Airfoil Selection and Wingsail Design for an Autonomous Sailboat
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Enhancing General Aviation Aircraft Safety with Supplemental Angle of Attack Systems
University of North Dakota UND Scholarly Commons Theses and Dissertations Theses, Dissertations, and Senior Projects January 2015 Enhancing General Aviation Aircraft aS fety With Supplemental Angle Of Attack Systems David E. Kugler Follow this and additional works at: https://commons.und.edu/theses Recommended Citation Kugler, David E., "Enhancing General Aviation Aircraft aS fety With Supplemental Angle Of Attack Systems" (2015). Theses and Dissertations. 1793. https://commons.und.edu/theses/1793 This Dissertation is brought to you for free and open access by the Theses, Dissertations, and Senior Projects at UND Scholarly Commons. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of UND Scholarly Commons. For more information, please contact [email protected]. ENHANCING GENERAL AVIATION AIRCRAFT SAFETY WITH SUPPLEMENTAL ANGLE OF ATTACK SYSTEMS by David E. Kugler Bachelor of Science, United States Air Force Academy, 1983 Master of Arts, University of North Dakota, 1991 Master of Science, University of North Dakota, 2011 A Dissertation Submitted to the Graduate Faculty of the University of North Dakota in partial fulfillment of the requirements for the degree of Doctor of Philosophy Grand Forks, North Dakota May 2015 Copyright 2015 David E. Kugler ii PERMISSION Title Enhancing General Aviation Aircraft Safety With Supplemental Angle of Attack Systems Department Aviation Degree Doctor of Philosophy In presenting this dissertation in partial fulfillment of the requirements for a graduate degree from the University of North Dakota, I agree that the library of this University shall make it freely available for inspection. I further agree that permission for extensive copying for scholarly purposes may be granted by the professor who supervised my dissertation work or, in his absence, by the Chairperson of the department or the dean of the School of Graduate Studies. -
Sailing for Performance
SD2706 Sailing for Performance Objective: Learn to calculate the performance of sailing boats Today: Sailplan aerodynamics Recap User input: Rig dimensions ‣ P,E,J,I,LPG,BAD Hull offset file Lines Processing Program, LPP: ‣ Example.bri LPP_for_VPP.m rigdata Hydrostatic calculations Loading condition ‣ GZdata,V,LOA,BMAX,KG,LCB, hulldata ‣ WK,LCG LCF,AWP,BWL,TC,CM,D,CP,LW, T,LCBfpp,LCFfpp Keel geometry ‣ TK,C Solve equilibrium State variables: Environmental variables: solve_Netwon.m iterative ‣ VS,HEEL ‣ TWS,TWA ‣ 2-dim Netwon-Raphson iterative method Hydrodynamics Aerodynamics calc_hydro.m calc_aero.m VS,HEEL dF,dM Canoe body viscous drag Lift ‣ RFC ‣ CL Residuals Viscous drag Residuary drag calc_residuals_Newton.m ‣ RR + dRRH ‣ CD ‣ dF = FAX + FHX (FORCE) Keel fin drag ‣ dM = MH + MR (MOMENT) Induced drag ‣ RF ‣ CDi Centre of effort Centre of effort ‣ CEH ‣ CEA FH,CEH FA,CEA The rig As we see it Sail plan ≈ Mainsail + Jib (or genoa) + Spinnaker The sail plan is defined by: IMSYC-66 P Mainsail hoist [m] P E Boom leech length [m] BAD Boom above deck [m] I I Height of fore triangle [m] J Base of fore triangle [m] LPG Perpendicular of jib [m] CEA CEA Centre of effort [m] R Reef factor [-] J E LPG BAD D Sailplan modelling What is the purpose of the sails on our yacht? To maximize boat speed on a given course in a given wind strength ‣ Max driving force, within our available righting moment Since: We seek: Fx (Thrust vs Resistance) ‣ Driving force, FAx Fy (Side forces, Sails vs. Keel) ‣ Heeling force, FAy (Mx (Heeling-righting moment)) ‣ Heeling arm, CAE Aerodynamics of sails A sail is: ‣ a foil with very small thickness and large camber, ‣ with flexible geometry, ‣ usually operating together with another sail ‣ and operating at a large variety of angles of attack ‣ Environment L D V Each vertical section is a differently cambered thin foil Aerodynamics of sails TWIST due to e.g. -
Technology for Pressure-Instrumented Thin Airfoil Models
