Vortex Generators: Band-Aids Or Magic?
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FCM Aircraft Operations That Generated Complaints July 2015
FCM Aircraft Operations that Generated Complaints July 2015 Complaints FCM FCM FCM Helicopter FCM Regarding Complaints Complaints Aircraft Types Nighttime FCM Submitted Submitted via Complaints Complaints Complaints Run-ups via Internet Phone Unknown 184 6 7 2 184 0 Beechcraft King Air 200 46 0 30 0 46 0 Raytheon Beechjet 400 15 0 9 0 15 0 Cessna Citation Jet 560XL 15 1 4 0 15 0 Beechcraft King Air 90 13 1 6 1 13 0 Cirrus SR-22 9 0 2 0 9 0 Cessna Skyhawk 172 8 0 0 0 8 0 Cessna Citation Jet 525 7 0 3 0 7 0 Beechcraft King Air 350 6 0 2 0 6 0 Learjet 45 6 0 1 0 6 0 Cessna 310 Twin 5 0 0 0 5 0 Cessna Skywagon 185 5 0 0 0 4 1 Piper Malibu Meridian 4 0 0 0 4 0 Hawker 125 Jet 4 0 1 0 4 0 Piper Malibu 4 0 1 0 4 0 Pilatus PC-12 4 0 1 0 4 0 Cessna Citation Jet 560 4 0 1 0 4 0 Cessna 340 Twin 3 0 0 0 3 0 Beechcraft King Air 300 3 0 2 0 3 0 Cessna Corsair 425 2 0 0 0 2 0 Cessna 206 2 0 0 0 2 0 Experimental 2 0 1 0 2 0 Cessna Citation Jet 750 2 0 2 0 2 0 Socata TBM 700 2 0 0 0 2 0 Cessna Golden Eagle 421 2 0 0 0 2 0 Cessna Centurion 210 2 0 0 0 2 0 Cessna Skylane 182 2 0 0 0 2 0 Piper Cherokee 2 0 0 0 2 0 T-6 TEXAN 2 0 0 0 2 0 Rockwell Turbo Commander 900 2 0 0 0 2 0 Cessna Citation Mustang 2 0 0 0 2 0 Boeing 737-900 1 0 1 0 1 0 Report Generated: 09/30/2015 15:36 Page 1 Complaints FCM FCM FCM Helicopter FCM Regarding Complaints Complaints Aircraft Types Nighttime FCM Submitted Submitted via Complaints Complaints Complaints Run-ups via Internet Phone Piper Navajo Twin 1 0 0 0 1 0 Mitsubishi MU-2 1 0 0 0 1 0 Beechcraft Debonair/Bonanza 1 0 1 0 1 0 -
Cessna 340 Page 1 of 14
Cessna 340 Page 1 of 14 Volume 34 • Number 2 • February 2004 Cessna 340 A fast, pressurized cabin-class twin that’s an excellent step-up from a Avionics Report high performance single. Used Aircraft Guide Maintenance Matters Accessories Although airplanes are often sold as Misc. business and transportation tools, the reality of ownership falls short of the ideal. They either lack the range, the carrying capacity or the ability to deal with real-world weather, thus an airline or a charter outfit gets the call. Still, there are plenty of pilot/businessmen who couldn’t function without an airplane. These owners typically start with single- The Cessna 340 is a standout thanks to engine airplanes and quickly outgrow payload/fuel flexibility and near 200-knot cruise them for the reasons stated above. A speeds. Pressurization is an added plus. serious business airplane needs a decent cabin, credible speed and the ability to hack it when there’s ice or thunder in the forecast. Pressurization is nice since the clients don’t want to spend several hours with a plastic hose stuck up their noses. Enter the Cessna 340. Owners looking to step-up from a high-performance single will inevitably make a pass or two through the 340 classified section. And well they should. Although not without its shortcomings—most notably certain loading limitations and an overly complex fuel system—the 340 is nevertheless an impressive, flexible and capable airplane that meets the business mission well and can do double duty as a family airplane. Model History The 340 owes its existence to the boom days of general aviation during the late 1960s and early 1970s. -
Aerodynamic Analysis and Design of a Twin Engine Commuter Aircraft
28TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AERODYNAMIC ANALYSIS AND DESIGN OF A TWIN ENGINE COMMUTER AIRCRAFT Fabrizio Nicolosi*, Pierluigi Della Vecchia*, Salvatore Corcione* *Department of Aerospace Engineering - University of Naples Federico II [email protected]; [email protected], [email protected] Keywords: Aircraft Design, Commuter Aircraft, Aerodynamic Analysis Abstract 1. Introduction The present paper deals with the preliminary design of a general aviation Commuter 11 seat Many in the industry had anticipated 2011 to be aircraft. The Commuter aircraft market is today the year when the General Aviation characterized by very few new models and the manufacturing industry would begin to recover. majority of aircraft in