however, spoilers are employed such that L drag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the wejehr of any fuel carried by the airplane. The maximum lift coefficient, with flaps fully em ployed at touchdown, is 2.5.
Pls help ASAP. Pls show all work annd circle the final answer.
A model of an aircraft is being tested in a wind-tunnel. If the model was replaced by one that is half the size but is otherwise identical, what would be the ratio of the drag on the large model to the drag on the small model for exactly the same flow conditions. Give your answer to two decimal places. The model is in a region where drag coefficent is independent of Reynolds number.
Semester on QUESTIONS QI) A small airplane has a total mass of 2000 kg and a wing area of 56 m². Speed of it is 290 km/h. Determine the lift and drag coefficient. (The density of standard air at an altitude of 5000 m is p0.802 kg/m³)
Using the information given in Table 10.4, determine the ratio of local pressure and density to sea-level values. Estimate the value of air density at the cruising altitude of most commercial airliners.
B2 is flying at an altitude of 43,000 ft and a speed of 400 KTAS under standard atmospheric conditions. If the average aerodynamic chord is 39,6 ft, calculate the Reynolds number and the average % aerodynamic chord present on the wing
A professional baseball pitcher can project a baseball atca speed as high as 35 m/s. 1.If air resistance can be ignored, how high in metres would a baseball launched at this speed rise if projected straight up? 2.How long would the baseball be in the air (in seconds)
(c) In a wind tunnel experiment, a drag force on 1:8 scale model billboard is 1 kN. The air in the wind tunnel is 20 degree Celsius. During a storm, the wind speed can reach 20 km/hr with air temperature of 10 degree Celsius. Determine the drag force experience by the billboard during storm. Refer Appendix B.
Strictly don't use chatgpt for this question.
Problem 3: Let's say you want to predict the aerodynamic drag of a new car based on the use of a model that is one- fifth scale of the actual car/prototype car. We want to predict the drag of the car when it has wind velocity 75 miles/hour with an air temperature of 40°C. The model is placed in a wind tunnel at 10°C. Determine the wind tunnel velocity necessary to achieve similarity between the model and the prototype.
Problem 2 A Beechcraft Bonanza wing has the following dimensions: - chord = 1.4 m; - span (wing tip to wing tip) = 7m and - wing is roughly rectangular in shape. This plane is flying at 30 m/sec under standard sea level conditions. Model this wing as a flat plate for boundary layer analysis. a) Calculate the Reynolds number for the wing. b) Calculate the boundary layer thickness at the trailing edge of the wing assuming fully laminar flow. c) Calculate the boundary layer thickness at the trailing edge of the wing assuming fully turbulent flow. d) Calculate the skin friction drag on the full wing assuming laminar flow transitions to turbulent flow at a critical Reynolds number = 5.8 x 105.