A jet plane weighing 29.4 kN and having a wing area of 20 m flies at a velocity of 950 km/h. When the engine delivers 7350 kW,65 percent of the power is used to overcome the drag resistance of the wing. Calculate the co-efficient of lift and drag for the wing. Take density of atmospheric air 1.208 kg/m³'. [Ans. 0.0349; 0.0215]

A jet plane weighing 29.4 kN and having a wing area of 20 m flies at a velocity of 950 km/h. When the engine delivers 7350 kW,65 percent of the power is used to overcome the drag resistance of the wing. Calculate the co-efficient of lift and drag for the wing. Take density of atmospheric air 1.208 kg/m³'. [Ans. 0.0349; 0.0215]

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 parachute of hemi-spherical shape allows a parachute jumper of weight 90kg to descend with a…

A: A drag force is the resistance created when a body moves through a fluid like water or air. A drag…

Q: Janie likes to drive with a tennis ball on her car antenna. The ball diameter is D = 2.62 in and its…

A: We need to first determine the velocity of the car and the frontal area of the ball. It will help to…

Q: An airfoil generates a 1200 N/m sectional lift when traveling at 75 m/s at sea level. What is the…

A: The circulation (Γ) around an airfoil is defined as the line integral of the velocity along a closed…

Q: If the Pump-1A flow rate is increased due to an increase in the process what modification is…

A: If the Pimp-1A flow rate is increased due to an increase in the process what modification is…

Q: Consider the equation gm v (t) (1 – e-C/m}t) For the free-falling bungee jumper with linear drag,…

Q: Consider again a semi truck traveling at 55 mph on the freeway. The ambient air is at 1 atm and…

Q: Calculate the minimum flight speed of an aircraft at constant altitude. Consider and aircraft with…

Q: Calculate the ratio of the drag force on a jet flying at 833 km/h at an altitude of 7.7 km to the…

Q: Velomobile Characteristics Mass: 29 kg in addition to the rider Aerodynamic drag: F = 0.0492 V…

A: Since we only answer upto 3 subparts, we will answer the first 3. Please resubmit the questionand…

Q: The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and…

A: Given Length = 9.144 m Width = 0.9144 m Drag coefficient = 0.01 Lift coefficient = 0.3 Altitude =…

Q: **75. ssm A uniform rectangular plate is hanging vertically downward from a hinge that passes along…

A: Consider the diagram shown below for the horizontal position of plate. Here, FP is the pressure…

Q: Required information The helium-filled balloon in the image is tethered at 20°C and 1 atm with a…

A: Given Temperature T= 20 0c String is negligible mass and drag diameter of the balloon d =58 cm =0.58…

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: Write down the Bernoulli equation and explain how the lift force is generated by an airfoil using…

A: The Bernoulli Equation is given by:P + ρgh + (1⁄2ρV2) = constant along a streamline (1)Where:P =…

Q: An aircraft has a total mass of (1.320x10^2) kg and a wing area of (2.90x10^1) m². It operated with…

Q: Consider two free-falling parachutists with linear drag. The first jumper is 70 kg and has a drag…

A: Given data:

Q: Consider again a semi truck traveling at 55 mph on the freeway. The ambient air is at 1 atm and 80F.…

A: Write the formula for Reynolds number. Re=VLν Here, Re is the Reynolds number, V is the velocity of…

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

Q: (a) Calculate the frontal area of a parachute of hemi-spherical shape which will allow a parachute…

Q: 2. The table below shows experimental data for the shape and pressure distribution on the upper and…

A: The central difference for the numerical derivatives are dYudx=Yui+1…

Q: The car shown in the figure below moves at a constant speed on a highway and has a drag coefficient…

Q: The drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 +…

A: The drag equation, CD = 0.358 + 0.0405CL2The weight, W = 18681 NThe wings area, A = 14.41 m2

Q: Task 3: An airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The…

A: Given data:- Span length of air foil S = 36 m Aspect ratio = 10 Speed, u = 150 m/s Altitude, h =…

Q: To maintain a constant speed, the force provided by a car's engine must equal the drag force plus…

Q: A 2 m diameter cylinder rotates at 1800 rpm in an air stream (p=1226 kg/m³) of 25 m/sec. Estimate…

A: Air density cannot be 1226 kg/m3 which is greater than density of water = 1000 kg/m3 . Hence,…

Question

Ajet plane weighing 29.4 kN and having a wing
area of 20 m² flies at a velocity of 950 km/h.
When the engine delivers 7350 kW,65 percent of
the power is used to overcome the drag resistance
of the wing. Calculate the co-efficient of lift and
drag for the wing. Take density of atmospheric
air 1.208 kg/m³.
[Ans. 0.0349; 0.0215]

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

VIEW

Step 2

VIEW

Trending now

This is a popular solution!

Step by step

Solved in 2 steps

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

An airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2. 2.0 0.024 1.6 0.020 1.2 0.016 0.8 S 0.012 0.4 0.008 0.004 -0.4 -0.8 -0.4 0.4 0.8 1.2 -8 8 16 24 CL a (degrees) 0.2 -0.2 1.0 xlc Figure 3: NACA 23012 airfoil characteristics of task 3.
Calculate the frontal area of a parachute of hemi-spherical shape which will allow aparachutejumper of weight 90 kg to descend with a steady velocity of 8 m/s ignoring air movement.The drag coefficient of parachute as determined from experiments is 1.5. Take the densityof air as 1.2 kg/m3
Answer correctly. Here is the Translation. "A luxury sports car has an area of 2 m² and there is a drag coefficient of 0.29 at a speed of 90 km/h. Calculate the drag force exerted on the car at this speed"
Assuming air resistance with drag ratio =0.50 find the terminal velocity for an object, initially suspended at the height Yo = 750 m above the Earth and dropped with v(0) = 0 m/s. Use gravitational accelerationg = 9. 8 m/s² . Round your answer to 2 decimal places. т
P
#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.
Question B3 – External Flow The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 15Okm/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings.
A C-130 pilot desires to fly a low-level navigation mission at 4 n miles/ min (240 kn ground speed).Winds are forecast out of the north (blowing south) at 20 kn, the pressure altitude is 10,000 ft, andthe temperature is 80 °F. What indicated airspeed should the pilot fly on a northbound leg if theposition error is negligible? The answer is q = 136 lb/ft2
Need help with this engineering problem.
Follow the step by step approach with the correct final answer .
What is the equation for the time of flight of a projectile? Is this equation dimensionally homogeneous?
The manufacturer of a car reduces the drag coefficient of the car from 0.38 to 0.33 as a result of some modifications in its shape and design. If, on average, the aerodynamic drag accounts for 20 percent of the fuel consumption, the percent reduction in the fuel consumption of the car due to reducing the drag coefficient is (a) 15% (b) 13% (c) 6.6% (d ) 2.6% (e) 1.3%