operation belonging to However, the demand for business airplanes and this category are older than 35 years. Tecnam services, especially in the established markets of Aircraft Industries and the Department of Europe and North America, remained soft and Aerospace Engineering (DIAS) of the University customer confidence in making purchase of Naples "Federico II" are deeply involved in decision in these regions remained weak. This the design of a new commuter aircraft that inactivity, nonetheless, was offset in part by should be introduced in this market with very demand from the emerging markets of China good opportunities of success. This paper aims and Russia. While a full resurgence did not take to provide some guidelines on the conception of place in 2011, the year finished with signs of a new twin-engine commuter aircraft with recovery and reason of optimism. GAMA eleven passengers. Aircraft configuration and (General Aviation Manufacturer Association) cabin layouts choices are shown, also compared 2011 Statistical Databook & Industry Outlook to the main competitors. -
Program Monitors
ALLEVIATION OF FUSELAGE FORM DRAG USING VORTEX FLOWS DOE/CE/15277--T1 Final Report on work performed under TI89 004158 U.S. Department of Energy Grant DE-FG01-86CE15277 15 September 1987 DISCLAIMER DR. A. Wortman This report was prepared as an account of work sponsored by an agency of the United States Government. Neither the United States Government nor any agency thereof, nor any of their employees, makes any warranty, express or implied, or assumes any legal liability or responsi- bility for the accuracy, completeness. or usefulness of any information, apparatus, product, or . process disclosed, or represents that its use would not infringe privately owned rights. Refer- ence herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise does not necessarily constitute or imply its endorsement, recom- mendation, or favoring by the United States Government or any agency thereof. The views and opinions of authors expressed herein do not necessarily state or reflect those of the United States Government or any agency thereof. ISTAR INC. 406 Aka Avenue Santa Monica, CA 90402 (213) 394-7332 PROGRAM MONITORS: _* T. Levinson D. Mello DISCLAIMER Portions of this document may be illegible electronic image products. Images are produced from the best available original document. FOREWORD AND ACKNOWLEDGEMENTS The concept of employing discrete large vortices, to develop favorable cross-flow and to energize the boundary layer in the aft regions of transport aircraft fuselages, was first proposed by the author almost 10 years ago as an apparently original approach to the reduction of fuselage drag. A series of feasibility demonstration proposals, starting with the 1981 USAF DESAT program was submitted to various U.S. -
NASA Contractor Report 165749
NASA Contractor Report 165749 (IASA-Ci!- 165749) SUUSQNli PIfCti- UP Etb 1-30137 ALLEVIATICN ON A 7U CEG DELTA hXh2 (Viqyau Rl~ssdrch Associates, Inc,) LO p HC A02/64F 801 CSCL 1)1C (iluclas Gj/OU &7267 SUBSONIC PITCH-UP ALLEVIATION ON A 74 DEG. DELTA WING Dhanvada W. Raa9iI: and Thomas D, Johnson, Jr. VIGYAN RESEARCH ASSOCIATES, INC . 28 Research Drive Hampton, Virgini a 23666 Contract NAS1-16259 July 1981 National Aeronautis and Space Administration Langley Reamrch Center Hampton,Virginia 23665 SUBSONIC PITCH-UP ALLEVIATION ON A 74-REG, DELTA WING Rhanvada M, Rao Vigyan Research Associates, Inc. and Thomas 0. Johnson, Jr. Kentron International, Inc. tiampton Technical Center SUMMARY Fixed leading-edge devices were investigated on a 74-deg. delta wing model for alleviating the low speed pitch-up and longi- tudinal instability following the onset of leading edge separation. Wind tunnel tests showed Pylon Vortex Generators to be highly effective, compared to the leading-edge fences and slots also investigated. The best Pylon Vortex Generator arrangement raised the pitch-up angle of attack from 8 deg. on the basic wing to 28 deg. , with negl igi bl e subsonic drag penalty . INTRODUCTION A review of research on the low-speed aerodynamics of highly swept wing configurations representative of supersonic-crui se aircraft designs indicates that a problem commonly observed is the so-cal led 'pitch-up' , i.e., a discontinuous nose-up change in the pitching moment uith increasing angle of attack. Pitch-up is caused by the onset of separation in the wing tip regions while the flow inboard is still attached, and has been of sufficient concern to dictate a comproniize in the optimum supersonic-crui se planform shape in order to have accept- able low-speed flight characteristics. -
