Airplane Icing
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Initial Piloted Simulation Study of Geared Flap R Tilt-Wing V/STOL
R NASA Technical Memorandum 103872 Initial Piloted Simulation Study of Geared Flap Control r Tilt-Wing V/STOL Aircraft Lourdes M. Guerrero and Lloyd Da Corliss [NASA-TM-103872) INITIAL PILOTED N93-10741 ~~~U~A~~~NSTUDY QF GEARft) FLAP ~Q~~~~~ fOR TILT-WING V/STOL AIRCRAFT (NASA) 39 p Wncfas 63/08 01180?6 October 1991 National Aeronautics and Space Administration NASA Technical Memorandum 103872 Initial Piloted Simulation Study of Geared Flap Control For Tilt-Wing V/STOL Aircraft Lourdes M. Guerrero and Lloyd D Corliss, Ames Research Center, Moffett Field, California October 1991 National Aeronautics and Space Administration Ames Research Center Moffett Field, Califorrlia94035 -1000 SUMMARY A simulation model was developed for piloted evaluations of a representative tilt-wing V/STOL (Vertical/Short Takeoff and Landing) aircraft. Using this model an initial tilt-wing simulation study was conducted in 1990 on the Ames Vertical Motion Simulator In the past, all tilt-wing aircraft have required a horizontal tail rotor or reaction jets to provide pitch control in hover and low speeds. To alleviate this need, devices such as monocyclic propellers and a geared flap have been proposed for providing control at low speed. The geared flap is the sub- ject of this study and it is compared to the conventional flap used in previous tilt-wing aircraft. Objectives of the study were to simulate a tilt-wing V/STOL aircraft, to evaluate and compare the control effectiveness and handling qualities of both a conventional (programmed flap) and the geared flap control configurations, and to determine the feasibility of eliminating the horizontal tail rotor or reaction jets of prior designs through the use of the geared flap control configuration. -
River Ice Management in North America
RIVER ICE MANAGEMENT IN NORTH AMERICA REPORT 2015:202 HYDRO POWER River ice management in North America MARCEL PAUL RAYMOND ENERGIE SYLVAIN ROBERT ISBN 978-91-7673-202-1 | © 2015 ENERGIFORSK Energiforsk AB | Phone: 08-677 25 30 | E-mail: [email protected] | www.energiforsk.se RIVER ICE MANAGEMENT IN NORTH AMERICA Foreword This report describes the most used ice control practices applied to hydroelectric generation in North America, with a special emphasis on practical considerations. The subjects covered include the control of ice cover formation and decay, ice jamming, frazil ice at the water intakes, and their impact on the optimization of power generation and on the riparians. This report was prepared by Marcel Paul Raymond Energie for the benefit of HUVA - Energiforsk’s working group for hydrological development. HUVA incorporates R&D- projects, surveys, education, seminars and standardization. The following are delegates in the HUVA-group: Peter Calla, Vattenregleringsföretagen (ordf.) Björn Norell, Vattenregleringsföretagen Stefan Busse, E.ON Vattenkraft Johan E. Andersson, Fortum Emma Wikner, Statkraft Knut Sand, Statkraft Susanne Nyström, Vattenfall Mikael Sundby, Vattenfall Lars Pettersson, Skellefteälvens vattenregleringsföretag Cristian Andersson, Energiforsk E.ON Vattenkraft Sverige AB, Fortum Generation AB, Holmen Energi AB, Jämtkraft AB, Karlstads Energi AB, Skellefteå Kraft AB, Sollefteåforsens AB, Statkraft Sverige AB, Umeå Energi AB and Vattenfall Vattenkraft AB partivipates in HUVA. Stockholm, November 2015 Cristian -
American Eagle Flight 3008 ALPA Submission
SUBMISSION OF THE AIR LINE PILOTS ASSOCIATION TO THE NATIONAL TRANSPORTATION SAFETY BOARD REGARDING AN INCIDENT INVOLVING AMERICAN EAGLE AIRLINES FLIGHT 3008 Santa Maria, CA January 2, 2006 1 SUMMARY..........................................................................................................................................3 2 HISTORY OF FLIGHT......................................................................................................................3 3 WEATHER ..........................................................................................................................................5 3.1 WEATHER RADAR ........................................................................................................................ 5 3.2 AIRMETS ................................................................................................................................... 5 3.3 CONCLUSION................................................................................................................................5 4 OPERATIONS.....................................................................................................................................5 4.1 DEFERRED DE-ICE TIMER CONTROL SYSTEM .............................................................................. 5 4.2 STALL WARNING SYSTEM............................................................................................................ 6 4.3 STALL RECOVERY TRAINING ...................................................................................................... -
CANARD.WING LIFT INTERFERENCE RELATED to MANEUVERING AIRCRAFT at SUBSONIC SPEEDS by Blair B
