Clark y lift coefficient

 

The lift force can be obtained in two ways. It can be seen that LES results capture the shedding process of sheet cavitation and agree much better with experimental images when compared with RANS results. DISCUSSION: The Clark Y-14 airfoil profile is unusual in that its lower surface is straight and is taken as its chord line. CL is the coefficient of lift, depending on the angle of attack and the type of aerofoil. Due to the highly nonlinear Clark Y airfoil has a maximum thickness of 11. 0×105 for angles of attack ranging from 0° to 30°. Following the process of mesh refinement, it is observed that the deviation between the calculated results and the empirical data is reduced to below 1%. 5 × 10 4 ⁠, and 1. In this figure the results of Clark Y tests i o 4 by 24 Cork Y O Clark Y is the name of a particular airfoil profile, widely used in general purpose aircraft designs, and much studied in aerodynamics over the years. when α=0 the lift coefficient is given by the relation: Since for cambered airfoils the lift coefficient is not zero at zero angle of attack. By integrating the measured pressure A 10 m Clark Y airfoil operates at a tip speed ratio of 7. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. Variable-den-sity-tunnel data from reference 4. Inside the soft fins and arms, we designed some May 13, 2017 · In 1922, Colonel Virginius Clark invented the eponymous Clark Y-14 airfoil. The Clark Y-14 was derived from deforming a contemporary Göttingen airfoil such that the aft 70 percent of its bottom is flat. , Sep 6, 2013 · Lift and drag tests were made on a Clark Y wing equipped with four fixed slots and a trailing-edge flap in the 5-foot vertical wind tunnel of the National Advisory Committee for Aeronautics. 12 for α = 2° and Re = 10 6. Aug 19, 2009 · Partial preview of the text. The meaning and values of model parameters f , ξ f , C L 0 , Ω are discussed in the original paper ( Tamura, 1981 ). LIFT AND DRAG OF A CLARK Y AIRFOIL By FliED E. A hysteresis phenomenon is observed in the hydrodynamic curve and cavity area in increasing and Nov 15, 2020 · Compared with experiment data (Roohi et al. d = density of the air. 7C in height and 10C in length. 75m/s. The lift and drag coefficients and the lift to drag ratio can be found in Figure C2. Procedure. Activity: Pressure distribution on the surface of an airfoil . Here, wind tunnel testing is used to demonstrate how the aerodynamic performance of a Clark Y-14 wing is affected by high-lift devices, such as flaps and slats. The effects of a flap on the lift coefficient produced by an airfoil section. The results for Reynolds number Re= 106 are shown on the Fig. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at The families chosen consisted of the Clark-Y, NACA 16 series, and NACA 4 digit series airfoils. 38 Mach in This report presents the results of a series of wind tunnel tests showing the force, moment, and autorotational characteristics of Clark Y airfoils having aspect ratios varying from 0. 1) (3. Pic 3 While matching the thickness the Clark Y is rotated for the chord front to coincide. 64 m in the air flow under standard sea-level conditions is considered. 14) have compared the aerodynamic performance and acoustic estimates of the ARA-D, Clark Y and NACA 16 series airfoils. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at Sep 6, 2013 · Scale Effect on Clark Y Airfoil Characteristics from NACA Full-Scale Wind-Tunnel Tests This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of the Clark Y airfoil over a large range of Reynolds numbers. These high-speed lift coefficients usually lie in a range from about CIL=0. The test section should be 1 ft x 1 ft and the wind tunnel should be able to sustain a maximum airspeed of 140 The purpose of this investigation is to measure the surface pressure distribution, wake axial velocity profile, and lift and drag forces on a Clark-Y airfoil set at two angles of attack (0 and 16 degrees), and to compare the results, including their uncertainties, with benchmark data. In addition, the lift coefficient of the Clark Y airfoil and NACA114 airfoil is between a 1 airfoil and a 2 airfoil, which demonstrate that the optimized airfoil in this paper has A Clark Y-14 airfoil is shown in Figure 1 and has a thickness of 14% and is flat on the lower surface from 30% of the chord to the back. 33, pitching frequency f*= 2 Hz via combined experimental and numerical studies. 7 percent and is flat on the lower surface aft of 30 percent of chord. 4% increment in lift coefficient Stall AOA delay Oct 1, 2016 · To determine the effect of slat as one of the high lift devices on Clark Y-14, a two slat configuration is undertaken. 0 degrees, the lift and drag force increase just after the inception of cavitation. 1c, 0. 4. 