Question

In: Physics

Consider a NACA 2412 airfoil with a 64 cm chord in an airstream with a velocity...

Consider a NACA 2412 airfoil with a 64 cm chord in an airstream with a velocity of 70m/s at standard sea level conditions. If the lift per unit span is 1254 N/m, obtain the following quantities:

b) Lift coefficient

c) Angle of Attack

d) Drag per unit span

e) moment per unit span about the aerodynamic center

Solutions

Expert Solution

genius_generous answered 1 year ago
Next > < Previous

Related Solutions

A rectangular wing with a NACA 65-210 airfoil section and a chord of 6 in is...
A rectangular wing with a NACA 65-210 airfoil section and a chord of 6 in is mounted in the Auburn University 2 ft × 2 ft wind tunnel, completely spanning the test-section. The tunnel is operating with test section velocity, pressure, temperature, and velocity of 1 atm, 520°R, and 75 ft/s, respectively. (a) Calculate the lift, drag, and moment about the quarter-chord when the angle of attack is 5°. (b) What angle of attack would be required to generate a...
Consider a double wedge airfoil with a maximum thickness of 5% chord at angle of attack...
Consider a double wedge airfoil with a maximum thickness of 5% chord at angle of attack = 0 degrees. a. Determine the approximate chord wise location (x/c) of the maximum thickness that producesthe minimum drag coefficient (cd) at Mach numbers of 2, 4 and 6. [Hint: you do not need to investigate locations ahead of 0.4c]. Include a composite plot of drag coefficient vs location of (t/c) max for each Mach number in your report. b. Repeat this analysis for...
Consider the low-speed airflow over the NACA 0012 airfoil at low angles of attack. The Reynolds...
Consider the low-speed airflow over the NACA 0012 airfoil at low angles of attack. The Reynolds number based on the chord is roughly Rec = 2.88 × 10^6. This flow can reasonably be modeled as incompressible and inviscid. The initial input value for your simulations is provided on the bottom of this assignment. Your need to generate a report to give background introduction, and address the following issues: (inlet Velocity: 1.5 Attack angle: 5) 1. Incompressible, Inviscid Model: Explain why...
There is an airfoil with a 3ft chord length for a small remote controlled aircraft. The...
There is an airfoil with a 3ft chord length for a small remote controlled aircraft. The lift coefficient is C = 0.59 and the pitching moment coefficient at a quarter chord length is Cm,c/4 = -0.032 for a landing spped of 45 ft/s at sea-level std conditions a) Calculate the lift per unit span (in lbf/ft) b) Calculate the moment about the quarter chord position per unit span c) Calculate the moment about the leading edge per unit span d)...
piper cherokee wing area is 16m², span is 9.75m. total weight is 1100kg. airfoil is NACA...
piper cherokee wing area is 16m², span is 9.75m. total weight is 1100kg. airfoil is NACA 65-415 and lift coefficient slope is 0.1033 per degree. αL=0 is -1.5degree. Assume τ = 0.12. when air density is 1.23Kg/m³ and speed is 193Km/h. Determine the wing's angle of attack
Develop MATLAB codes for Blade Element Momentum Theory for horizontal axis tidal turbine for airfoil NACA...
Develop MATLAB codes for Blade Element Momentum Theory for horizontal axis tidal turbine for airfoil NACA 0015, analyzing the performance of the turbine; power.
A new two-dimensional airfoil constant chord model is being tested in a wind tunnel. The model...
A new two-dimensional airfoil constant chord model is being tested in a wind tunnel. The model chord is 3ft. The atmosphere is standard. The velocity of the airflow is 250 ft/s. The forces are resolved as 150lb of perpendicular to the relative wind and 10lb parallel to the relative wind. Find the dynamic pressure and the section coefficient of lift (cl) and the section coefficient of drag (cd).
Two concentric circles are of radii 5 cm and 3 cm. Determine the length of the chord of the larger circle which touches the smaller circle.
Two concentric circles are of radii 5 cm and 3 cm. Determine the length of the chord of the larger circle which touches the smaller circle.
Consider an airfoil in a high-­?speed wind tunnel. At the minimum-­?pressure point on the wing, the...
Consider an airfoil in a high-­?speed wind tunnel. At the minimum-­?pressure point on the wing, the velocity is 900 ft/s. If the test section flow velocity is 750 ft/s at standard sea-­? level conditions: a) Calculate the pressure coefficient at this point on the wing. b) Calculate the critical pressure coefficient corresponding to this flight condition. c) Comparing your answers from parts (a) and (b), what conclusion can you make as to the nature of the flow over the wing?...
Consider an airfoil in a high-­?speed wind tunnel. At the minimum-­?pressure point on the wing, the...
Consider an airfoil in a high-­?speed wind tunnel. At the minimum-­?pressure point on the wing, the velocity is 900 ft/s. If the test section flow velocity is 750 ft/s at standard sea-­? level conditions: a) Calculate the pressure coefficient at this point on the wing. b) Calculate the critical pressure coefficient corresponding to this flight condition. c) Comparing your answers from parts (a) and (b), what conclusion can you make as to the nature of the flow over the wing?...
ADVERTISEMENT
Subjects
ADVERTISEMENT
Latest Questions
ADVERTISEMENT