https://ntrs.nasa.gov/search.jsp?R=19740003706 2020-03-23T12:22:11+00:00Z NASA TECHNICAL NASA TM X-2897 MEMORANDUM CO CN| I X CANARD.WING LIFT INTERFERENCE RELATED TO MANEUVERING AIRCRAFT AT SUBSONIC SPEEDS by Blair B. Gloss and Linwood W. McKmney Langley Research Center Hampton, Va. 23665 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • DECEMBER 1973 1.. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TM X-2897 4. Title and Subtitle 5. Report Date CANARD-WING LIFT INTERFERENCE RELATED TO December 1973 MANEUVERING AIRCRAFT AT SUBSONIC SPEEDS 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. L-9096 Blair B. Gloss and Linwood W. McKinney 10. Work Unit No. 9. Performing Organization Name and Address • 760-67-01-01 NASA Langley Research Center 11. Contract or Grant No. Hampton, Va. 23665 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Memorandum National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington , D . C . 20546 15. Supplementary Notes 16. Abstract An investigation was conducted at Mach numbers of 0.7 and 0.9 to determine the lift interference effect of canard location on wing planforms typical of maneuvering fighter con- figurations. The canard had an exposed area of 16.0 percent of the wing reference area and was located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. In addition, the canard could be located at two longitudinal stations. -
FAA Advisory Circular AC 91-74B
U.S. Department Advisory of Transportation Federal Aviation Administration Circular Subject: Pilot Guide: Flight in Icing Conditions Date:10/8/15 AC No: 91-74B Initiated by: AFS-800 Change: This advisory circular (AC) contains updated and additional information for the pilots of airplanes under Title 14 of the Code of Federal Regulations (14 CFR) parts 91, 121, 125, and 135. The purpose of this AC is to provide pilots with a convenient reference guide on the principal factors related to flight in icing conditions and the location of additional information in related publications. As a result of these updates and consolidating of information, AC 91-74A, Pilot Guide: Flight in Icing Conditions, dated December 31, 2007, and AC 91-51A, Effect of Icing on Aircraft Control and Airplane Deice and Anti-Ice Systems, dated July 19, 1996, are cancelled. This AC does not authorize deviations from established company procedures or regulatory requirements. John Barbagallo Deputy Director, Flight Standards Service 10/8/15 AC 91-74B CONTENTS Paragraph Page CHAPTER 1. INTRODUCTION 1-1. Purpose ..............................................................................................................................1 1-2. Cancellation ......................................................................................................................1 1-3. Definitions.........................................................................................................................1 1-4. Discussion .........................................................................................................................6 -
Electrically Heated Composite Leading Edges for Aircraft Anti-Icing Applications”
UNIVERSITY OF NAPLES “FEDERICO II” PhD course in Aerospace, Naval and Quality Engineering PhD Thesis in Aerospace Engineering “ELECTRICALLY HEATED COMPOSITE LEADING EDGES FOR AIRCRAFT ANTI-ICING APPLICATIONS” by Francesco De Rosa 2010 To my girlfriend Tiziana for her patience and understanding precious and rare human virtues University of Naples Federico II Department of Aerospace Engineering DIAS PhD Thesis in Aerospace Engineering Author: F. De Rosa Tutor: Prof. G.P. Russo PhD course in Aerospace, Naval and Quality Engineering XXIII PhD course in Aerospace Engineering, 2008-2010 PhD course coordinator: Prof. A. Moccia ___________________________________________________________________________ Francesco De Rosa - Electrically Heated Composite Leading Edges for Aircraft Anti-Icing Applications 2 Abstract An investigation was conducted in the Aerospace Engineering Department (DIAS) at Federico II University of Naples aiming to evaluate the feasibility and the performance of an electrically heated composite leading edge for anti-icing and de-icing applications. A 283 [mm] chord NACA0012 airfoil prototype was designed, manufactured and equipped with an High Temperature composite leading edge with embedded Ni-Cr heating element. The heating element was fed by a DC power supply unit and the average power densities supplied to the leading edge were ranging 1.0 to 30.0 [kW m-2]. The present investigation focused on thermal tests experimentally performed under fixed icing conditions with zero AOA, Mach=0.2, total temperature of -20 [°C], liquid water content LWC=0.6 [g m-3] and average mean volume droplet diameter MVD=35 [µm]. These fixed conditions represented the top icing performance of the Icing Flow Facility (IFF) available at DIAS and therefore it has represented the “sizing design case” for the tested prototype. -
Vertical Motion Simulator Experiment on Stall Recovery Guidance
