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MAE 1202: AEROSPACE PRACTICUM. Lecture 5: Compressible and Isentropic Flow 1 February 11, 2013 Mechanical and Aerospace Engineering Department Florida Institute of Technology D. R. Kirk. READING AND HOMEWORK ASSIGNMENTS. Reading: Introduction to Flight , by John D. Anderson, Jr.

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### MAE 1202: AEROSPACE PRACTICUM

Lecture 5: Compressible and Isentropic Flow 1

February 11, 2013

Mechanical and Aerospace Engineering Department

Florida Institute of Technology

D. R. Kirk

• Reading: Introduction to Flight, by John D. Anderson, Jr.

• For this week’s lecture: Chapter 4, Sections 4.10 - 4.21, 4.27

• For next week’s lecture: Chapter 5, Sections 5.1 - 5.13

• Lecture-Based Homework Assignment:

• Problems: 4.7, 4.11, 4.18, 4.19, 4.20, 4.23, 4.27

• DUE: Friday, February 22, 2013 by 5 PM

• Problems: 5.2, 5.3, 5.4, 5.6

• DUE: Friday, March 1, 2013 by 5 PM

• Turn in hard copy of homework

• Also be sure to review and be familiar with textbook examples in Chapter 5

• 5.2: L = 23.9 lb, D = 0.25 lb, Mc/4 = -2.68 lb ft

• Note 1: Two sets of lift and moment coefficient data are given for the NACA 1412 airfoil, with and without flap deflection. Make sure to read axis and legend properly, and use only flap retracted data.

• Note 2: The scale for cm,c/4 is different than that for cl, so be careful when reading the data

• 5.3: L = 308 N, D = 2.77 N, Mc/4 = - 0.925 N m

• 5.4:a = 2°

• 5.6: (L/D)max ~ 112

• Create most elaborate, complex, stunning Aerospace Related project in Creo

• Criteria: Assembly and/or exploded view

• First place

• Either increase your grade by an entire letter (C → B), or

• Second place: +10 points on final exam

• Third place: +10 points on final exam

### If you do the PRO|E challenge…Do not let it consume you!

Constant along a streamline

• One of most fundamental and useful equations in aerospace engineering!

• Remember:

• Bernoulli’s equation holds only for inviscid (frictionless) and incompressible (r = constant) flows

• Bernoulli’s equation relates properties between different points along a streamline

• For a compressible flow Euler’s equation must be used (r is variable)

• Both Euler’s and Bernoulli’s equations are expressions of F = ma expressed in a useful form for fluid flows and aerodynamics

How do we measure an airplanes speed in flight?

Pitot tubes are used on aircraft as speedometers (point measurement)

13

In aerodynamics, 2 types of pressure: Static and Total (Stagnation)

Static Pressure, p

Due to random motion of gas molecules

Pressure we would feel if moving along with flow

Strong function of altitude

Total (or Stagnation) Pressure, p0 or pt

Property associated with flow motion

Total pressure at a given point in flow is the pressure that would exist if flow were slowed down isentropically to zero velocity

p0 ≥ p

14

Static

pressure

Dynamic

pressure

Total

pressure

Incompressible Flow

• Measures total pressure

• Open at A, closed at B

• Gas stagnated (not moving) anywhere in tube

• Gas particle moving along streamline C will be isentropically brought to rest at point A, giving total pressure

17

Point A: Static Pressure, p

Only random motion of gas is measured

Point B: Total Pressure, p0

Flow is isentropically decelerated to zero velocity

A combination of p0 and p allows us to measure V1 at a given point

Instrument is called a Pitot-static probe

p

p0

18

Static

pressure

Dynamic

pressure

Total

pressure

Incompressible Flow

19

What is value of r?

If r is measured in actual air around the airplane

Measurement is difficult to do

Practically easier to use value at standard seal-level conditions, rs

This gives an expression called equivalent airspeed

20

• Aircraft crashed following an aerodynamic stall caused by inconsistent airspeed sensor readings, disengagement of autopilot, and pilot making nose-up inputs despite stall warnings

• Reason for faulty readings is unknown, but it is assumed by accident investigators to have been caused by formation of ice inside pitot tubes, depriving airspeed sensors of forward-facing air pressure.

• Pitot tube blockage has contributed to airliner crashes in the past

• Lift due to imbalance of pressure distribution over top and bottom surfaces of airfoil (or wing)

• If pressure on top is lower than pressure on bottom surface, lift is generated

• Why is pressure lower on top surface?

