CHAPTER 3 Drag Force and Drag Coefficient
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Airfoil Drag by Wake Survey Using Ldv
AIRFOIL DRAG BY WAKE SURVEY USING LDV 1 Purpose This experiment introduces the student to the use of Laser Doppler Velocimetry (LDV) as a means of measuring air flow velocities. The section drag of a NACA 0012 airfoil is determined from velocity measurements obtained in the airfoil wake. 2 Apparatus (1) .5 m x .7 m wind tunnel (max velocity 20 m/s) (2) NACA 0015 airfoil (0.2 m chord, 0.7 m span) (3) Betz manometer (4) Pitot tube (5) DISA LDV optics (6) Spectra Physics 124B 15 mW laser (632.8 nm) (7) DISA 55N20 LDV frequency tracker (8) TSI atomizer using 50cs silicone oil (9) XYZ LDV traversing system (10) Computer data reduction program 1 3 Notation A wing area (m2) b initial laser beam radius (m) bo minimum laser beam radius at lens focus (m) c airfoil chord length (m) Cd drag coefficient da elemental area in wake survey plane (m2) d drag force per unit span f focal length of primary lens (m) fo Doppler frequency (Hz) I detected signal amplitude (V) l distance across survey plane (m) r seed particle radius (m) s airfoil span (m) v seed particle velocity (instantaneous flow velocity) (m/s) U wake velocity (m/s) Uo upstream flow velocity (m/s) α Mie scatter size parameter/angle of attack (degs) δy fringe separation (m) θ intersection angle of laser beams λ laser wavelength (632.8 nm for He Ne laser) ρ air density at NTP (1.225 kg/m3) τ Doppler period (s) 4 Theory 4.1 Introduction The profile drag of a two-dimensional airfoil is the sum of the form drag due to boundary layer sep- aration (pressure drag), and the skin friction drag. -
Drag Force Calculation
DRAG FORCE CALCULATION “Drag is the component of force on a body acting parallel to the direction of relative motion.” [1] This can occur between two differing fluids or between a fluid and a solid. In this lab, the drag force will be explored between a fluid, air, and a solid shape. Drag force is a function of shape geometry, velocity of the moving fluid over a stationary shape, and the fluid properties density and viscosity. It can be calculated using the following equation, ퟏ 푭 = 흆푨푪 푽ퟐ 푫 ퟐ 푫 Equation 1: Drag force equation using total profile where ρ is density determined from Table A.9 or A.10 in your textbook A is the frontal area of the submerged object CD is the drag coefficient determined from Table 1 V is the free-stream velocity measured during the lab Table 1: Known drag coefficients for various shapes Body Status Shape CD Square Rod Sharp Corner 2.2 Circular Rod 0.3 Concave Face 1.2 Semicircular Rod Flat Face 1.7 The drag force of an object can also be calculated by applying the conservation of momentum equation for your stationary object. 휕 퐹⃗ = ∫ 푉⃗⃗ 휌푑∀ + ∫ 푉⃗⃗휌푉⃗⃗ ∙ 푑퐴⃗ 휕푡 퐶푉 퐶푆 Assuming steady flow, the equation reduces to 퐹⃗ = ∫ 푉⃗⃗휌푉⃗⃗ ∙ 푑퐴⃗ 퐶푆 The following frontal view of the duct is shown below. Integrating the velocity profile after the shape will allow calculation of drag force per unit span. Figure 1: Velocity profile after an inserted shape. Combining the previous equation with Figure 1, the following equation is obtained: 푊 퐷푓 = ∫ 휌푈푖(푈∞ − 푈푖)퐿푑푦 0 Simplifying the equation, you get: 20 퐷푓 = 휌퐿 ∑ 푈푖(푈∞ − 푈푖)훥푦 푖=1 Equation 2: Drag force equation using wake profile The pressure measurements can be converted into velocity using the Bernoulli’s equation as follows: 2Δ푃푖 푈푖 = √ 휌퐴푖푟 Be sure to remember that the manometers used are in W.C. -
Chapter 4: Immersed Body Flow [Pp
MECH 3492 Fluid Mechanics and Applications Univ. of Manitoba Fall Term, 2017 Chapter 4: Immersed Body Flow [pp. 445-459 (8e), or 374-386 (9e)] Dr. Bing-Chen Wang Dept. of Mechanical Engineering Univ. of Manitoba, Winnipeg, MB, R3T 5V6 When a viscous fluid flow passes a solid body (fully-immersed in the fluid), the body experiences a net force, F, which can be decomposed into two components: a drag force F , which is parallel to the flow direction, and • D a lift force F , which is perpendicular to the flow direction. • L The drag coefficient CD and lift coefficient CL are defined as follows: FD FL CD = 1 2 and CL = 1 2 , (112) 2 ρU A 2 ρU Ap respectively. Here, U is the free-stream velocity, A is the “wetted area” (total surface area in contact with fluid), and Ap is the “planform area” (maximum projected area of an object such as a wing). In the remainder of this section, we focus our attention on the drag forces. As discussed previously, there are two types of drag forces acting on a solid body immersed in a viscous flow: friction drag (also called “viscous drag”), due to the wall friction shear stress exerted on the • surface of a solid body; pressure drag (also called “form drag”), due to the difference in the pressure exerted on the front • and rear surfaces of a solid body. The friction drag and pressure drag on a finite immersed body are defined as FD,vis = τwdA and FD, pres = pdA , (113) ZA ZA Streamwise component respectively. -
