Characterization of Inlet Contamination Potential

Slides:



Advertisements
Similar presentations
Ferry Fuel System Reference: Pilot Int’l PI-1200M Manual dtd
Advertisements

Analyzer flow (30 lpm) Carbon vane pump Exhaust filter System vacuum gauge Spare#1 (30 lpm) Spare#2 (30 lpm) Spare#3 (30 lpm) Spare#4 (30 lpm) Blower#1.
Modeling of Fuel Tank Inerting for FAA OBIGGS Research
Observing Networks and Data Aircraft Humidity Sensor Enters the E-AMDAR Fleet A. Hoff (Deutscher Wetterdienst, Department of Observing Networks and Data)
AMS Performance at DC3-Test Some preliminary results Pedro Campuzano Jost, Douglas Day, Michael Lechner, Jose Luis Jimenez.
Flight Instrument Systems
The Flame Deflector and Five Segment Booster By: Geoffrey Husk.
HIAPER Modular Inlets (HIMIL) & Instrument Exhaust System - Dave Rogers - Outline HIMIL description contamination testing re-install HIMIL to different.
Progressive Science Missions Overview of resources Schedule Data logging and communication Individual flight plans Joint flight plans Agenda:
Basic Aerodynamics and Stability Presented by: Mr Jamie Presser.
Flammability Characteristics of JP-8 Fuel Vapors Existing Within a Typical Aircraft Fuel Tank Steven M. Summer Department of Mechanical & Aerospace Engg.
Aircraft Systems Oxygen Systems A-4N/TA-4. Aircraft Systems Oxygen System LESSON OBJECTIVES To give the TP information on the Oxygen System to include.
ME 388 – Applied Instrumentation Laboratory Wind Tunnel Lab
6.07 Stalls References: FTGU pages 18, 35-38
A Survey of Wyoming King Air and Cloud Radar Observations in the Cumulus Photogrammetric In-Situ and Doppler Observations (CuPIDO) experiment J. Cory Demko.
 Purpose  Test design  Measurement system and Procedures  Uncertainty Analysis.
Introduction to Fluid Mechanics
Actuators.
¾-1/2” Red. Union 3/8”OD ACSM Inlet Configuration 0.1 lpm to ACSM with PM 1 passing thru aerodynamic lens 2.9 lpm to external Pump* Sheath Flow 6 lpm dry.
Aircraft Ice Protection Systems
Fuel Tank Inerting Joint Airbus/FAA, A320 Flight Tests
Mounting Direction Water Cooler Best solution OK Risk of air bubbles in the system Heatsink Water channels Inlet Outlet.
Application of a High-Pulse-Rate, Low-Pulse-Energy Doppler Lidar for Airborne Pollution Transport Measurement Mike Hardesty 1,4, Sara Tucker 4*,Guy Pearson.
AIR NAVIGATION Part 1 Distance & Speed. RECAP Latitude and Longitude lines divide the surface of the Earth into degrees and minutes. One minute of latitude.
Glider Instrumentation and Plumbing NCSA Safety Seminar 11 Feb 2006.
1 Measuring the flow boundary layer on HIAPER's fuselage Rogers, Fox, Lord, Stith, Maclean, EOL technical staff, Friehe, McClusky goal: measure air speed.
Lecture 5: Climb PERFORMANCE
Federal Aviation Administration 0 Composite Wing Tank Flammability April 2-3, Composite and Aluminum Wing Tank Flammability Comparison Testing Steve.
Systems Fire Protection Working Group DTA - Grenoble, France June 21-22, 2003 FAA Inerting System Flight Testing on an Airbus A320 William Cavage AAR-440.
 Purpose  Test design  Measurement system and Procedures  Uncertainty Analysis.
IIT-Madras, Momentum Transfer: July 2005-Dec 2005.
UNIVERSITY OF LEEDS Institute for Atmospheric Science SCHOOL OF EARTH AND ENVIRONMENT VACC - Volatility Aerosol Composition and Concentration.
Microlight Flight Lessons. Exercise 10A Slow Flight Aim To become familiar with the feel of the aircraft in slow flight just above the stall speed, and.
ME 322: Instrumentation Lecture 11 February 11, 2015 Professor Miles Greiner Pitot probe operation, non-linear transfer function, fluid density, uncertainty,
Atmospheric Technology Division Rain In Cumulus over the Ocean Jorgen Jensen, Jeff Stith, Teresa Campos, Mary Barth, Dave Rogers NCAR science to complement.
Aerodynamic Forces Lift and Drag.
6.07 Stalls References: FTGU pages 18, 35-38
Measurement of Pressure Distribution and Lift for an Airfoil  Purpose  Test design  Measurement system and Procedures  Uncertainty Analysis  Data.
Progress Report. What we’ve done so far… A fluid dynamics model to calculate leakage A method to set pass/fail limits for roughness A Quality Control.
Background 1. Energy conservation equation If there is no friction.
Lecture Leading Cadet Training Principles of Flight 3 Drag.
Full-Scale Ground-Based Inerting ___________________________________ AAR-422 Fire Safety R&D July 17-18, 2001 International Aircraft Systems Fire Protection.
On Reynolds Stresses over Wind Waves Tel-Aviv University School of Mechanical Engineering Supported by Israel Science Foundation Lev Shemer and Andrey.
Chalmers University of Technology Elementary axial turbine theory –Velocity triangles –Degree of reaction –Blade loading coefficient, flow coefficient.
Federal Aviation Administration Halon 1211 Stratification/ Localization in Aircraft Louise Speitel Fire Safety Branch FAA Wm. J. Hughes Technical Center.
Federal Aviation Administration 0 Composite Wing Tank Flammability November 20, Composite and Aluminum Wing Tank Flammability Comparison Testing.
March 26-27, 2003 International Aircraft Systems Fire Protection Working Group Phoenix, Az Inerting of a Scale 747SP Center-Wing Fuel Tank During a Typical.
Original CPC Box schematic
October 30-31, 2002 International Aircraft Systems Fire Protection Working Group Atlantic City, NJ Inerting of a Scale 747SP Center Wing Fuel Tank During.
MECH 322 Instrumentation Lab 6 Fluid Speed and Volume Flow Rate Performed: February 27, 2007 Group 0 Miles Greiner Lab Instructors: Mithun Gudipati, Venkata.
Federal Aviation Administration 0 Composite Wing Tank Flammability May 19 th, Composite and Aluminum Wing Tank Flammability Comparison Testing Steve.
Federal Aviation Administration 0 Composite Wing Tank Flammability May 20, Composite and Aluminum Wing Tank Flammability Comparison Testing Steve.
Some Observations from Using a Colloidal Borescope in Basalt Aquifers Gerry Winter.
ME 391 Instrumentation LAB #6 Volume Flow Rate and Centerline Speed in a Tube Wind Tunnel Performed: 03/05/2004 Soma: I believe I performed 50% of this.
Aerosol Working Group Location: Room 2.16, 2 nd Floor, Williamson Building, Oxford Road, Manchester 11:00 Coffee 11:30 – 13:00Instrument Updates: CCN/CPC/PSAPJamie.
Preliminary Results from FLAGG-MD Test Flight 02/06/2015.
Exercise 10B Stalling Aim To recognise and enter a fully developed stall in various modes of flight both straight and turning, then to recover with minimum.
AIR CONDITIONING SYSTEM. FUNCTION Air conditioning systems create a safe and comfortable environment for passengers and crews in the aircraft cabin. The.
The BioTector B7000i TOC analyzer with integrated oxygen concentrator
Date of download: 10/9/2017 Copyright © ASME. All rights reserved.
CGS Ground School Technical The Variometer © Crown Copyright 2011
Monitoring H2 by Real Time H2 Sensor
6.07 Stalls References: FTGU pages 18, 35-38
LAB #6 Volume Flow Rate and Centerline Speed in a Tube Wind Tunnel
Air Volume Flow Rate and Centerline Velocity in a Tube Wind Tunnel
Aircraft Performance Charts Private Pilot Ground School
Chain Wear QI Plots Data from Testkeys , , , , and
Ventilation Measurement Tracer Gas Decay Testing
Catalyze Concentrations Related to Oxygen Production
Exhaust gas intake to cabin air.
Presentation transcript:

