Answer: Foundries
Explanation: Casting is the method of making the liquid material to be shaped into solid form by being poured in a mold and having a hollow cavity . The liquid then turns into a solid state and this is known as casting. the casting odd metal is usually carried out in different shapes by the help of furnaces ,gases, molds etc.This process is usually performed in the certain industries known as foundry.
Answer:
- |z*| = r , ∠(z*) = -∅
- |z²| = r² , ∠(z²) = 2∅
- |jz| = r , ∠(jz) = ∅
- |zz*| = r² , ∠(zz*) = 0
- |z/z*| = 1 , ∠(z/z*) = 2∅
- |1/z| = r ⁻¹ , ∠(1/z) = -∅
Explanation:
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1.) The * mean you take the conjugate of the value. This means you change the sign of the imaginary part, so if it's positive, turn it negative and vice versa.
2.) The magnitude with an exponent can have the exponent moved outside the magnitude. |zⁿ| = |z|ⁿ
The angle multiplies with its exponent instead. ∠zⁿ = n∠z
3.) This part is just testing if you can convert the number using the eulers formula and convert back.
The magnitude could be found using the distance formula. √(R² + I²)
The angle could be found using tan⁻¹(Imaginary/Real).
4.) Magnitude of a product could be split up. |zv| = |z|·|v|
Angle of a product could be splitted up and added. ∠(zv) = ∠z + ∠v
5.) Simplify it first using some algebra and use the euler's identity to identify the magnitude and angle. It takes in a form like this:
A is your magnitude, ∅ is your angle.
6.) Same rule as part 2
Ehheem✔️
Explanation:
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Answer:
c from transmitter to a receiver
Answer:
The thrust of the engine calculated using the cold air is 34227.35 N
Explanation:
For the turbofan engine, firstly the overall mass flow rate is considered. The mass flow rate is given as
Here
- ρ is the density which is given as
- P is the pressure of air at 5500 m from the ISA whose value is 50506.80 Pa
- R is the gas constant whose value is 286.9 J/kg.K
- T is the temperature of the inlet which is given as 253 K
- A is the cross-sectional area of the inlet which is given by using the diameter of 2.0 m
- V_a is the velocity of the aircraft which is given as 250 m/s
So the equation becomes
Now in order to find the flow from the fan, the Bypass ratio is used.
Here BPR is given as 8 so the equation becomes
Now the exit velocity is calculated using the total energy balance which is given as below:
Here
- h_4 and h_5 are the enthalpies at point 4 and 5 which could be rewritten as and respectively.
- The value of T_4 is the inlet temperature which is 253 K
- The value of T_5 is the outlet temperature which is 233K
- The value of c_p is constant which is 1005 J/kgK
- V_a is the inlet velocity which is 250 m/s
- V_e is the outlet velocity that is to be calculated.
So the equation becomes
Rearranging the equation gives
Now using the cold air approach, the thrust is given as follows
So the thrust of the engine calculated using the cold air is 34227.35 N