The Power for Flight: NASA's Contributions To
The Power Power The forFlight NASA’s Contributions to Aircraft Propulsion for for Flight Jeremy R. Kinney ThePower for NASA’s Contributions to Aircraft Propulsion Flight Jeremy R. Kinney Library of Congress Cataloging-in-Publication Data Names: Kinney, Jeremy R., author. Title: The power for flight : NASA’s contributions to aircraft propulsion / Jeremy R. Kinney. Description: Washington, DC : National Aeronautics and Space Administration, [2017] | Includes bibliographical references and index. Identifiers: LCCN 2017027182 (print) | LCCN 2017028761 (ebook) | ISBN 9781626830387 (Epub) | ISBN 9781626830370 (hardcover) ) | ISBN 9781626830394 (softcover) Subjects: LCSH: United States. National Aeronautics and Space Administration– Research–History. | Airplanes–Jet propulsion–Research–United States– History. | Airplanes–Motors–Research–United States–History. Classification: LCC TL521.312 (ebook) | LCC TL521.312 .K47 2017 (print) | DDC 629.134/35072073–dc23 LC record available at https://lccn.loc.gov/2017027182 Copyright © 2017 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks National Aeronautics and Space Administration Washington, DC Table of Contents Dedication v Acknowledgments vi Foreword vii Chapter 1: The NACA and Aircraft Propulsion, 1915–1958.................................1 Chapter 2: NASA Gets to Work, 1958–1975 ..................................................... 49 Chapter 3: The Shift Toward Commercial Aviation, 1966–1975 ...................... 73 Chapter 4: The Quest for Propulsive Efficiency, 1976–1989 ......................... 103 Chapter 5: Propulsion Control Enters the Computer Era, 1976–1998 ........... 139 Chapter 6: Transiting to a New Century, 1990–2008 .................................... -
Aircraft Library
Interagency Aviation Training Aircraft Library Disclaimer: The information provided in the Aircraft Library is intended to provide basic information for mission planning purposes and should NOT be used for flight planning. Due to variances in Make and Model, along with aircraft configuration and performance variability, it is necessary acquire the specific technical information for an aircraft from the operator when planning a flight. Revised: June 2021 Interagency Aviation Training—Aircraft Library This document includes information on Fixed-Wing aircraft (small, large, air tankers) and Rotor-Wing aircraft/Helicopters (Type 1, 2, 3) to assist in aviation mission planning. Click on any Make/Model listed in the different categories to view information about that aircraft. Fixed-Wing Aircraft - SMALL Make /Model High Low Single Multi Fleet Vendor Passenger Wing Wing engine engine seats Aero Commander XX XX XX 5 500 / 680 FL Aero Commander XX XX XX 7 680V / 690 American Champion X XX XX 1 8GCBC Scout American Rockwell XX XX 0 OV-10 Bronco Aviat A1 Husky XX XX X XX 1 Beechcraft A36/A36TC XX XX XX 6 B36TC Bonanza Beechcraft C99 XX XX XX 19 Beechcraft XX XX XX 7 90/100 King Air Beechcraft 200 XX XX XX XX 7 Super King Air Britten-Norman X X X 9 BN-2 Islander Cessna 172 XX XX XX 3 Skyhawk Cessna 180 XX XX XX 3 Skywagon Cessna 182 XX XX XX XX 3 Skylane Cessna 185 XX XX XX XX 4 Skywagon Cessna 205/206 XX XX XX XX 5 Stationair Cessna 207 Skywagon/ XX XX XX 6 Stationair Cessna/Texron XX XX XX 7 - 10 208 Caravan Cessna 210 X X x 5 Centurion Fixed-Wing Aircraft - SMALL—cont’d. -
Portola Valley Aircraft Noise Monitoring