NASA-CR-3891 19850015493 NASA Contractor Report 3891 i 1 Technology for Pressure-Instrumented Thin Airfoil Models David A. Wigley ., ..... " .... _' /, !..... .,L_. '' CONTRACT NAS1-17571 MAY 1985 ( • " " c _J ._._l._,.. ¸_ - j, ;_.. , r_ '._:i , _ . ; . ,. NIA NASA Contractor Report 3891 Technology for Pressure-Instrumented Thin Airfoil Models David A. Wigley Applied Cryogenics & Materials Consultants, Inc. New Castle, Delaware Prepared for Langley Research Center under Contract NAS1-17571 N//X National Aeronautics and Space Administration Scientific and Technical InformationBranch 1985 Use of trademarks or names of manufacturers in this report does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the National Aeronautics and Space Administration. FINAL REPORT ON PHASE 1 OF NASA CONTRACT NASI-17571 "TECHNOLOGY FOR PRESSURE-INSTRUMENTED THIN AIRFOIL MODELS" PROJECT SU_IARY The objective of Phase 1 of this research was to identify, then select and evaluate, the most appropriate combination of materials and fabrication techniques required to produce a Pressure Instrumented Thin Airfoil model for testing in a Cryogenic wind Tunnel ( PITACT ). Particular attention was to be given to proving the feasability and reliability of each sub-stage and ensuring that they could be combined together without compromising the quality of the resultant segment or model. In order to provide a sharp focus for this research, experimental samples were to be fabricated as if they were trailing edge segments of a 6% thick supercritical airfoil, number 0631X7, scaled to a 325mm (13in.) chord, the maximum likely to be tested in the 13in. x 13in. adaptive wall test section of the 0.3m Transonic Cryogenic Tunnel at NASA Langley Research Center. -
Aerodynamic Characteristics of Naca 0012 Airfoil Section at Different Angles of Attack
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK SUPREETH NARASIMHAMURTHY GRADUATE STUDENT 1327291 Table of Contents 1) Introduction………………………………………………………………………………………………………………………………………...1 2) Methodology……………………………………………………………………………………………………………………………………….3 3) Results……………………………………………………………………………………………………………………………………………......5 4) Conclusion …………………………………………………………………………………………………………………………………………..9 5) References…………………………………………………………………………………………………………………………………………10 List of Figures Figure 1: Basic nomenclature of an airfoil………………………………………………………………………………………………...1 Figure 2: Computational domain………………………………………………………………………………………………………………4 Figure 3: Static Pressure Contours for different angles of attack……………………………………………………………..5 Figure 4: Velocity Magnitude Contours for different angles of attack………………………………………………………………………7 Fig 5: Variation of Cl and Cd with alpha……………………………………………………………………………………………………8 Figure 6: Lift Coefficient and Drag Coefficient Ratio for Re = 50000…………………………………………………………8 List of Tables Table 1: Lift and Drag coefficients as calculated from lift and drag forces from formulae given above……7 Introduction It is a fact of common experience that a body in motion through a fluid experience a resultant force which, in most cases is mainly a resistance to the motion. A class of body exists, However for which the component of the resultant force normal to the direction to the motion is many time greater than the component resisting the motion, and the possibility of the flight of an airplane depends on the use of the body of this class for wing structure. Airfoil is such an aerodynamic shape that when it moves through air, the air is split and passes above and below the wing. The wing’s upper surface is shaped so the air rushing over the top speeds up and stretches out. This decreases the air pressure above the wing. The air flowing below the wing moves in a comparatively straighter line, so its speed and air pressure remain the same. -
Aerodynamics of High-Performance Wing Sails
