Term

Definition
(1+ [(γ1)/2]M1^2)^[γ/(γ1)]
For Isentropic Flow
γ = Gamma 


Term

Definition
(1+ [(γ1)/2]M1^2)^[γ/(γ1)]
For Isentropic Flow 


Term
Density1*Area1*Velocity1 = 

Definition


Term

Definition
Isentropic flow is flow that is Adiabatic and reversible, meaning that: 1) No heat is added or taken away 2) No friction or other dissipative effects occur. 


Term
For Isentropic Flow:
P2/P1 = ? = ?? 

Definition
= (Roh2/Roh1)^γ = (T2/T1)^(γ/(γ1)) 


Term
Air can be assumed to be Incompressible if 

Definition
V < 100 M/s or V < 225 Miles/Hour or If Mach # < 0.3 


Term
Define Eulers Equation, and explain how it is used. 

Definition
dP = Roh*V*dV
It relates the change of momentum to the force, It is also referred to as the Momentum Equation 


Term
Define Bernoulli's Equation, and explain how it is used 

Definition
P1+Roh*[(V1^2)/2] = P2+Roh*[(V2^2)/2] Or P+Roh*[(V^2)/2] =Constant along Streamline
Only Holds true for Inviscid(frictionless), Incompressible flow. Must NOT be used for comressible Flow 


Term
Define the Equation of State 

Definition
P1 = Roh1*(R)*(T1)
R = Constant = 287 for SI, or 1716 for US.
T = Temperature = Kelvin or Rankine 0F = 460 Rankine 0C = 273K = 32F 


Term
Define the first law of Thermodynamics 

Definition
δQ + δw = de
The sum of the heat added + the sum of the work done on the system = the change in internal energy. 


Term
Define the terms of this equation
h1 + (V1^2)/2 = h2 + (V2^2)/2 or h + (V^2)/2 = Constant 

Definition
h = CpT where Cp [u]=[/u] (δQ/dT) Constant Volume, T = Temperature V = velocity
Also can be written as CpT1 + (V1^2)/2 = CpT2 + (V2^2)/2 


Term
Finish these Equations, and name them:
a) Roh1*A1*V1 = b) P1 + (1/2)*Roh*(V1^2) = c) CpT1 + (V1^2)/2 = d) P1 = 

Definition
a) Roh2*A2*V2 (Continuity) b) P2 + (1/2)*Roh*(V2^2) (Bernoulli) c) CpT2 + (V2^2)/2 (Energy) (Cp =[u]=[/u] (δQ/dT) Constant Volume, T = Temperature) d)Roh1*R*T1 (Equation of state, R = 287 or 1716) 


Term
The speed of sound in a perfect gas depends only on ... 

Definition
...The temperature of the gas.
a = Sqrt(γRT) = Speed of sound
γ = 1.4 for Air on earth 


Term

Definition
V/a, where V is the speed of the object (in ft/s) and a is the speed of sound (in ft/s)
a must be determined by the equation: a = Sqrt(γRT) = Speed of sound
γ = 1.4 for Air on earth if Altitude is given, use altitude table to determine T
If M<1, flow is subsonic if M=1, flow is sonic If M > 1, flow is supersonic if M >> 1, flow is hypersonic ( M > 5) If 0.8 [u]<[/u] M [u]<[/m] 1.2, flow is transonic 


Term
Convert 550 Mi/h to ft/s: 

Definition
88 ft/s = 60 mi/h ...
Therefore 550 (Mi/h)*(88/60) = 807 ft/s 


Term
For a manometer used to measure pressure differences in a wind tunnel:
P1*A = or P1P2 = 

Definition
= P2*A + ω*A*Δh or = ω*A*Δh
ω*A*Δh = [Roh(fluid)*g(gravity)]*(Area)*(difference of heights between two tubes) 


Term
When dealing with low speed subsonic flow: 

Definition
V2 = Sqrt[(2*(P1P2))/(Roh*(1(A2/A1)^2))]
since we asume Roh1 = Roh for low speed subsonic flow. 


Term
When calculating Mass flow:
M = 

Definition
Roh1*A1*V1 or Roh*A1*V1 for low speed subsonic airflow also = Roh*A2*V2.
Can be measured anywhere in the airflow M = roh*A*V 


Term
Compare static and total pressure 

Definition
Static pressure is the pressure felt by a particle of air in the airflow, while Total presure is the presure felt by a foreign object in the airflow.
For ex, A bug flies into you inside your car while you are driving, windows up, at 60mph. since both you and the bug are doing 60mph, the force is very small.
now if you open the window, and the bug flies out and hits a person standing on the side of the road, the force is much greater, since the bug and person are not traveling the same speed. 


Term
Define Vtrue and Ve
Vtrue =
Ve = 

Definition
Sqrt[(2*(P0P))/Roh] for Vtrue
Sqrt[(2*(P0P))/Roh(s)] for Ve, where Roh(s) is the air density at sea level 


Term
A pitot tube is used to measure air pressure acting on an aircraft. The equation for this is
P0/P1 =
P0 = total pressue, 

Definition
(1 + [(γ1)/2]*M1^2)^[γ/(γ1)] γ = 1.4 


Term
The relationship between T0 (total temperature) and T1 (static temperature) is given by
T0/T1 = 

Definition
1+ [(γ1)/2]*M1^2 γ = 1.4 


Term
The relationship between Roh0 and Roh1 is shown by the equation :
Roh0/Roh1 =
Roh0 = Total density Roh1 = static Density 

Definition
= (1 + [(γ1)/2]*M1^2)^[1/(γ1)] γ = 1.4 


Term
As a fluid element flows through a shock wave
a) Mach number (M) b) static pressure (P1) c) static Temperature (T1) d) flow velocity e) Total Pressure (P0) f) Total temperature (T0) 

Definition
a) decreases b) increases c) increases d) decreases e) decreases f) stays the same (for a perfect gas) 


Term
For Pitot Tubes in supersonic airspeeds, the shockwave must be accounted for
P(02)/P1 = 

Definition
{[((γ+1)^2)*M1^2]/[4*γ*M1^22(γ1)]}^[γ/(γ1)]
All that ^^ Times (*) [1γ+2γ*M1^2]/(γ+1)
Rayleigh Pitot Tube formula, where P(02) is the total P behind the wave, and P1 is the tatic pressure infront of the wave. 


Term
a) For subsonic airflow, for the velocity to inrease, the Area must ...
b) for Supersonic airflow, for the velocity to increase, the area must 

Definition
a) decrease ( think subsonic wind tunnel)
b) Increase (think rocket engine nozzle) 


Term
The boundary layer that surrounds an object in an airstream is caused by 

Definition
friction between the gas and the surface of the object 


Term
The shear stress due to air resistance is 

Definition
τw = μ*(dV/dY), Y = 0
μ = absolute viscosity coefficient of the gas (mass/(length*time)) 

