Standard Atmosphere
Four Main Regions of Std Atm
Troposphere region nearest the surface of the
earth extends from ~ 5mi at the poles to 10 mi at
the equator (clouds and turbulent conditions)
Stratosphere from the top of the Troposphere
to ~50-75 mi abov
AE/ME 5363 MAE 4301
Fall 2016
HW#3
Hover Analysis
Analysis Assignment: Due Monday, October 24th
Given the supplied HOGE analysis spreadsheet (with the geometry in the
spreadsheet) calculate and plot the hover ceiling (maximum altitude of hover vs.
gross w
AE/ME 5363 MAE 4301
Fall 2016
Reading Assignment #1
Basic Helicopter Introduction
Reading Assignment: pp 1-45 Aerodynamics of the Helicopter by Gessow & Myers (provided in
Blackboard)
1
For the helicopter provided in class (using the input data in the program and assuming a
standard day) evaluate the following mission.
Calculate and tabulate the following data for each segment of the mission.
1) Time
2) Fuel used
3) Speed
4) Range
5) Wei
Introduction to Hovering Theory
Introduction to Hovering Theory
We will initiate our study of the aerodynamics of
the rotor by first examining the aerodynamics
of the rotor in hover and vertical flight as
there is no dissymmetry of the velocity in
these c
Introduction to Hovering Theory
Introduction to Hovering Theory
General Equation for Induced Velocity
Introduction to Hovering Theory
General Equation for Induced Velocity
1
2
dT b r a cdr
2
from blade element theory
Examine the elemental thrust from a
mo
AE/ME 5363 MAE 4301
Fall 2016
HW#4
Drag Analysis
Analysis Assignment: Due Wednesday, November 9th
Given the supplied lines drawing, component drag handout, NASA CR and S. F.
Hoernors text Aerodynamic Drag (in library) calculate the equivalent flat plate
d
AE/ME 5363 MAE 4301
Fall 2016
HW#1
Standard Atmosphere
Reading Assignment: see STD ATMOS 2 document in Blackboard for model development review
Analysis Assignment:
Develop a computer program to determine the properties of a standard atmosphere for altitud
Introduction
Rotorcraft Concepts Early Visions
Rotorcraft Concepts Early Attempts
Rotorcraft Concepts Autogyros
Juan de la Cierva
Rotorcraft Concepts Autogyros
Rotorcraft Concepts Autogyros/Compounds
Rotorcraft Concepts Early Helicopters
AE 5326
Aerospace Propulsion
07B Turbomachinery
(Axial Flow Compressors)
Axial Flow Compressor
Axial Flow Compressors
Comments
The flow is inherently 3-D
Simplified analysis - divide the 3-D flow field into three 2-D
flow fields
Complex flow field is
AE 5326
Airbreathing Propulsion
04A(2) - Ideal Cycle Analysis
(Turbojet)
GE J47 Turbojet
The J47 was developed by the General Electric Company and was first flight-tested in
May 1948 as a replacement for the J35 used in the North American XF-86 "Sabre". I
AE 5326
Airbreathing Propulsion
04A(1) Ideal Cycle Analysis
(Brayton Cycle)
Introduction
Thermodynamic cycle analysis provides a consistent
method of predicting gas turbine performance as a function of
individual component thermodynamic parameters (prima
AE 5326
Airbreathing Propulsion
04B(2) Non-Ideal Cycle Analysis
(Afterburning Turbojet ACP)
Average cp (ACP) Model
ACP thermodynamic model ~ use average value of cp and for
temperature range covered by each component
2- model use cpc and c for component
AE 5326
Aerospace Propulsion
07A Turbomachinery
(Fundamental Concepts)
Modern Fan Design
The Trent 900 utilizes advanced
Swept Fan technology
The swept fan of the Trent 1000 (20 blades) increased aerodynamic efficiency and less noise
http:/www.investis.co
Glass, Brandon
AE5363-001
Intro to Rotorcraft
02/16/2017
Using the rotor geometry and operating conditions as in problem #2 , calculate the induced
velocity distribution of the rotor(Aerodynamics of the Helicopter by Gessow and Myer p. 68):
Geometry: Roto
AE5327/ MAE4301
Introduction to Computational Fluid Dynamics
Homework #3
Due 11/13/14
Given the following model equation:
d
d
+ 0.1
= 0.0
dt
dx
Perform the following tasks:
a) Derive the amplification factor for these schemes:
i. forward Euler with first-
AE5327/ MAE4301
Introduction to Computational Fluid Dynamics
Homework #2
Due 10/28/14
Given the following model equation:
d 2
0.1 x 2
2
dx
Perform the following tasks:
a) Derive the exact solution to the equation for the boundary conditions
(1.0)=ddx(0.0
Combustion HW 3
1.
Consider the hypothetical reaction
A+BC+D
The reaction as shown is exothermic. Which has the larger activation energy, the exothermic
forward reaction or its backward analog? Explain. (Hint see the Graph from class on activation
energy)
Project Ideas 2015
The project report should include the following sections: introduction/problem
background, methodology, results, conclusions, references, and code listing (if a program
was developed). The report is due by email at or before the end of
Homework Chapter 4
Due 11/01/2016
1. A stoichiometric fuelair mixture flowing in a Bunsen burner forms a well-defined conical flame. The mixture is then made leaner. For the
same flow velocity in the tube, how does the cone angle change for the leaner mix
Combustion Homework 1
DUE 09/15/2016
1. Suppose that methane and air in stoichiometric proportions are
brought into a calorimeter at 500 K. The product composition is
brought to the ambient temperature (298 K) by the cooling water.
The pressure in the cal
AE5327/MAE4301
Introduction to Computational Fluid Dynamics
Homework #1
Due 10/9/14
1. Starting from the dimensional form, derive the non-dimensional form of the
unsteady incompressible Navier-Stokes equations (without gravity & energy
equation). The fina