Aerodynamics of High-Performance Wing Sails J. otto Scherer^ Some of tfie primary requirements for tiie design of wing sails are discussed. In particular, ttie requirements for maximizing thrust when sailing to windward and tacking downwind are presented. The results of water channel tests on six sail section shapes are also presented. These test results Include the data for the double-slotted flapped wing sail designed by David Hubbard for A. F. Dl Mauro's lYRU "C" class catamaran Patient Lady II. Introduction The propulsion system is probably the single most neglect ed area of yacht design. The conventional triangular "soft" sails, while simple, practical, and traditional, are a long way from being aerodynamically desirable. The aerodynamic driving force of the sails is, of course, just as large and just as important as the hydrodynamic resistance of the hull. Yet, designers will go to great lengths to fair hull lines and tank test hull shapes, while simply drawing a triangle on the plans to define the sails. There is no question in my mind that the application of the wealth of available airfoil technology will yield enormous gains in yacht performance when applied to sail design. Re cent years have seen the application of some of this technolo gy in the form of wing sails on the lYRU "C" class catamar ans. In this paper, I will review some of the aerodynamic re quirements of yacht sails which have led to the development of the wing sails. For purposes of discussion, we can divide sail require ments into three points of sailing: • Upwind and close reaching. -
Formula 1 Race Car Performance Improvement by Optimization of the Aerodynamic Relationship Between the Front and Rear Wings
The Pennsylvania State University The Graduate School College of Engineering FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS A Thesis in Aerospace Engineering by Unmukt Rajeev Bhatnagar © 2014 Unmukt Rajeev Bhatnagar Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science December 2014 The thesis of Unmukt R. Bhatnagar was reviewed and approved* by the following: Mark D. Maughmer Professor of Aerospace Engineering Thesis Adviser Sven Schmitz Assistant Professor of Aerospace Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School ii Abstract The sport of Formula 1 (F1) has been a proving ground for race fanatics and engineers for more than half a century. With every driver wanting to go faster and beat the previous best time, research and innovation in engineering of the car is really essential. Although higher speeds are the main criterion for determining the Formula 1 car’s aerodynamic setup, post the San Marino Grand Prix of 1994, the engineering research and development has also targeted for driver’s safety. The governing body of Formula 1, i.e. Fédération Internationale de l'Automobile (FIA) has made significant rule changes since this time, primarily targeting car safety and speed. Aerodynamic performance of a F1 car is currently one of the vital aspects of performance gain, as marginal gains are obtained due to engine and mechanical changes to the car. Thus, it has become the key to success in this sport, resulting in teams spending millions of dollars on research and development in this sector each year. -
Naca Research Memorandum
https://ntrs.nasa.gov/search.jsp?R=19930086840 2020-06-17T13:35:35+00:00Z Copy RMA5lll2 NACA RESEARCH MEMORANDUM A FLIGHT EVALUATION OF THE LONGITUDINAL STABILITY CHARACTERISTICS ASSOCIATED WITH THE PITCH-TIP OF A SWEPT-WING AIRPLANE IN MANEUVERING FLIGHT AT TRANSONIC SPEEDS 4'YJ A By Seth B. Anderson and Richard S. Bray Ames Aeronautical Laboratory Moffett Field, Calif. ENGINEERING DPT, CHANCE-VOUGHT AIRuRAf' DALLAS, TEXAS This material contains information hi etenoe toe jeoted States w:thin toe of the espionage laws, Title 18, 15 and ?j4, the transnJssionc e reveLation tnotct: in manner to unauthorized person Is et 05 Lan. NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON November 27, 1951 NACA RM A51112 INN-1.W, NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS A FLIGHT EVALUATION OF THE LONGITUDINAL STABILITY CHARACTERISTICS ASSOCIATED WITH THE PITCH-UP OF A SWEPT-WING AIPLAI'1E IN MANEUVERING FLIGHT AT TRANSONIC SPEEDS By Seth B. Anderson and Richard S. Bray SUMMARY Flight measurements of the longitudinal stability and control characteristics were made on a swept-wing jet aircraft to determine the origin of the pitch-up encountered in maneuvering flight at transonic speeds. The results showed that the pitch-up. encountered in a wind-up turn at constant Mach number was caused principally by an unstable break in the wing pitching moment with increasing lift. This unstable break in pitching moment, which was associated with flow separation near the wing tips, was not present beyond approximately 0.93 Mach number over the lift range covered in these tests. The pitch-up encountered in a high Mach number dive-recovery maneuver was due chiefly to a reduction in the wing- fuselage stability with decreasing Mach number. -
