Nigel Charles Looks at the Europa's Dramatically Changed, Graceful Performance with Motor-Glider Wings
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Alone Across the Atlantic
® 8 - DECEMBER 2013 www.kitplanes.com RV Atlantic Across in an in Swage Fittings Swage Secure? Cables Your Are the Adventure FT A Alone T REVIEW H ’S GUIDE SHOP R E H Easy Fiberglass Prep Aerodynamic Bookworm Tire Changing 101 T Soaring on Homemade Wings 2014 BUYER’S GUIDE2014 ISSUE! N • • • I HP-24 FLIG HP-24 BUYE Over 350 Planes Listed! Planes 350 Over 2014 KIT AIRCR KITPLANES DECEMBER 2013 Kit Buyer’s Guide • Transatlantic RV-8 • HP-24 Sailplane • Design to Fit • Swagelocks • Dawn Patrol • Testing to DO-160 • Home Shop Machines BELVOIR PUBLICATIONS Enjoy the Freedom of Homebuilt Aircraft Weather the Storm with SkyView’s IFR Capabilities Redundant flight instruments that automatically cross-check each other • ADS-B traffic and weather in-flight • SkyView network modules that detect wiring faults without losing capability • Li-Ion backup batteries that keep your SkyView system up when the power goes down • Autopilot with fully coupled ILS and GPS WAAS/LPV approaches. SkyView should already be your IFR platform of choice. But if that’s not enough, SkyView 7.0 introduces geo-referenced instrument approach charts, airport diagrams, and the best mapping software we’ve ever built. Go Fly! www.DynonAvionics.com 425-402-0433 [email protected] Seattle,Washington December 2013 | Volume 30, Number 12 Annual Buyer’s Guide, Part 1 26 2014 KIT AIRCRAFT BUYER’S GUIDE: The state of the kit world is sound. By Paul Dye and Mark Schrimmer. 38 KIT AIRCRAFT QUICK REFERENCE: A brief overview of available kit aircraft for 2014. Compiled by Richard VanderMeulen and Omar Filipovic. -
Effects of Gurney Flap on Supercritical and Natural Laminar Flow Transonic Aerofoil Performance
Effects of Gurney Flap on Supercritical and Natural Laminar Flow Transonic Aerofoil Performance Ho Chun Raybin Yu March 2015 MPhil Thesis Department of Mechanical Engineering The University of Sheffield Project Supervisor: Prof N. Qin Thesis submitted to the University of Sheffield in partial fulfilment of the requirements for the degree of Master of Philosophy Abstract The aerodynamic effect of a novel combination of a Gurney flap and shockbump on RAE2822 supercritical aerofoil and RAE5243 Natural Laminar Flow (NLF) aerofoil is investigated by solving the two-dimensional steady Reynolds-averaged Navier-Stokes (RANS) equation. The shockbump geometry is predetermined and pre-optimised on a specific designed condition. This study investigated Gurney flap height range from 0.1% to 0.7% aerofoil chord length. The drag benefits of camber modification against a retrofit Gurney flap was also investigated. The results indicate that a Gurney flap has the ability to move shock downstream on both types of aerofoil. A significant lift-to-drag improvement is shown on the RAE2822, however, no improvement is illustrated on the RAE5243 NLF. The results suggest that a Gurney flap may lead to drag reduction in high lift regions, thus, increasing the lift-to-drag ratio before stall. Page 2 Dedication I dedicate this thesis to my beloved grandmother Sandy Yip who passed away during the course of my research, thank you so much for the support, I love you grandma. This difficult journey would not have completed without the deep understanding, support, motivation, encouragement and unconditional love from my beloved parents Maggie and James and my brother Billy. -
SBM20-322 2015 June 23 Temporary