Drag Coefficients of Inclined Hollow Cylinders
Drag Coefficients of Inclined Hollow Cylinders: RANS versus LES A Major Qualifying Project Report Submitted to the Faculty of the WORCESTER POLYTECHNIC INSTITUTE in partial fulfillment of the requirements for the Degree of Bachelor of Science In Chemical Engineering By Ben Franzluebbers _______________ Date: April 2013 Approved: ________________________ Dr. Anthony G. Dixon, Advisor Abstract The goal of this project was use LES and RANS (SST k-ω) CFD turbulence models to find the drag coefficient of a hollow cylinder at various inclinations and compare the results. The drag coefficients were evaluated for three angles relative to the flow (0⁰, 45⁰, and 90⁰) and three Reynolds numbers (1000, 5000, and 10000). The drag coefficients determined by LES and RANS agreed for the 0⁰ and 90⁰ inclined hollow cylinder. For the 45⁰ inclined hollow cylinder the RANS model predicted drag coefficients about 0.2 lower the drag coefficients predicted by LES. 2 Executive Summary The design of catalyst particles is an important topic in the chemical industry. Chemical products made using catalytic processes are worth $900 billion a year and about 75% of all chemical and petroleum products by value (U.S. Climate Change Technology Program, 2005). The catalyst particles used for fixed bed reactors are an important part of this. Knowing properties of the catalyst particle such as the drag coefficient is necessary to understand how fluid flow will be affected by the packed bed. The particles are inclined at different angles in the reactor and can come in a wide variety of shapes meaning that understanding the effect of particle shape on drag coefficient has practical importance. -
On the Generation of a Reverse Von Kármán Street for the Controlled Cylinder Wake in the Laminar Regime
On the generation of a reverse Von Kármán street for the controlled cylinder wake in the laminar regime Michel Bergmann,∗ Laurent Cordier, and Jean-Pierre Brancher LEMTA, UMR 7563 (CNRS - INPL - UHP) ENSEM - 2, avenue de la forêt de Haye BP 160 - 54504 Vandœuvre cedex, France (Dated: December 8, 2005) 1 Abstract In this Brief Communication we are interested in the maximum mean drag reduction that can be achieved under rotary sinusoidal control for the circular cylinder wake in the laminar regime. For a Reynolds number equal to 200, we give numerical evidence that partial control restricted to an upstream part of the cylinder surface may increase considerably the effectiveness of the control. Indeed, a maximum value of relative mean drag reduction equal to 30% is obtained when applying a specific sinusoidal control to the whole cylinder, where up to 75% of reduction can be obtained when the same control law is applied only to a well selected upstream part of the cylinder. This result suggests that a mean flow correction field with negative drag is observable for this controlled flow configuration. The significant thrust force that is locally generated in the near wake corresponds to a reverse Kármán vortex street as commonly observed in fish-like locomotion or flapping wing flight. Finally, the energetic efficiency of the control is quantified by examining the Power Saving Ratio: it is shown that our approach is energetically inefficient. However, it is also demonstrated that for this control scheme the improvement of the effectiveness goes generally with an improvement of the efficiency. Keywords: Partial rotary control ; Cylinder wake ; Drag minimization ; reverse Kármán vortex street. -
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. -
Chapter 4: Immersed Body Flow [Pp
MECH 3492 Fluid Mechanics and Applications Univ. of Manitoba Fall Term, 2017 Chapter 4: Immersed Body Flow [pp. 445-459 (8e), or 374-386 (9e)] Dr. Bing-Chen Wang Dept. of Mechanical Engineering Univ. of Manitoba, Winnipeg, MB, R3T 5V6 When a viscous fluid flow passes a solid body (fully-immersed in the fluid), the body experiences a net force, F, which can be decomposed into two components: a drag force F , which is parallel to the flow direction, and • D a lift force F , which is perpendicular to the flow direction. • L The drag coefficient CD and lift coefficient CL are defined as follows: FD FL CD = 1 2 and CL = 1 2 , (112) 2 ρU A 2 ρU Ap respectively. Here, U is the free-stream velocity, A is the “wetted area” (total surface area in contact with fluid), and Ap is the “planform area” (maximum projected area of an object such as a wing). In the remainder of this section, we focus our attention on the drag forces. As discussed previously, there are two types of drag forces acting on a solid body immersed in a viscous flow: friction drag (also called “viscous drag”), due to the wall friction shear stress exerted on the • surface of a solid body; pressure drag (also called “form drag”), due to the difference in the pressure exerted on the front • and rear surfaces of a solid body. The friction drag and pressure drag on a finite immersed body are defined as FD,vis = τwdA and FD, pres = pdA , (113) ZA ZA Streamwise component respectively. -