Mainsail Trim Pointers, Reefing and Sail Care for the Beneteau Oceanis Series
Neil Pryde Sails International 1681 Barnum Avenue Stratford, CT 06614 203-375-2626 [email protected] INTERNATIONAL DESIGN AND TECHNICAL OFFICE Mainsail Trim Pointers, Reefing and Sail Care for the Beneteau Oceanis Series The following points on mainsail trim apply both to the Furling and Classic mainsails we produce for Beneteau USA and the Oceanis Line of boats. In sailing the boats we can offer these general ideas and observations that will apply to the 311’s through to the newest B49. Mainsail trim falls into two categories, upwind and downwind. MAINSAIL TRIM: The following points on mainsail trim apply both to the Furling and Classic mainsail, as the concepts are the same. Mainsail trim falls into two categories, upwind and downwind. Upwind 1. Upwind in up to about 8 knots true wind the traveler can be brought to weather of centerline. This ensures that the boom will be close centerline and the leech of the sail in a powerful upwind mode. 2. The outhaul should be eased 2” / 50mm at the stopper, easing the foot of the mainsail away from the boom about 8”/200mm 3. Mainsheet tension should be tight enough to have the uppermost tell tail on the leech streaming aft about 50% of the time in the 7- 12 true wind range. For those with furling mainsails the action of furling and unfurling the sail can play havoc with keeping the telltales on the sail and you may need to replace them from time to time. Mainsail outhaul eased for light air upwind trim You will find that the upper tell tail will stall and fold over to the weather side of the sail about 50% of the time in 7-12 knots. -
Sail Trimming Guide for the Beneteau 37 September 2008
INTERNATIONAL DESIGN AND TECHNICAL OFFICE Sail Trimming Guide for the Beneteau 37 September 2008 © Neil Pryde Sails International 1681 Barnum Avenue Stratford, CONN 06614 Phone: 203-375-2626 • Fax: 203-375-2627 Email: [email protected] Web: www.neilprydesails.com All material herein Copyright 2007-2008 Neil Pryde Sails International All Rights Reserved HEADSAIL OVERVIEW: The Beneteau 37 built in the USA and supplied with Neil Pryde Sails is equipped with a 105% non-overlapping headsail that is 337sf / 31.3m2 in area and is fitted to a Profurl C320 furling unit. The following features are built into this headsail: • The genoa sheets in front of the spreaders and shrouds for optimal sheeting angle and upwind performance • The size is optimized to sheet correctly to the factory track when fully deployed and when reefed. • Reef ‘buffer’ patches are fitted at both head and tack, which are designed to distribute the loads on the sail when reefed. • Reefing marks located on the starboard side of the tack buffer patch provide a visual mark for setting up pre-determined reefing locations. These are located 508mm/1’-8” and 1040mm / 3’-5” aft of the tack. • A telltale ‘window’ at the leading edge of the sail located about 14% of the luff length above the tack of the sail and is designed to allow the helmsperson to easily see the wind flowing around the leading edge of the sail when sailing upwind and close-hauled. The tell-tales are red and green, so that one can quickly identify the leeward and weather telltales. -
The Weather Helm Issue (Rev 20 02 2020)
Corbin 39 – the weather helm issue (rev 20 02 2020) Synopsis The subject of weather helm comes up repeatedly when discussing the Corbin 39 and not all of the folklore is justified. This note attempts to summarise the issue and to relate it to sufficient evidence, and to qualitative theory, that we can be reasonably certain of the situation. Remember - It is possible to overpower a yacht and induce weather helm, what we are trying to do is identify excessive weather helm. The key take-away is that the excessive weather helm was a genuine issue, which affected all the mk1 cutters irrespective of whether they were equipped with the taller double-spreader mast or the shorter single-spreader mast, provided that the mast was set in the intended aft mast position. Perhaps this was worse in the mk1 tallmast vs the mk1 