MOONEY INTERNATIONAL CORPORATION SERVICE BULLETIN 165 Al Mooney Road North Kerrville, Texas 78028 SERVICE BULLETIN M20-322 Date: June 23, 2015 THIS BULLETIN IS FAA APPROVED FOR ENGINEERING DESIGN SUBJECT: Temporary Replacement of Icing System Stall Strip MODELS/ SN Mooney Aircraft with Known Icing System Installed AFFECTED: TIME OF AS SOON AS PRACTICABLE COMPLIANCE: INTRODUCTION: For instances involving missing icing system stall strips, airplanes are grounded. To remedy this situation, a temporary non-icing system stall strip can be installed in place of the icing stall strip to allow the aircraft to operate as a “Not Certified for Flight in Known Icing Conditions” aircraft until the icing strip can be installed. This Service Bulletin is to provide instructions for installing the temporary stall strip. The attached compliance card needs to be filled out and returned to Mooney International Corporation upon completion of this Service Bulletin M20-322. WARNING: Flight into known icing conditions and the use of the aircraft’s icing system is prohibited until the permanent icing system stall strip can be installed. This Service Bulletin only allows for a temporary non-icing stall strip to be installed for temporary flight until the permanent icing stall strip can be obtained. INSTRUCTIONS: Read entire procedures before beginning work. INSTALLING TEMPORARY STALL STRIP: 1.1. Disable and secure circuit breaker to prevent accidental operation of icing system. 1.2. Remove all old sealant and thoroughly clean the porous surface of the wing where the temporary stall strip is to be installed. Acceptable cleaning solvents are listed below. NOTE: The primary factor affecting the adhesion of the stall strip is absolute cleanliness of the porous panel. -
General Aviation Aircraft Design
Contents 1. The Aircraft Design Process 3.2 Constraint Analysis 57 3.2.1 General Methodology 58 1.1 Introduction 2 3.2.2 Introduction of Stall Speed Limits into 1.1.1 The Content of this Chapter 5 the Constraint Diagram 65 1.1.2 Important Elements of a New Aircraft 3.3 Introduction to Trade Studies 66 Design 5 3.3.1 Step-by-step: Stall Speed e Cruise Speed 1.2 General Process of Aircraft Design 11 Carpet Plot 67 1.2.1 Common Description of the Design Process 11 3.3.2 Design of Experiments 69 1.2.2 Important Regulatory Concepts 13 3.3.3 Cost Functions 72 1.3 Aircraft Design Algorithm 15 Exercises 74 1.3.1 Conceptual Design Algorithm for a GA Variables 75 Aircraft 16 1.3.2 Implementation of the Conceptual 4. Aircraft Conceptual Layout Design Algorithm 16 1.4 Elements of Project Engineering 19 4.1 Introduction 77 1.4.1 Gantt Diagrams 19 4.1.1 The Content of this Chapter 78 1.4.2 Fishbone Diagram for Preliminary 4.1.2 Requirements, Mission, and Applicable Regulations 78 Airplane Design 19 4.1.3 Past and Present Directions in Aircraft Design 79 1.4.3 Managing Compliance with Project 4.1.4 Aircraft Component Recognition 79 Requirements 21 4.2 The Fundamentals of the Configuration Layout 82 1.4.4 Project Plan and Task Management 21 4.2.1 Vertical Wing Location 82 1.4.5 Quality Function Deployment and a House 4.2.2 Wing Configuration 86 of Quality 21 4.2.3 Wing Dihedral 86 1.5 Presenting the Design Project 27 4.2.4 Wing Structural Configuration 87 Variables 32 4.2.5 Cabin Configurations 88 References 32 4.2.6 Propeller Configuration 89 4.2.7 Engine Placement 89 2. -
Pilot´S Operating Handbook
PILOT´S OPERATING HANDBOOK Document Number: AS-POH-10-487 Date of Issue: 07. 05. 2019 Aircraft Model: WT9 Dynamic LSA / Club Aircraft Serial Number: DY-487/2013 LSA Aircraft Registration Number: F-HVXC THIS HANDBOOK INCLUDES THE INFORMATION REQUIRED TO BE FURNISHED TO THE PILOT BY REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY THE AIRCRAFT MANUFACTURER – AEROSPOOL, SPOL. S R. O. PAGES MARKED AS “EASA APPROVED” ARE APPROVED BY EUROPEAN AVIATION SAFETY AGENCY. THIS AIRCRAFT MUST BE OPERATED IN COMPLIANCE WITH THE INFORMATION AND LIMITATIONS STATED IN THIS MANUAL. This page is left blank intentionally RECORD OF REVISIONS Any revision of the present manual, except actual weight data, must be recorded in the following table, and in the case of approved chapters, endorsed by the responsible airworthiness authority. The new or amended text in the revised pages will be indicated by a black vertical line in the page margin, and the revision will be shown on the bottom side of the page. Revision Date Description of Revision Approved by Initial issue 07. 05. 2019 New issue. Initial issue Page A This page is left blank intentionally Page B Initial issue LIST OF EFFECTIVE PAGES Chapter Page Status Chapter Page Status Title page Initial issue 3 3-1 Initial issue Page Initial issue EASA Approved 3-2 Initial issue Page A Initial issue EASA Approved 3-3 Initial issue Page B Initial issue EASA Approved 3-4 Initial issue Page C Initial issue EASA Approved 3-5 Initial issue Page D Initial issue EASA Approved 3-6 Initial issue Page E Initial issue EASA -