Upwind Sail Aerodynamics : a RANS Numerical Investigation Validated with Wind Tunnel Pressure Measurements I.M Viola, Patrick Bot, M
Upwind sail aerodynamics : A RANS numerical investigation validated with wind tunnel pressure measurements I.M Viola, Patrick Bot, M. Riotte To cite this version: I.M Viola, Patrick Bot, M. Riotte. Upwind sail aerodynamics : A RANS numerical investigation validated with wind tunnel pressure measurements. International Journal of Heat and Fluid Flow, Elsevier, 2012, 39, pp.90-101. 10.1016/j.ijheatfluidflow.2012.10.004. hal-01071323 HAL Id: hal-01071323 https://hal.archives-ouvertes.fr/hal-01071323 Submitted on 8 Oct 2014 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. I.M. Viola, P. Bot, M. Riotte Upwind Sail Aerodynamics: a RANS numerical investigation validated with wind tunnel pressure measurements International Journal of Heat and Fluid Flow 39 (2013) 90–101 http://dx.doi.org/10.1016/j.ijheatfluidflow.2012.10.004 Keywords: sail aerodynamics, CFD, RANS, yacht, laminar separation bubble, viscous drag. Abstract The aerodynamics of a sailing yacht with different sail trims are presented, derived from simulations performed using Computational Fluid Dynamics. A Reynolds-averaged Navier- Stokes approach was used to model sixteen sail trims first tested in a wind tunnel, where the pressure distributions on the sails were measured. -
Technical Memorandum X-26
.. .. 1 NASA TM X-26 TECHNICAL MEMORANDUM X-26 DESIGN GUIDE FOR PITCH-UP EVALUATION AND INVESTIGATION AT HIGH SUBSONIC SPEEDS OF POSSIBLE LlMITATIONS DUE TO WING-ASPECT-RATIO VARIATIONS By Kenneth P. Spreemann Langley Research Center Langley Field, Va. Declassified July 11, 1961 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON August 1959 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION . TEKX"NCAL MEMORANDUM x-26 DESIGN GUIDE FOR PITCH-UP EVALUATION AND INVESTIGATION AT HIGH SUBSONIC SPEEDS OF POSSIBLE LIMITATIONS DUE TO WING-ASPECT-RATIO VARIATIONS J By Kenneth P. Spreemann SUMMARY A design guide is suggested as a basis for indicating combinations of airplane design variables for which the possibilities of pitch-up are minimized for tail-behind-wing and tailless airplane configurations. The guide specifies wing plan forms that would be expected to show increased tail-off stability with increasing lift and plan forms that show decreased tail-off stability with increasing lift. Boundaries indicating tail-behind-wing positions that should be considered along with given tail-off characteristics also are suggested. An investigation of one possible limitation of the guide with respect to the effects of wing-aspect-ratio variations on the contribu- tion to stability of a high tail has been made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.92. The measured pitching-moment characteristics were found to be consistent with those of the design guide through the lift range for aspect ratios from 3.0 to 2.0. However, a configuration with an aspect ratio of 1.55 failed to provide the predicted pitch-up warning characterized by sharply increasing stability at the high lifts following the initial stall before pitching up. -
Scramjet Nozzle Design and Analysis As Applied to a Highly Integrated Hypersonic Research Airplane
NASA TECHN'ICAL NOTE NASA D-8334 d- . ,d d K a+ 4 c/) 4 z SCRAMJET NOZZLE DESIGN AND ANALYSIS AS APPLIED TO A HIGHLY INTEGRATED HYPERSONIC RESEARCH AIRPLANE Wi'llidm J. Smull, John P. Wehher, and P. J. Johnston i Ldngley Reseurch Center Humpton, Va. 23665 / NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. c. .'NOVEMBER 1976 TECH LIBRARY KAFB, NM I Illill 111 lllll11Il1 lllll lllll lllll IIll ~~ ~~- - 1. Report No. 2. Government Accession No. -. ___r_- --.-= .--. NASA TN D-8334 I ~~ 4. Title and ,Subtitle 5. Report Date November 1976 7. Author(sl 8. Performing Organization Report No. William J. Small, John P. Weidner, L-11003 and P. J. Johnston . ~ ~-.. ~ 10. Work Unit No. 9. Performing Organization Nwne and Address 505-11-31-02 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 Note National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, DC 20546 -. I 15. Supplementary Notes -~ 16. Abstract The great potential expected from future air-breathing hypersonic aircraft systems is predicated on the assumption that the propulsion system can be effi- ciently integrated with the airframe. A study of engine-nozzle airframe inte- gration at hypersonic speeds has been conducted by using a high-speed research- aircraft concept as a focus. Recently developed techniques for analysis of scramjet-nozzle exhaust flows provide a realistic analysis of complex forces resulting from the engine-nozzle airframe coupling. Results from these studies show that by properly integrating the engine-nozzle propulsive system with the airframe, efficient, controlled and stable flight results over a wide speed range.