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1 Describe transonic flight. At what speeds does it occur? What
control problems, if any, does it present? Why do these problems
exist and what has been done to try and remedy the problems? (20
Points)
A. Describe transonic flight. Transonic flight will be flight in the region of
speed
B. Mach 1. It is for the most part concurred that transonic velocities are 20 to 30 percent
both above and underneath Mach 1 or sonic speed. C. At what speeds does this occur? Transonic flight happens between Mach 0.8 and 1.2. This is around 600 to 768 miles for each hour adrift
level C What control problems, if any, does it present?
Wave drag is an issue. The wind stream over the wing is at different focuses
at the same time beneath, at, or more the speed of sound (Mach 1). The nearer the plane gets to Mach 1 the further back toward the trailing edge of
the wing the stun wave is pushed past the stun wave the cover stream of air
up the wing is lost, this can bring about control vibrations and even prompt
loss of air ship control. D Why do these problems exist and what has been done to try and
remedy the problems?
These issues exist since it is generally the wings of the air ship that first
approach Mach 1 while whatever remains of the air ship is still at subsonic
paces. A cleared wing configuration has been utilized to diminish the
antagonistic impacts of flight in the transonic district. Vortex generators can
likewise be utilized to beat the unfriendly weight of the stun waves by
separating the stun wave and counteracting wind current division.
Supercritical airfoil plans can likewise be utilized, they commonly planned
with the thickest bit of the wing nearer to the trailing edge and furthermore
with a negligible measure of upper wing ebb and flow to help keep stun
waves from framing exceptionally far forward on the upper surface of the
wing
2 Describe supersonic flight. At what speeds does it occur? What
control problems, if any, does it present? Why do these problems exist and what has been done to try and remedy the
problems?
A. Describe supersonic flight.
Flight above Mach 1. By and large acknowledged as flight above Mach 1.2 to
5.0. Flight quicker than the speed of sound. B. At what speeds does it occur?
Mach 1.2 to 5.0
C. What control problems, if any, does it present? A shock wave can frame at the intersection of control surfaces that have
settled and moveable parts. The lift stabilizer is a case of such a control
surface. The stun wave keeps the lift from having any impact on the
stabilizer in front of it significantly diminishing pitch control.
D Why do these problems exist and what has been done to try and
remedy the problems?
Much like the wing the lift additionally gives lift. The stun wave that
structures keeps the lift from impacting the stabilizer, which extraordinarily
lessens pitch control. The arrangement here is an all moveable control
surface that wipes out the intersection and the stun wave those outcomes
from the intersection. 3 What does the Critical Mach number of an aircraft represent?
Specifically, what happens aerodynamically when an aircraft
reaches this speed?
The Critical Mach number is the point at which the forward speed of the
plane or free airstream stream causes the air streaming over the wing to
achieve Mach 1. For instance if a plane is flying Mach .75 and the wind
stream over the thickest piece of the wing or the speediest air over the wing
is just Mach .87 then the plane is all subsonic. On the off chance that the
speed were expanded to Mach .78 and the speediest air over the wing
achieves Mach 1 then the Critical Mach number for the plane is Mach .78. 4 What is the phenomenon known as area rule, and why is it
important to supersonic flight?
Zone run is an outline method used to lessen delay transonic and supersonic
planes. Basically the drag, and particularly the wave drag, made by the extra
surface region at the wing foundation of a plane is fundamentally expanded
on a round and hollow fuselage. Richard Whitcomb found that on the off
chance that you decrease or make the fuselage smaller at the wing root then
you diminish the option surface are picked up while adding a wing to a flying
machine. This narrowing of the fuselage essentially invalidates the expansion
drag brought about by the expansion of the wing to the airplane. There is a
perfect shape to length and distance across proportion for air ship. This fuselage shape is known as the Sears-Haack body. This diminishment in extra
drag helps by constraining the measure of push required. 5 Identify two design features that aid aircraft in reaching
supersonic speeds. What aerodynamic problems do these
features address?
The cleared wing outline and the rapid airfoil help air ship achieve supersonic paces. The Swept wing
configuration diminishes wave drag and gives the whole wing a chance to achieve supersonic rates. The
fast airfoil is a wing outlined with a sharp or restricted blade like driving edge that permits the bow wave
to hold fast to the wing putting the whole wing in supersonic flight. This lessens drag also.

 

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