3. Assume the airplane is landing with a weight of 2900 Ib. While unscientific in its design, the Clark Y-14 proved to be a popular airfoil Typical values for maximum lift coefficient These suggestions are from Roskam, Part I, pg. The angle of attack can consequently be checked with an inclinometer contacting the lower surface. As expected, the lift increases when the flap is deflected for all ground heights (Fig. Compared with the traditional Clark-Y and NACA0015 hydrofoils, the inflection point in the lift-drag curves of the S side and S top moves backward, and the flow stall is The wind turbine used Clark-Y airfoil considering it has good ratio of lift coefficient and drag coefficient. While unscientific in its design, the Clark Y-14 proved to be a popular airfoil resulting in the lift coefficient at the Reynolds number 5×104 being three times higher than that at 104 for a given angle of attack [16]. 11. 2 – 1. © 2017 The Authors. Figure 9 shows the variation of the maximmtnn lift coefficient for the Clark Y airfoil over a Reynolds Number range from 1,000,000 to 6,000,000. NACA2415 airfoil is used as the flat wing of a low-speed aircraft. 3, decreased rapidly to a Mach number of 0. Feb 7, 2014 · The aerodynamic effects of pressure, drag. The computational domain shown in Fig. An attempt at matching the airfoils thickness (height) together. Unsteady cavitating flow and lift/drag characteristics of a two-dimensional Clark Y-. 1 to 0. where: L denotes lift force. 0 × 10 4, 7. Tests. May 10, 2012 · Fig. C. 6 – 2. The wind tunnel experiments were performed for the DTU-LN221 User page server for CoE The lift coefficient increases with the increase of airfoil camber with the same angle of attack, and it show an obvious enhances trend toward the camber increase. 5 ⁰); this indicates an increase in lift coefficient by 30. Jan 1, 2018 · Induced drag can be reduced of about 2-3% a low cruise lift coefficient, until 8-10% at relative high cruise lift coefficient. Maximum lift coefficient increased up to a Mach number of 0. The various component of each computer code, the source of the data used to create the airfoil data bank, the limitations of each data bank, program listing, and a sample case with its associated input-output are described. The Clark-Y is a cambered airfoil that performs well at low and medium Reynolds numbers, having a maximum thickness of 11. 31 and a drag coefficient at 90 deg of 2. 19% C) which increase maximum lift to drag ratio An airfoil with aspect ratio of 6 at an angle of attack of 7° has lift coefficient and drag coefficient of 0. The twist angle along the blade was set as well to give maximum lift coefficient on each segment due to relative velocity. 4% at 28% and 42% of the chord length, respectively. Download scientific diagram | Effect of flap and slat on lift coefficient [13] from publication: Investigation of New Slat Configurations on Clark Y-14 Wing for Enhancing Aerodynamic Performance Mar 27, 2013 · Views: 133. Procedure May 13, 2021 · An aircraft's lift capabilities can be measured from the following formula: L = (1/2) d v2 s CL. Standard Atmosphere Table. 30 to 1. from publication: Airfoil Aerodynamics in Proximity to Wavy Ground for a Wide Range of Angles of Attack | Wing-in-ground craft Apr 30, 2023 · The pressure distribution and lift coefficient are important parameters that characterize the behavior of airfoils. velocity of 35. The free flow velocity is 70 m/s, and the lift per unit chord is 1254 N/m. 418: 18. Oct 1, 2016 · Results obtained show that Lift coefficient (C L) increased to (C L max=1. I have given some ranges for categories other than the ones needed in your assignments to remind you to think "outside the box". 3c & 0. Apr 30, 2023 · A Clark Y-14 airfoil is shown in Figure 1 and has a thickness of 14% and is flat on the lower surface from 30% of the chord to the back. 940 for the same airfoil with aspect ratio of 7. _VEICK fl. C. Sep 19, 2018 · L=1/2 ρv2 Sref CL. from publication: Aerodynamic effects of Gurney . 1) Δ C L max = 0. 8 1. The airfoil is analyzed for the Reynolds number of 6, 090,000 with the Clark Y type airfoil of uniform. fixed slots and a trailing-edge flap in the 5-foot vertical wind tunnel qf the National Advisory Committee for Aeronautics. 75. Lift characteristics and pressure distribution for a NACA 230 wing were investigated for an angle of attack range of from -10 to +24 degrees and Mach range of from 0. Reference area of a Clark Y-14 airfoil. Further increases in maximum lift coefficient may be possible using different types of flaps, such as slotted flaps, Fowler flaps, and double-slotted or triple-slotted flaps. 