- Pre lab for Lab 2. Please bring completed to the laboratory. A For the NACA 4412 whose geometry data is speci ed in the lab handout, the following
- Portfolio Assignment #2. 1) Show the appropriate equation for thrust required for your aircraft.
- Portfolio 2 redo notes Please note that the spec sheets for the various aircraft have been updated. These updates were made
- Homework 2, Due Tues. Jan. 29 1 For incompressible ow we know that 5v = 0.
- Portfoilio Assignment III 1) Plot the rate of climb versus flight speed at sea level and at altitude (at altitude remember
- INVERSE AEROACOUSTIC PROBLEM FOR A RECTANGULAR WING IN A GUST y
- Reduction of the Complexity of the Intrisically Nonlinear Problem of Aerodynamic Sound Generation
- THE PRESSURE FIELD OF A GUST INTERACTING WITH A FLAT PLATE Ha z M. Atassi and Sheryl M. Patrick y
- INVERSE PROBLEMS IN UNSTEADY AERODYNAMICS AND AEROACOUSTICS Sheryl M. Patrick y and Ha z M. Atassi z
- Proceedings of IMECE 07 2007 ASME International Mechanical Engineering Congress and Exposition
- VKI Lecture Series: Advances in Aeroacoustics
- Acoustic Energy Absorption By A Shear Layer y Sheryl M. Grace z
- Aerodynamic Forces, Atmosphere University Corporation for Atmospheric Research
- AM201 Fall 2007 Javafoil exercise
- 1. Problem 3.2 in text 2. A gas has a molar mass of 44 and a specific heat ratio of 1.3. At a certain point in
- Design of a supersonic double wedge airfoil. In this assignment you will create a matlab code that accepts the following input param-
- Conical flow simulation project. In this assignment you will create a matlab code that accepts the following input param-
- 1. Problems 9.2, 9.3 (a&c), 9.4, 9.11. 6. A symmetrical double-wedge airfoil has a maximum thickness equal to 0.05 times the
- AM201 Fall 2006 Javafoil exercise
- AIAA 20000607 FREE-WAKE ANALYSIS FOR
- Wing Geometry Effect on Blade-Vortex Interaction
- Portfoilio Assignment III 1) Plot the max load factor curves for your aircraft (i.e. create a graph like in Figure 6.2).
- XFOIL Quick Reference Once logged into conductor-am, type xfoil at the prompt.
- Aircraft Portfolio Overview AM201 Fall 2006
- Homework 4, Due Thurs. Feb. 14 1 A two-dimensional velocity eld is given as
- Homework 9, Due Tues. April 30 1 For the approximate at-plate laminar boundary layer pro le
- Hybrid Prediction of Fan Tonal Noise Sheryl M. Grace
- AIAA 20012209 UNSTEADY BLADE RESPONSE: THE BVI MODEL
- Aircraft Portfolio Overview Each performance concept that is introduced in the course will be used to analyze your aircraft's
- 1. A convergent-divergent nozzle is designed to expand air from a chamber in which the pressure is 800 kPa and the temperature is 40
- INVERSE AEROACOUSTIC PROBLEM FOR A RECTANGULAR WING INTERACTING WITH A GUST y
- Proceedings of IMECE 2000 International Mechanical Engineering Congress & Exposition
- THE INFLUENCE OF GRAZING FLOW ON THE RAYLEIGH CONDUCTIVIITY OF AN APERTURE OF
- Aircraft Project Building Information
- Tutorial: Computational Methods for Aeroacoustics
- Aircraft Project Building Information
- Exterior Acoustic Modeling for Gerbils
- IMPLICATIONS OF RECENT BVI CALCULATIONS ON PREDICTION METHODS FOR NOISE FROM TURBULENCE INGESTION
- Wing Specifications Your task for this project is to create a wing to use in conjunction with the fuselage of the
- PREDICTING THE UNSTEADY PRESSURE ON A STREAMLINED BODY FROM ITS ACOUSTIC SIGNAL
- Computational Fluid Dynamics Laboratory AM423 Compressible Aerodynamics
- ACOUSTIC RADIATION FROM A LIFTING AIRFOIL IN NONUNIFORM SUBSONIC FLOWS
- PREDICTING UNSTEADY AERODYNAMIC PARAMETERS FROM AIRFOIL SURFACE PRESSURE MEASUREMENTS
- AN INVERSE PROBLEM IN THE PRESENCE OF A MEAN FLOW Sheryl M. Patrick y
- Proceedings of 2001 ASME International Mechanical Engineering Congress and Exposition
- Effect of Rotor Wake Structure on Fan Interaction Jeremy Maunus
- Homework 3, Due Thurs. Feb. 7 2 CFD type problems