Unusual Attitudes and the Aerodynamics of Maneuvering Flight Author’S Note to Flightlab Students
Unusual Attitudes and the Aerodynamics of Maneuvering Flight Author’s Note to Flightlab Students The collection of documents assembled here, under the general title “Unusual Attitudes and the Aerodynamics of Maneuvering Flight,” covers a lot of ground. That’s because unusual-attitude training is the perfect occasion for aerodynamics training, and in turn depends on aerodynamics training for success. I don’t expect a pilot new to the subject to absorb everything here in one gulp. That’s not necessary; in fact, it would be beyond the call of duty for most—aspiring test pilots aside. But do give the contents a quick initial pass, if only to get the measure of what’s available and how it’s organized. Your flights will be more productive if you know where to go in the texts for additional background. Before we fly together, I suggest that you read the section called “Axes and Derivatives.” This will introduce you to the concept of the velocity vector and to the basic aircraft response modes. If you pick up a head of steam, go on to read “Two-Dimensional Aerodynamics.” This is mostly about how pressure patterns form over the surface of a wing during the generation of lift, and begins to suggest how changes in those patterns, visible to us through our wing tufts, affect control. If you catch any typos, or statements that you think are either unclear or simply preposterous, please let me know. Thanks. Bill Crawford ii Bill Crawford: WWW.FLIGHTLAB.NET Unusual Attitudes and the Aerodynamics of Maneuvering Flight © Flight Emergency & Advanced Maneuvers Training, Inc. -
Safe Flight Aoa Manual
Page 3 of 28 Sym A . Dwg. 56201-2 . PROPRIETARY NOTICE This document contains proprietary information and covers equipment in which Safe Flight has proprietary rights. No data contained herein may be duplicated, used, or disclosed, in whole or in part, for any purpose, without the express written permission of Safe Flight Instrument Corporation. Safe Flight Instrument Corporation expressly reserves all rights, including all rights of patent and copyright protection. © SAFE FLIGHT INSTRUMENT CORPORATION 2016 Page 4 of 28 Sym B . Dwg. 56201-2 . TABLE OF CONTENTS Para. Description Page None Title Page ...................................................................................................................... 1 None Revision Notice ............................................................................................................. 2 None Proprietary Notice ......................................................................................................... 3 None Table of Contents .......................................................................................................... 4 1.0 System Description ....................................................................................................... 5 1.1 SCc................................................................................................................................ 5 1.2 System Components ..................................................................................................... 5 1.3 Theory of Operation ..................................................................................................... -
The Addition of Vortex Generators for STOL Performance and Or for Meeting the Light Sport Aircraft Rules ______