5 degrees, at the For this purpose, an aircraft with a Clark-Y airfoil is shown. Fl = 0. Assume elliptical lift distribution. Pic 2 The Clark Y chord is lower and parallel to the 2412 chord. SUBSONIC WIND-TUNNEL WALL CORRECTIONS ON A WING WITH A CLARK Y-14 AIRFOIL A Masters Project Presented to The Faculty of the Department of Mechanical and Aerospace Engineering Download scientific diagram | Lift coefficients of the Clark-Y airfoil including Gurney flap, reproduced and modified from Kheir-Aldeen (2014). These values can be found in a I. Category (C L,max)clean (C L,max)TO (C L,max)L Twin engine propeller 1. Sep 6, 2013 · Scale Effect on Clark Y Airfoil Characteristics from NACA Full-Scale Wind-Tunnel Tests This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of the Clark Y airfoil over a large range of Reynolds numbers. 55×105, cavitation number σ = 1. As a next step, the analysis tool XFOIL by Mark Drela [2] is used to evaluate the lift and drag polars of the resulting shape and compare it with the chosen airfoil at a given operating point. 7. The chord l Apr 1, 2021 · The lift coefficient C l of asymmetric hydrofoils (S side and Clark-Y hydrofoils) is significantly higher than that of symmetric hydrofoils (S top and NACA0015 hydrofoils). 225. 77 m/s and 0. 0 × 10 5 for angles of attack ranging from 0° to 30°. 4 – 2. 7% at 28% of the chord Sep 1, 2020 · The CLARK-Y hydrofoil with the chord length C of 70 mm is placed in the center of the computational domain. 8 F l = 0. v = 12m/s v = 12 m / s. 8. The optimal results were validated using Fluent. 2c, 0. Plot and print the shape of an airfoil (aerofoil) for your specific chord width and transformation. I recently conducted a wind tunnel experiment on a Clark Y-14 airfoil and am trying to quantify my data. 55, and then decreased moderately. The chord was design used Schimtz distribution to give proper force distribution along the blade. In conjunction with leading edge slats, significant stall speed reductions can be achieved 1945-01-01. from publication: Research on Integrated Optimization Design Method of High-Efficiency Motor Propeller System for UAVs With Multi-States lift and lateral control. A Cub has a minimum flying speed of 39. Jan 1, 2015 · It is shown how the supercritical airfoil distinguishes itself in terms pressure distribution and drag behavior once transonic conditions are encountered. particular interest. A genetic algorithm was used in each iteration to maximize the lift coefficient and lift-to-drag ratio, as predicted using a deep neural network (DNN). Note that for the symmetrical shape the lift coefficient is zero at zero angle of attack. This will change due to altitude. —The tests were made in the N. Propeller-research-tunnel value from reference 3. 7- by 10-foot wind tunnel which, together with associ- Nov 4, 2017 · CCW configurations to achieve high lift coefficients with low drag forces have been investigated on a Clark-Y airfoil [54], where a 3-D wing with an aspect ratio of AR \(=\) 2 is built and tested in a low speed wind tunnel. a). The flat Jan 10, 2014 · Measure the Lift, Drag and Pitching Moment of a Clark Y-14 airfoil. Procedure 1. May 13, 2017 · In 1922, Colonel Virginius Clark invented the eponymous Clark Y-14 airfoil. pressure distributions which evolve into the aerodynamic coefficients determine the load distribution and also allows an acoustic evaluation by the strip method. 05 Mach (turbulent conditions) to derive and study the sensitivity of meshing, coefficient of lift, coefficient of drag, lift to drag ratio, pressure, velocity and vector profile of Clark Y airfoil. All possible combinations oj Sep 18, 2016 · I am doing it for a competition) with a twin boom configuration like this: My wing shape is like this: I decided that the lift should be 0. Estimate the sea-level landing ground roll distance for the airplane in problem #4. , as shown in Table 1. The lift coefficient Cl is equal to the lift L divided The data reduction equation for the lift coefficient, CL, is given by [] U bc L CL L U b c 2 2, , , , ∞ ∞ = ρ ρ (3) where, L is the lift force acting on the airfoil surface, b is the airfoil span, and c is the airfoil chord (as shown in Figure 1. The acting forces, shown as vectors, adapt accordingly. 0×104, 7. The Clark Y is the name of a particular airfoil profile, widely used in general purpose aircraft designs, and much studied in aerodynamics over the years. The pressure distribution is directly related to the lift generated by airfoils. velocity of 0. The polar diagram shows how the lift and drag coefficients of the wing relate to each other. 7% hydrofoil are experimentally investigated in order to clarify the relation between the lift drop Jan 26, 2022 · 3. 5 to 3. 1 x 105] corresponding to angles of attack ranging from -4 degrees to 14. Open full size plan in new window test on a Clark Y airfoil, because the more recent tests are believed to be more accurate. 5 Sep 1, 2014 · The Gurney flap improve performance of Clark y-14 airfoil wing compare with clean wing, the results show that the most beneficial Gurney flap is (1. 