A simple wing may be modeled as a 0.3 m wide flat plate set at an...
A simple wing may be modeled as a 0.3 m wide flat plate set at an angle of 3° to an airflow at a Mach number of 2.5, the pressure in this flow being 40 kPa. Assuming that the flow over the wing is two-dimensional, estimate the lift and drag force per meter span due to the wave formation on the wing. What other factor causes drag on the wing?
Homework Answers
Add Answer to:
A simple wing may be modeled as a 0.3 m wide flat plate set at
an...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
With Details please!!, I saw a solution for this question, i did not get it. 6.A two-dimensional, flat plate is incline...
With Details please!!, I saw a solution for this question, i did
not get it.
6.A two-dimensional, flat plate is inclined at a positive angle of attack in a supersonic air stream of Mach 2.0 (Figure P7.6). Below the plate, an oblique shock wave starts at the leading edge, making an angle of 42° with the stream direction. On the upper side, an expansion occurs at the leading edge. (a) Find the angle of attack of the plate. (b) What...
4.11 The flying wing, B-2 stealth bomber can be approximated by a flat plate with dimensions...
4.11 The flying wing, B-2 stealth bomber can be approximated by a flat plate with dimensions of 69 f (chord) x 172 f (span). It’s cruising at 25,000 f. Assume the flow over both sides of the bomber is completely turbulent. The absolute viscosity coefficient is 5.2(10)-7 sl/f/s. Determine the total skin friction drag at Mach numbers 1.0, 2.0 and 3.0 for this airplane.
and drag of the wing if the airplane is cruising at 130 knots at 5,500 feet under standard conditions. 5.15 A flat plate is oriented at an angle of attack of 90° to the flow in a low-speed wind t...
and drag of the wing if the airplane is cruising at 130 knots at 5,500 feet under standard conditions. 5.15 A flat plate is oriented at an angle of attack of 90° to the flow in a low-speed wind tunnel. Assume the pressure over the front of the plate is constant and equal to the stagnation pressure. Assume the pressure on the reward facing side is also constant but equal to the free stream static pressure. Since the flat plate...
Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear supersonic theor...
Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data: • Total Wing Area: 18.22 m2 • Aircraft Mass: 8,000 kg -Is supersonic linear theory valid for this flight regime? Explain your answer.
Water at 10 degrees Celsius and a velocity of 2.5 m/s is flowing along a 4.5 m long flat plate at a uniform temperature of 40 degrees Celsius. If the plate is 1.5 m wide, determine: a) the distance fr...
Water at 10 degrees Celsius and a velocity of 2.5 m/s is flowing along a 4.5 m long flat plate at a uniform temperature of 40 degrees Celsius. If the plate is 1.5 m wide, determine: a) the distance from the leading edge of the plate where the flow becomes turbulent, b) the heat transfer rate between the plate and the flowing water, c) the fraction of the force exerted by the water on the first half of the plate...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...
summatize the following info and break them into differeng key points. write them in yojr own...
summatize the following info and break them into differeng key points. write them in yojr own words
apartus
6.1 Introduction—The design of a successful hot box appa- ratus is influenced by many factors. Before beginning the design of an apparatus meeting this standard, the designer shall review the discussion on the limitations and accuracy, Section 13, discussions of the energy flows in a hot box, Annex A2, the metering box wall loss flow, Annex A3, and flanking loss, Annex...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
With Details please!!, I saw a solution for this question, i did
not get it.
6.A two-dimensional, flat plate is inclined at a positive angle of attack in a supersonic air stream of Mach 2.0 (Figure P7.6). Below the plate, an oblique shock wave starts at the leading edge, making an angle of 42° with the stream direction. On the upper side, an expansion occurs at the leading edge. (a) Find the angle of attack of the plate. (b) What...
and drag of the wing if the airplane is cruising at 130 knots at 5,500 feet under standard conditions. 5.15 A flat plate is oriented at an angle of attack of 90° to the flow in a low-speed wind tunnel. Assume the pressure over the front of the plate is constant and equal to the stagnation pressure. Assume the pressure on the reward facing side is also constant but equal to the free stream static pressure. Since the flat plate...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...
summatize the following info and break them into differeng key points. write them in yojr own words
apartus
6.1 Introduction—The design of a successful hot box appa- ratus is influenced by many factors. Before beginning the design of an apparatus meeting this standard, the designer shall review the discussion on the limitations and accuracy, Section 13, discussions of the energy flows in a hot box, Annex A2, the metering box wall loss flow, Annex A3, and flanking loss, Annex...
Most questions answered within 3 hours.
-
Where is the error in this code sequence?
String s1 = "Hello";
String s2 = "ello";...
asked 10 months ago -
Financial data for Joel de Paris, Inc., for last year
follow:
Joel de Paris, Inc.
Balance...
asked 10 months ago -
Consider this reaction:
Al2(SO4)3 (aq)+ BaCl3
(aq) Al2Cl6 (aq)- +
3BaSO4(s) . What is the...
asked 10 months ago -
Suppose that Savneet is considering increasing her
recent random sample from 20 car rentals to 40...
asked 10 months ago -
Trucks arrive at an unloading terminal at an average rate of 120
per hour.
Trucks arrive...
asked 10 months ago -
Why are methanol and ethanol completely soluble in water while
octanol is not very little soluble....
asked 10 months ago -
A facilities manager at a university reads in a research report
that the mean amount of...
asked 10 months ago -
When the CuSO4 is rehydrated by adding water to the anhydrous
compound, is this an endothermic...
asked 10 months ago -
A ray of sunlight is passing from diamond into crown glass; the
angle of incidence is...
asked 10 months ago -
A block of mass 0.249 kg is placed on top of a light, vertical
spring of...
asked 10 months ago -
how do the kidneys compensate in the presences of acidosis
a) trigger hyperventilate
b) reserve acid...
asked 10 months ago -
Question 501 pts
The rental rate of capital to the firm increases. Which of the
following...
asked 10 months ago