__________________________________________________________________________ The Addition of Vortex Generators for STOL performance and or for Meeting the Light Sport Aircraft Rules ___________________________________________________________________________ This modification allows the Europa XS or Classic aircraft to operate with a greater stall margin and better low speed characteristics. For those owners operating out of very short runways or tight landing patterns requiring steep approach paths or slow speed maneuvering the addition of vortex generators (VGs) will improve safety margins. General Background: Aerodynamically, the Europa wing is capable of generating a 1.7 Cl or Coefficient of lift. This is used as a benchmark for aerodynamicists to determine stall speed. For the Europa XS this places the stall at approximately 49 Knots for the XS and 53 for the Classic aircraft (1300 lb gross weight for the Classic and 1370 for the XS). The differences between the stall speeds are due to the slight differences in wing area, gross weight and shape. VGs are small vertical fins attached at an angle to the airstream to the wing just aft of the leading edge of the upper surface of the airfoil. These VGs generate tiny vortices which thicken and add energy to the boundary layer allowing the wing to achieve a higher stalling angle of attack and thereby more lift, better aileron control and a lower stall speed. The positioning, spacing and angle of the VGs on the wing is critical for proper handling characteristics, pre-stall warning and stall speed reduction. This modification will provide guidance on the spacing and positioning necessary to achieve optimum handling characteristics to meet the builder’s desires. -
Falco Builders Letter
Falco Builders Letter A Visit with Frati If anybody ever suggests you go visit Frati “in Milan,” as Alfred Scott did when he heard I was going to be in Italy writing about the Piaggio Avanti turboprop, here’s my suggestion: get Alfred to pay the cabfare. If you can’t do that, buy a car. A small Fiat will do, and it’ll prob- ably be cheaper than a cab. I leapt off the train from Genoa at Milan’s central station and plunged straight into a waiting taxi. “Via Trieste Vente-Quat- tro,” I said in my best non-Italian, and about $15 later, that’s exactly where he took me—24 Via Trieste. Quiet urban residential street... relatively upscale... odd place for an airplane factory.... Actually, there was no number 24. We found a phone booth, and my cabbie Jim and Gail Martin's Falco is the 17th Sequoia Falco to fly. was nice enough to tackle the Italian telephone system on my behalf. He First Flight: Around the Falco called Frati’s number, and I knew I was in trouble when I saw him perform the Jim and Gail Martin Patch classic application of heel of hand smartly Jim and Gail Martin’s Falco flew for Luciano Nustrini came to Oshkosh as to forehead, as though trying to jar loose a the first time on August 13th in But- planned, but not via Europe as he had subdural hematoma: the Via Trieste that ler, Pennsylvania, making it the 17th intended. There was a change in plans, I wanted, it turned out—a street that ap- Sequoia Falco to fly. -
Rotor Blade Computations with 3D Vortex Generators
Risø-R-1486(EN) KNOW-BLADE Task-3.3 report; Rotor Blade Computations with 3D Vortex Generators Jeppe Johansen, Niels N. Sørensen, Mads Reck, Martin O.L.Hansen, Arne Stuermer, Jan Ramboer, Charles Hirsch,John Ekaterinaris, Spyros Voutsinas and Yannis Perivolaris Risø National Laboratory Roskilde Denmark January 2005 Author: Jeppe Johansen, Niels N. Sørensen, Mads Reck, Martin Risø-R-1486(EN) O.L.Hansen, Arne Stuermer, Jan Ramboer, Charles Hirsch,John January 2005 Ekaterinaris, Spyros Voutsinas and Yannis Perivolaris Title: KNOW-BLADE Task-3.3 report; Rotor Blade Computations with 3D Vortex Generators Abstract (max. 2000 char.): ISSN 0106-2840 The present report describes the work done in work package WP3.3: ISBN 87-550-3386-5 Aerodynamic Accessories in 3D in the EC project KNOW-BLADE. Vortex generators (VGs) are modelled in 3D Navier-Stokes solvers and applied on the flow around an airfoil and a wind turbine blade. Three test cases have been