Portola Valley Aircraft Noise Monitoring Prepared by San Francisco International Airport Aircraft Noise Abatement Office Technical Report #012017-978 January 2017 San Francisco International Airport Portola Valley Aircraft Noise Monitoring Report Page | 2 Table of Contents Executive Summary ................................................................................................................................ 3 Community and SFO Operations............................................................................................................ 3 Equipment ............................................................................................................................................... 3 Aircraft Noise Analysis........................................................................................................................... 4 Aircraft Operations ................................................................................................................................. 6 Track Density.......................................................................................................................................... 8 Noise Reporters....................................................................................................................................... 9 Conclusion ............................................................................................................................................ 10 Figure 1 ................................................................................................................................................ -
Subsonic and Transonic Flutter and Flow Investigations of the T-Tail of a Large Multijet Cargo Airplane
1 -1.0 8% NASA TECHNICAL NOTE NASA TN D-4316 -c - SUBSONIC AND TRANSONIC FLUTTER I AND FLOW INVESTIGATIONS OF THE T-TAIL OF A LARGE MULTIJET CARGO AIRPLANE Langley Reseurch Center Ldngley Station, Humpton, Vu. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. FEBRUARY 1968 i i 1 t i r SUBSONIC AND TRANSONIC FLUTTER AND FLOW INVESTIGATIONS OF THE T-TAIL OF A LARGE MULTIJET CARGO AIRPLANE By Maynard C. Sandford, Charles L. Ruhlin, and E. Carson Yates, Jr. Langley Research Center Langley Station, Hampton, Va. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federol Scientific and Technical Information Springfield, Virginia 22151 - CFSTl price $3.00 SUBSONIC AND TRANSONIC FLUTTER AND FLOW INVESTIGATIONS OF THE T-TAIL OF A LARGE MULTIJET CARGO AIRPLANE By Maynard C. Sandford, Charles L. Ruhlin, and E. Carson Yates, Jr. Langley Research Center . - SUMMARY Flutter and flow studies of the T-tail of a large multijet cargo airplane have been conducted in the Langley transonic dynamics tunnel at Mach numbers up to 1.08. The tail and aft fuselage of the model employed were geometrically, dynamically, and elastically scaled, whereas only the mass and stiffness characteristics of the forward fuselage, wings, and nacelles were simulated. The flutter studies included variations in fin-spar stiffness, stabilizer-pitch-actuator stiffness, rotational stiffnesses of elevators and rudder, as well as small variations in stabilizer incidence angle. Flow studies were initiated to reduce areas of separated flow in the vicinity of the fin-stabilizer juncture and included the use of vortex generators and fences, as well as modifications to the bullet-fairing shape. -
Measurements on a Vertical Tail with Vane Vortex Generators
Deutscher Luft- und Raumfahrtkongress 2017 DocumentID: 450111 MEASUREMENTS ON A VERTICAL TAIL WITH VANE VORTEX GENERATORS V. M. Singh, P. Scholz Institute of Fluid Mechanics, TU Braunschweig, Braunschweig, D-38108, Germany Abstract This contribution presents the investigation of a passive method of boundary layer separation control on a swept and tapered vertical tail plane with a deflected rudder. The primary objective was the increase of the total side force coefficient. For that, an array of co-rotating vane vortex generators was placed close to the rudder knee to maintain an attached flow, which consequently led to an increase of the side force coefficient. The second objective was a parameter sensitivity study, which covered a large scope of different vane vortex generator parameters: size, shape, angle of attack, position and separation. Experiments were performed in a low-speed wind tunnel. The results show the ability of vane vortex generators to increase the side force coefficient for a large range of yaw angles. The