shortmast, but we are not at all certain of that. All the mk1’s that had the forestay relocated onto a 3-foot long bowsprit were later able to alleviate this to an extent. The mk 1’s that have reduced the area of their main by shortening the mainsail boom & foot (or used in-mast furling) have reportedly completely eliminated this weather helm. All other versions including the mk1 ketches and all the mk2 cutters & ketches appear to be completely unaffected. This is the first openly published version of this analysis. Previous drafts were incomplete and drew erroneous conclusions in some areas due to an absence of reliable data. That has now been overcome as further evidence has come forwards, and so there are material differences between this version and previous drafts. -
How the Beaufort Scale Affects Your Sail Plan
How the Beaufort scale affects your sail plan The Beaufort scale is a measurement that relates wind speed to observed conditions at sea. Used in the sea area forecast it allows sailors to anticipate the condition that they are likely to face. Modern cruising yachts have become wider over the years to allow more room inside the boat when berthed. This offers the occupants a large living space but does have an effect on the handling of the boat. A wide beam, relatively short keel and rudder mean that if they have too much sail up they have a greater tendency to broach into the wind. Broaching, although dramatic for those onboard, is nothing more than the boat turning into the wind and is easy to rectify by carrying less sail. If the helm is struggling to keep the boat in a straight line then the boat has too much ‘weather helm’ i.e. the boat keeps turning into the wind- in this instance it is necessary to reduce sail. Racer/cruisers are often narrower than their cruising counter parts, with longer keels and rudders which mean they are less likely to broach, but often more difficult to sail with a small crew. Cruising yachts often have large overlapping jibs or genoas and relevantly small main sails. This allows the sail area to be reduced quickly and easily simply by furling away some head sail. The main sail is used to balance boat as the main drive comes from the head sail. Racer cruisers will often have smaller jibs and larger main sails, so reducing the sail area means reefing the main sail first and using the jib to balance the boat. -
Active Control of Flow Over an Oscillating NACA 0012 Airfoil
Active Control of Flow over an Oscillating NACA 0012 Airfoil Dissertation Presented in Partial Fulfillment of the Requirements for the Degree Doctor of Philosophy in the Graduate School of The Ohio State University By David Armando Castañeda Vergara, M.S., B.S. Graduate Program in Aeronautical and Astronautical Engineering The Ohio State University 2020 Dissertation Committee: Dr. Mo Samimy, Advisor Dr. Datta Gaitonde Dr. Jim Gregory Dr. Miguel Visbal Dr. Nathan Webb c Copyright by David Armando Castañeda Vergara 2020 Abstract Dynamic stall (DS) is a time-dependent flow separation and stall phenomenon that occurs due to unsteady motion of a lifting surface. When the motion is sufficiently rapid, the flow can remain attached well beyond the static stall angle of attack. The eventual stall and dynamic stall vortex formation, convection, and shedding processes introduce large unsteady aerodynamic loads (lift, drag, and moment) which are undesirable. Dynamic stall occurs in many applications, including rotorcraft, micro aerial vehicles (MAVs), and wind turbines. This phenomenon typically occurs in rotorcraft applications over the rotor at high forward flight speeds or during maneuvers with high load factors. The primary adverse characteristic of dynamic stall is the onset of high torsional and vibrational loads on the rotor due to the associated unsteady aerodynamic forces. Nanosecond Dielectric Barrier Discharge (NS-DBD) actuators are flow control devices which can excite natural instabilities in the flow. These actuators have demonstrated the ability to delay or mitigate dynamic stall. To study the effect of an NS-DBD actuator on DS, a preliminary proof-of-concept experiment was conducted. This experiment examined the control of DS over a NACA 0015 airfoil; however, the setup had significant limitations.