NASA/TP{2017{219733 Vertical Motion Simulator Experiment on Stall Recovery Guidance Stefan Schuet National Aeronautics and Space Administration Thomas Lombaerts Stinger Ghaffarian Technologies, Inc. Vahram Stepanyan Universities Space Research Association John Kaneshige, Kimberlee Shish, Peter Robinson National Aeronautics and Space Administration Gordon Hardy Retired Research Test Pilot Science Applications International Corporation October 2017 NASA STI Program. in Profile Since its founding, NASA has been dedicated • CONFERENCE PUBLICATION. to the advancement of aeronautics and space Collected papers from scientific and science. The NASA scientific and technical technical conferences, symposia, seminars, information (STI) program plays a key part or other meetings sponsored or in helping NASA maintain this important co-sponsored by NASA. role. • SPECIAL PUBLICATION. Scientific, The NASA STI Program operates under the technical, or historical information from auspices of the Agency Chief Information NASA programs, projects, and missions, Officer. It collects, organizes, provides for often concerned with subjects having archiving, and disseminates NASA's STI. substantial public interest. The NASA STI Program provides access to the NASA Aeronautics and Space Database • TECHNICAL TRANSLATION. English- and its public interface, the NASA Technical language translations of foreign scientific Report Server, thus providing one of the and technical material pertinent to largest collection of aeronautical and space NASA's mission. science STI in the world. Results are Specialized services also include organizing published in both non-NASA channels and and publishing research results, distributing by NASA in the NASA STI Report Series, specialized research announcements and which includes the following report types: feeds, providing information desk and • TECHNICAL PUBLICATION. Reports of personal search support, and enabling data completed research or a major significant exchange services. -
For Improved Airplane Performance
BLENDED WINGLETS FORFOR IMPROVEDIMPROVED AIRPLANEAIRPLANE PERFORMANCEPERFORMANCE New blended winglets on the Boeing Business Jet and the 737-800 commercial airplane offer operational benefits to customers. Besides giving the airplanes a distinctive appear- ance, the winglets create more efficient flight characteristics in cruise and during takeoff and climbout, which translate into additional range with the same fuel and payload. ROBERT FAYE ROBERT LAPRETE MICHAEL WINTER TECHNICAL DIRECTOR ASSOCIATE TECHNICAL FELLOW PRINCIPAL ENGINEER BOEING BUSINESS JETS AERODYNAMICS TECHNOLOGY STATIC AEROELASTIC LOADS BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES TECHNOLOGY/PRODUCT DEVELOPMENT AERO 16 vertical height of the lifting system (i.e., increasing the length of the TE that sheds the vortices). The winglets increase the spread of the vortices along the TE, creating more lift at the wingtips (figs. 2 and 3). The result is a reduction in induced drag (fig. 4). The maximum benefit of the induced drag reduction depends on the spanwise lift distribution on the wing. Theoretically, for a planar wing, induced drag is opti- mized with an elliptical lift distribution that minimizes the change in vorticity along the span. For the same amount of structural material, nonplanar wingtip 737-800 TECHNICAL CHARACTERISTICS devices can achieve a similar induced drag benefit as a planar span increase; however, new Boeing airplane designs Passengers focus on minimizing induced drag with 3-class configuration Not applicable The 737-800 commercial airplane wingspan influenced by additional 2-class configuration 162 is one of four 737s introduced BBJ TECHNICAL CHARACTERISTICS The Boeing Business Jet design benefits. 1-class configuration 189 in the late 1990s for short- to (BBJ) was launched in 1996 On derivative airplanes, performance Cargo 1,555 ft3 (44 m3) medium-range commercial air- Passengers Not applicable as a joint venture between can be improved by using wingtip Boeing and General Electric. -
[4910-13-P] DEPARTMENT of TRANSPORTATION Federal
This document is scheduled to be published in the Federal Register on 05/13/2021 and available online at federalregister.gov/d/2021-10015, and on govinfo.gov [4910-13-P] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2021-0366; Project Identifier MCAI-2021-00080-T] RIN 2120-AA64 Airworthiness Directives; ATR – GIE Avions de Transport Régional Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 2020-23-13, which applies to all ATR – GIE Avions de Transport Régional Model ATR42-200, -300, and -320 airplanes. AD 2020-23-13 requires a one-time inspection for discrepancies of the wire bundles between the left- and right-hand angle of attack (AOA) probes and the crew alerting computer, and, depending on findings, applicable corrective actions. Since the FAA issued AD 2020-23-13, a wiring modification for the captain stick shaker has been developed, along with an update to the aircraft flight manual (AFM). This proposed AD would continue to require the actions in AD 2020-23-13. This proposed AD would also require, for certain airplanes, modifying the captain stick shaker wiring, and for all airplanes, revising the existing AFM and applicable corresponding operational procedures to incorporate procedures for the stick pusher/shaker, as specified in a European Union Aviation Safety Agency (EASA), which is proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by [INSERT DATE 45 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. -