investigated. They are: − A non-rotating airfoil section with VGs − A rotating airfoil section with VGs − A non-rotating wind turbine blade with VGs Contract no.: ENK6-CT-2001-00503 The airfoil section was the FFA-W3-241 airfoil, which has been measured in the VELUX wind tunnel with and without VGs placed at different chordwise positions. Three of the partners have modelled the airfoil section Group's own reg. no.: 1110033-00 as a thin airfoil section with symmetry boundary conditions in the spanwise direction to simulate an array of VGs. The wind turbine blade is the LM19.1 blade equipped with one pair of VGs Sponsorship: placed at radius = 8.5 m. -
CFD Study of a NACA 63-415 Aerofoil Fitted with Stall Strips
Ris0-R-137O(EN) CFD Study of a NACA 63-415 Aerofoil Fitted with Stall Strips Frederik Zahle, Niels N. S0rensen, Jeppe Johansen Ris0 National Laboratory, Roskilde September 2002 Abstract The present work describes a thorough investigation of 2D computa tions of the flow around a NACA 63-415 aerofoil fitted with stall strips (SS). A mesh study as well as a time step study is carried out and all computations are compared with experiments. Two different SS, 5mm and 7mm are investigated at several positions. Furthermore the influence of laminar to turbulent transition and the effect of a rounded SS were tested. There is not sufficient agreement between the experimental results and the simulations to draw any conclusions of optimum position and geometry of the SS. The 7mm SS’s placed at P00 and P-02 has the greatest effect on the max lift followed by SS P02. The 5mm SS’s does, as in the experiment, not change the lift curve noticeably. Even though this investigation does not conclusively suc ceed in verifying the experimental results with CFD, many useful conclusions can be drawn from the results. It is observed in the experiment that the vertical force fluctuates at higher an gles of attack. This indicates that small bubbles are being shed off the profile causing the force to vary. This property is observed when transition is included in the model and also when the tip of the SS is rounded. From this result it could be concluded that the level of turbulence produced on the tip of the SS is very important for the development of the flow downstream. -
Europa Classic Trigear Conversion to an Experimental Amateur Built Light
Europa Classic Trigear Conversion to an Experimental Amateur Built Light Sport Aircraft (EABLSA) by use of Vortex Generators normally used for STOL Modifications Testing Dates 3 January 2010 thru 15 September 2010 Test Aircraft: N12AY Europa Classic Kit Power plant: Rotax 914 Propeller: Warp Drive three blade 64 inch wide chord This test was conducted to determine the feasibility of modifying a Europa Classic or XS kit aircraft to Light Sport Aircraft (LSA) standards. Experience has shown that the Europa kit aircraft is an efficient comfortable cruising aircraft with pleasing lines and superb flight characteristics. Many LSA aircraft are limited in cruise speed, strength, efficiency and comfort, which the Europa is not. The criteria for an aircraft to meet LSA, is in Ref 1 at the end of this document. Aerodynamically, the Europa wing is capable of generating a 1.7 Cl. Simple solution of the lift equation indicates the aircraft should stall at approximately 49 Knots for the XS and 53 for the Classic allowing for the slight differences in wing area. The LSA criteria set for the by the Federal Aviation Authority (FAA) calls for a controllable stall at 45 KIAS. My experience with adding vortex generators (VGs) to the Zenith and Piper Aircraft for STOL operations showed that a full length set of VGs, properly placed can lower the stall speed 5- 8 knots. The application of VGs should bring the stall speed of the Europa down to just meet the criteria listed in Ref 1. Since the maximum continuous power setting of the 914 is 73.5 KW or 95 HP the next problem is achieving a propeller setting that will absorb the power but limit the Europa to 120 Kts IAS cruise at sea level.