• We can understand answer from basic physics:

• Continuity (Mass Conservation)

• Newton’s 2nd law (Euler or Bernoulli Equation)

Lift Force = SPA

• Flow velocity over top of airfoil is faster than over bottom surface

• Streamtube A senses upper portion of airfoil as an obstruction

• Streamtube A is squashed to smaller cross-sectional area

• Mass continuity rAV=constant: IF A↓ THEN V↑

Streamtube A is squashed

most in nose region

A

B

• As V ↑ p↓

• Incompressible: Bernoulli’s Equation

• Compressible: Euler’s Equation

• Called Bernoulli Effect

• With lower pressure over upper surface and higher pressure over bottom surface, airfoil feels a net force in upward direction → Lift

Most of lift is produced

in first 20-30% of wing

Can you express these ideas in your own words?

Incorrect Lift Theory

• http://www.grc.nasa.gov/WWW/k-12/airplane/wrong1.html

• Steady, incompressible flow of an inviscid (frictionless) fluid along a streamline or in a stream tube of varying area

• Most important variables: p and V

• T and r are constants throughout flow

continuity

Bernoulli

What if flow is high speed, M > 0.3?

What if there are temperature effects?

How does density change?

1st LAW OF THERMODYNAMICS (4.5)

Boundary

System

e (J/kg)

Surroundings

• System (gas) composed of molecules moving in random motion

• Energy of molecular motion is internal energy per unit mass, e, of system

• Only two ways e can be increased (or decreased):

• Heat, dq, added to (or removed from) system

• Work, dw, is done on (or by) system

• Do not allow size of balloon to change (hold volume constant)

• Turn on a heat lamp

• Heat (or q) is added to the system

• How does e (internal energy per unit mass) inside the balloon change?

• *You* take balloon and squeeze it down to a small size

• When volume varies work is done

• Who did the work on the balloon?

• How does e (internal energy per unit mass) inside the balloon change?

• Where did this increased energy come from?

1st LAW OF THERMODYNAMICS (4.5)

Boundary

SYSTEM

(unit mass of gas)

SURROUNDINGS

dq

• System (gas) composed of molecules moving in random motion

• Energy of all molecular motion is called internal energy per unit mass, e, of system

• Only two ways e can be increased (or decreased):

• Heat, dq, added to (or removed from) system

• Work, dw, is done on (or by) system

1st LAW IN MORE USEFUL FORM (4.5)

• 1st Law: de = dq + dw

• Find more useful expression for dw, in terms of p and r (or v = 1/r)

• When volume varies → work is done

• Work done on balloon, volume ↓

• Work done by balloon, volume ↑

Change in

Volume (-)

Define a new quantity

called enthalpy, h:

(recall ideal gas law: pv = RT)

Differentiate

Substitute into 1st law

(from previous slide)

Another version of 1st law

that uses enthalpy, h:

• Addition of dq will cause a small change in temperature dT of system

dq

dT

• Specific heat is heat added per unit change in temperature of system

• Different materials have different specific heats

• Balloon filled with He, N2, Ar, water, lead, uranium, etc…

• ALSO, for a fixed dq, resulting dT depends on type of process…

• Addition of dq will cause a small change in temperature dT of system

• System pressure remains constant

dq

dT

Extra Credit #1:

Show this step

• Addition of dq will cause a small change in temperature dT of system

• System volume remains constant

dq

dT

Extra Credit #2:

Show this step

• Addition of dq will cause a small change in temperature dT of system

• Specific heat is heat added per unit change in temperature of system

• However, for a fixed dq, resulting dT depends on type of process:

Constant Pressure

Constant Volume

Specific heat ratio

For air, g = 1.4

• Goal: Relate Thermodynamics to Compressible Flow

• dq = 0

• Note: Temperature can still change because of changing density

• Reversible Process: No friction (or other dissipative effects)

• Isentropic Process: (1) Adiabatic + (2) Reversible

• (1) No heat exchange + (2) no frictional losses

• Relevant for compressible flows only

• Provides important relationships among thermodynamic variables at two different points along a streamline

g = ratio of specific heats

g = cp/cv

gair=1.4

Energy can neither be created nor destroyed

1st law in terms of enthalpy

Recall Euler’s equation

Combine

Integrate

• Energy can neither be created nor destroyed; can only change physical form

• Same idea as 1st law of thermodynamics

Energy equation for frictionless,

h = enthalpy = e+p/r = e+RT

h = cpT for an ideal gas

Also energy equation for

Relates T and V at two different points along a streamline

SUMMARY OF GOVERNING EQUATIONS (4.8)STEADY AND INVISCID FLOW

• Incompressible flow of fluid along a streamline or in a stream tube of varying area