CAP High Ground 18.03
The High Ground A Newsletter From Wyoming Wing Standards/Evaluation 15 March, 2018 Hot Topics Pilot Proficiency Profiles… The New Reality! With the implementation of CAPR 70-1 Flight Management, the Air Force came out with new requirements for documentation of training sorties. The AF now requires us to document what is planned, and what we actually accomplished during that sortie, per the Pilot Prof iciency Profile. We are required to accomplish all of the REQUIRED items listed in the PPP Checklist. We have to document each item and upload/note supporting documentation, or document why we did not accomplish the required item. Please review the preamble of the Pilot Proficiency Profiles (first page) and the specific Profile which you are planning on flying. Unfortunately, we can’t “just wing it” anymore. (Sigh) This ain’t my idea, this is from “On High”. Pilot Proficiency Profiles To review, the Pilot Proficiency Profiles, dated 01 January 2018, have changes. Best to print out a copy and keep it handy while operating under any one of these Profiles. And the Profiles are now to be documented in the “Profile Used” in WMIRS as P#, i.e. Profile number 1 would be entered as “P1”. Note that each Profile has a header which dictates the PIC qualifications to operate under that Profile. Read these before you attempt to fly the Profile. Now the BIG CHANGE is in the details of each Profile, what we are expected to do, and what we have to document for each Pilot Proficiency Profile sortie. Each PPP has in its description “Routine” and “Required” Items. -
2018 Undergraduate Team Aircraft Design Competition Hybrid-Electric
2017 – 2018 Undergraduate Team Aircraft Design Competition Hybrid-Electric General Aviation Aircraft (HEGAA) Presented by Federal University of Uberlândia Department of Aerospace Engineering Minas Gerais, Brazil 2017 – 2018 Undergraduate Team Aircraft Design Competition Hybrid-Electric General Aviation Aircraft (HEGAA) Presented by Federal University of Uberlândia Department of Aerospace Engineering Minas Gerais, Brazil Team Members AIAA Numbers Signatures Alexandre Acerra Gil 922668 Eduardo Pavoni Gamba 922678 Gabriel Araújo Hernández 922675 Guilherme Miquelim Caires 922581 Higor Luis Silva 922459 João Paulo Vieira 922563 Kimberlly Costa Carvalho 922564 Luiz Gustavo Santiago 922576 Pedro Brito 922566 Roberto Martins de Castro Neto 922571 Advisor: Dr. Thiago A. M. Guimarães - 498079 Table of Contents 1. Introduction .......................................................................................................................................................... 6 2. Design Requirements and Proposals .................................................................................................................... 7 3. Market Research ................................................................................................................................................... 9 4. Conceptual Design .............................................................................................................................................. 10 4.1. Initial Design Estimate ................................................................................................................................. -
Overview of Icing Research at NASA Glenn
Overview of Icing Research at NASA Glenn Eric Kreeger NASA Glenn Research Center Icing Branch 25 February, 2013 Glenn Research Center at Lewis Field Outline • The Icing Problem • Types of Ice • Icing Effects on Aircraft Performance • Icing Research Facilities • Icing Codes Glenn Research Center at Lewis Field 2 Aircraft Icing Ground Icing Ice build-up results in significant changes to the aerodynamics of the vehicle This degrades the performance and controllability of the aircraft In-Flight Icing Glenn Research Center at Lewis Field 3 3 Aircraft Icing During an in-flight encounter with icing conditions, ice can build up on all unprotected surfaces. Glenn Research Center at Lewis Field 4 Recent Commercial Aircraft Accidents • ATR-72: Roselawn, IN; October 1994 – 68 fatalities, hull loss – NTSB findings: probable cause of accident was aileron hinge moment reversal due to an ice ridge that formed aft of the protected areas • EMB-120: Monroe, MI; January 1997 – 29 fatalities, hull loss – NTSB findings: probable cause of accident was loss-of-control due to ice contaminated wing stall • EMB-120: West Palm Beach, FL; March 2001 – 0 fatalities, no hull loss, significant damage to wing control surfaces – NTSB findings: probable cause was loss-of-control due to increased stall speeds while operating in icing conditions (8K feet altitude loss prior to recovery) • Bombardier DHC-8-400: Clarence Center, NY; February 2009 – 50 fatalities, hull loss – NTSB findings: probable cause was captain’s inappropriate response to icing condition 5 Glenn Research