Characterization of Inlet Contamination Potential - Teresa Campos - The cabin exhaust valve is located just aft of the nose on the right fuselage. The cabin volume of 2400 cu ft undergoes complete turnover of fresh air in 2.8 minutes, implying about 70kL/min flow rate exiting the cabin. To check the potential for sampling boundary layer air with the HIMIL, it was proposed to release a pulse of high concentration of CO2 at the cabin exhaust vent and alternately sample from the HIMIL and boundary layer ports. This exercise was conducted during speed runs and level flight legs. Flow was split to look for cabin CN using this inlet. In this figure, the BL depth was ~4.0" for both the fastest and slowest flight speeds. Note on this semi-log plot that the profile of dynamic pressures is approximately a straight line within the BL. qcR, qcF are dynamic pressures at the Radome and Fuselage pitot tube.

Characterization of Inlet Contamination Potential Due to time and instrument performance limitations, only one aperture location was tested for CO2 contamination sampling during Progressive Science: FS 498R. Data have not been fully analyzed. Preliminary results imply that during straight and level flight, boundary layer air is not sampled even at the HIMIL distance from the fuselage. However, enhancement of CO2 above background levels is observed at even small changes in aircraft attack angle. In this figure, the BL depth was ~4.0" for both the fastest and slowest flight speeds. Note on this semi-log plot that the profile of dynamic pressures is approximately a straight line within the BL. qcR, qcF are dynamic pressures at the Radome and Fuselage pitot tube.