• Most important variables: p and V

• T and r are constants throughout flow

continuity

Bernoulli

continuity

• Compressible, isentropic (adiabatic and frictionless) flow along a streamline or in a stream tube of varying area

• T, p, r, and V are all variables

isentropic

energy

equation of state

at any point

• Sound waves travel through air at a finite speed

• Sound speed (information speed) has an important role in aerodynamics

• Combine conservation of mass, Euler’s equation and isentropic relations:

• Speed of sound, a, in a perfect gas depends only on temperature of gas

• Mach number = flow velocity normalizes by speed of sound

• If M < 1 flow is subsonic

• If M = 1 flow is sonic

• If M > flow is supersonic

• If M < 0.3 flow may be considered incompressible

Stream tube

Viscid flow

Inviscid flow

Compressible flow

Incompressible flow

Laminar flow

Turbulent flow

Constant pressure process

Constant volume process

Reversible

Isentropic

Enthalpy

KEY TERMS: CAN YOU DEFINE THEM?

MEASUREMENT OF AIRSPEED:SUBSONIC COMRESSIBLE FLOW

• If M > 0.3, flow is compressible (density changes are important)

• Need to introduce energy equation and isentropic relations

cp: specific heat at constant pressure

M1=V1/a1

gair=1.4

MEASUREMENT OF AIRSPEED:SUBSONIC COMRESSIBLE FLOW

• So, how do we use these results to measure airspeed

p0 and p1 give

Flight Mach number

Mach meter

M1=V1/a1

Actual Flight Speed

Actual Flight Speed

using pressure difference

What is T1 and a1?

Again use sea-level conditions Ts, as, ps (a1=340.3 m/s)

• A rocket is flying at Mach 6 through a portion of the atmosphere where the static temperature is 200 K

• What temperature does the nose of the rocket ‘feel’?

• T0 = 200(1+ 0.2(36)) = 1,640 K!

Total temperature

Static temperature

Vehicle flight

Mach number

MEASUREMENT OF AIRSPEED:SUPERSONIC FLOW

• What can happen in supersonic flows?

• Supersonic flows (M > 1) are qualitatively and quantitatively different from subsonic flows (M < 1)

• Think of a as ‘information speed’ and M=V/a as ratio of flow speed to information speed

• If M < 1 information available throughout flow field

• If M > 1 information confined to some region of flow field

MEASUREMENT OF AIRSPEED:SUPERSONIC FLOW

Notice how different this expression is from previous expressions

You will learn a lot more about shock wave in compressible flow course

• Subsonic, incompressible

• Subsonic, compressible

• Supersonic

Isentropic flow in a streamtube

Differentiate

Euler’s Equation

Since flow is isentropic

a2=dp/dr

Area-Velocity Relation

• IF Flow is Subsonic (M < 1)

• For V to increase (dV positive) area must decrease (dA negative)

• Note that this is consistent with Euler’s equation for dV and dp

• IF Flow is Supersonic (M > 1)

• For V to increase (dV positive) area must increase (dA positive)

• IF Flow is Sonic (M = 1)

• M = 1 occurs at a minimum area of cross-section

• Minimum area is called a throat (dA/A = 0)

2: OUTLET

1: INLET

M1 < 1

M1 > 1

V2 > V1

V2 < V1

2: OUTLET

1: INLET

M1 < 1

M1 > 1

V2 < V1

V2 > V1

2: OUTLET

1: INLET

• A converging-diverging, with a minimum area throat, is necessary to produce a supersonic flow from rest

Rocket nozzle

Supersonic wind tunnel section

SUMMARY OF GOVERNING EQUATIONS (4.8)STEADY AND INVISCID FLOW

• Incompressible flow of fluid along a streamline or in a stream tube of varying area

• Most important variables: p and V

• T and r are constants throughout flow

continuity

Bernoulli

continuity

• Compressible, isentropic (adiabatic and frictionless) flow along a streamline or in a stream tube of varying area

• T, p, r, and V are all variables

isentropic

energy

equation of state

at any point