maximal increase of side force coefficient was about 14 %. However, the influence of the vane vortex generators on the stall of the vertical tail plane was limited. Nevertheless, in a range of yaw angles, an increase of the lift to drag ratio of about 30 % was obtained. The effect was found to be sensitive for the angle of attack, chordwise position, size and geometry of a vortex generator, whereas parameters such as spanwise extension and separation were less sensitive to parameter change. NOMENCLATURE maneuvers. Although the main part of the mission profile is usually the cruise flight, it is not the critical design point for AoA Angle of attack of a VVG a VTP. -
July2020.Pdf
The JULY 2020 TWIN CESSNA Flyer FEATURING: THORNTON 310 - Youtube “310 PILOT” INTERIOR RENOVATIONS - PT. 1 FLY LIKE A PRO - TEN TIPS READERS WRITE SupportingSupporting Twin Twin Cessna Cessna Owners Owners Worldwide Worldwide since since 1988 1988 The AdvantageBetter Parts • Better Engines Cessna • Beechcraft • Cirrus Cessna: T206 TSIO-520-M P210 TSIO-520-P, -AF Beechcraft Bonanza: T210 TSIO-520-R 414A TSIO-520-NB 421B GTSIO-520-H F33, A36 IO-520-BB 310R IO-520-MB A36 IO-550-B T310 TSIO-520-BB, EB 421C GTSIO-520-L, -N Stock & Turbo-Normalized T310 TSIO-520-NB A36TC TSIO-520-UB 320 TSIO-520-EB, -NB Beechcraft Baron: B36TC TSIO-520-UB 335 TSIO-520-EB 58 IO-520-CB 340/A TSIO-520-NB 58 IO-550-C Cirrus: 402 B/C TSIO-520-EB/-VB 58 P/ TC TSIO-520-LB SR22 IO-550-N 404 GTSIO-520-M 58 P/ TC TSIO-520-WB Stock & Turbo-Normalized 414 TSIO-520-NB Critical Gears In Stock! NEW Crankcases for: RAM PMA-New gears are back in stock. If you are overhauling an • Beechcraft Baron • Cessna T310 engine (of having someone overhaul yours), contact RAM to get (58, 58P/TC) • Cessna 320 the best parts for your engine at a fraction of the OEM price! • Beechcraft Bonanza • Cessna 335 Large Cam Gear (C33A, E33A/C, F33, S35, • Cessna 340/A Replaces OEM #: 656818, V35/A/B, A36, A36TC, B36TC) • Cessna 402B/C 656031, 655516, 631845 • Cessna 310R • Cessna 414 RAM PN: 2078-1 • Cessna 414A Dealer Price: $850 • Cirrus SR22 Cost-Effective relief from Continental Critical Service Bulletin CSB05-8D Large Crankshaft Gear Replaces OEM #: 656991, 632893 RAM PN: 2074-1 Dealer Price: $896 Small Crankshaft Gear Replaces OEM #: 657175, 656989, 653652, 632892, 629301 RAM PN: 2075-11 AIRCRAFT PARTS STORE Dealer Price: $395 • SINCE 1976 • RAM AIRCRAFT, LP • SINCE 1976 • ©2020 RAM Aircraft, LP TTCF052720 The SM TWIN CESSNA Flyer FEATURES sm The Twin Cessna Flyer Wolter, owner of Air Mod Inc., one of the P.O. -
Cessna 120 140 140A 150 170 170A 170B 172 175 180 182 185 190
Cessna 120 140 140A 150 170 170A 170B 172 175 180 182 185 190 195 6 Cessna Manuals Cessna Model Section / Index Manuals (continued) Owners Manuals (continued) Model/Section Page No. Description Part No. Description Part No. Manuals ........................................................ 7, 8 188 AG Aircraft Series, 1976-1984 ..... P694-12 150 Owners Manual, 1959-1960 ......... P187-13 120-140 Controls ............................................. 7 190-195 Parts Catalog, 1948-1953 .......P112-12 150A Owners Manual, 1961 ................ P220-13 120-140 Engine ................................................ 8 150B Owners Manual, 1962 ................D123-13 120-140 Landing Gear ..................................... 8 150C Owners Manual, 1963 ................D156-13 120-140 Fuselage ......................................... 8, 9 150D Owners Manual, 1964 ................D208-13 120-140 Tail Surfaces .................................... 10 150E Owners Manual, 1965 ................D251-13 120-140 Wings ............................................... 10 Service Manuals 150F Owners Manual, 1966 ................D326-13 150 Controls, Engine ..................................... 12 150G Owners Manual, 1967 ............ D397-1-13 150 Landing Gear, Wings, Miscellaneous ..... 12 150H Owners Manual, 1968 ................D518-13 170 Parts ........................................................ 13 150J Owners Manual, 1969 .................D624-13 172-175 Engine .............................................. 13 150K Owners Manual, 1970 ................D727-13