2. Protocol highest value of the maximum lift coefficient for the Clark Y airfoil together with reasonable hinge moments (20-percent-chord flap) was used with the N. 0 × 10 5: Individual blowing & suction; combined blowing & suction: C L and C D: NACA0012: 0: 18: One suction One blowing: 0. At zero angle of attack i. contain explicit adjustments for the effects of aspect ratio (length to chord width) on lift and drag. After touchdown, assume zero lift. The profile was designed in 1922 by Virginius E. The number 2 after the dash indicates a design lift coefficient of 0. Download scientific diagram | Lift coefficient of ClarkY. Try to calculate the angle of attack and drag per unit chord. An airfoil of rectangular plan form was tested with rectangular tips, flared tips, and semicircular tips. 23021 airfoils. CLARK Y AIRFOIL - CLARK Y airfoil. to determine the behavior of the Clark Y airfoil with an air. Sref is the reference area or the wing area of an aircraft measured in square metres. These graphs show test results for several different Reynolds Nov 1, 2022 · Tamura’s model, applied on a static cylinder (y = 0), leads to a lift coefficient given by C L = − f α, where (1) α ̈ − 2 ξ f Ω 1 − 4 f 2 C L 0 2 α 2 α ̇ + Ω 2 α = 0. Figure 1. All possible combinations of the four slots were tested with the flap neutral and the most promising combinations were tested with the flap down 45 degrees. The pressure distribution and lift coefficient are important parameters that characterize the behavior of airfoils. 6c: momentum coefficients from 0. ρ is air density, affected by altitude. 12a). Similar tests are repeated here, but at lower moment coefficients of blowing, and with a different testing apparatus. Nov 14, 2023 · The lift coefficient is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on lift. The FX 63-137 produces a maximum poststall lift coefficient of 1. Find the angle of attack and drag coefficient corresponding to lift coefficient of 0. 2, and the number 15 denotes a 15% thickness-to-chord ratio. ) The present investigation was made to determine the effect on its aerodynamic characteristics of equipping a Clark Y airfoil with several fixed slots similar in neutral no appreciable improvement was found with the Jan 1, 2012 · The lift coefficient reaches a local maximum as shown in Fig. Would I just do the chord length times sin of the angle of attack (c*sin (\alpha)) for all angles Oct 10, 2000 · In order to generate greater lift force in the air, the soft fin was designed referring to Clark Y airfoil with large lift coefficient [23]. Apr 2, 2022 · The objective of this paper is to investigate the hysteresis effect of cavitating flow over a Clark-Y hydrofoil undergoing a transient pitching motion at Reynolds number Re = 4. 8g and I need to use this equation to find the wing area (as per the instructions) Fl = 1 2ρv2SCd F l = 1 2 ρ v 2 S C d. Effect of a Slat The airfoil used is Clark-Y type because it has a high glide ratio (coefficient lift/coefficient drag) in the application of subsonic flow. Furthermore, it is demonstrated that transonic flow limitations can play a major role in the maximum lift coefficient of (multi-element) airfoils at Mach numbers as low as 0. In a later study, the authors (Ref. However, the amount of lift augmentation due to Jan 15, 2022 · The increase in the maximum coefficient of lift of the wing ( ΔCLmax Δ C L max) can be related with the increase of the maximum coefficient of lift of an airfoil ( ΔcLmax Δ c L max ). Tests were also made on one airfoil of circular Clark Y pro le [8] has been selected as the base shape. A. For slotted and Fowler flaps, the expression is: ΔCLmax = 0. 5. 062 respectively. A lifting body is a foil or a complete foil-bearing body such as a fixed-wing aircraft. at 20. Camber in the main wing airfoil means that the wing's center of pressure will move forward with increasing angle of attack (AoA). e. Oct 31, 2023 · The lift coefficient C L and drag coefficient C D computed with varying grids are compared with the experiment values of Wang et al. 33%, respectively. For a 30 cm x 30 cm area at the tip of the airfoil calculate the net force and torque generated by this airfoil section (the 30 cm x 30 cm section). Comparison of the data with those of reference 1 indicates that a cambered (Clark Y) flap has characteristics more favorable to airplane performance than one of symmetrical section. Since the reference point for the pitching moment coefficient c m m is the airfoil's quarter point, this drives the c m m to negative values. 1 x 105] and [5. 25. Discuss the contributions of pressure and shear stress to over lift and drag. 3 mph in straight, level flight. The information on flap loads was judged adequate for the Dec 8, 2014 · Abstract. The angle of attack of the wing can be changed. Because the torsional stiffness of a wind turbine or fan airfoil about its longitudinal axis is normally high, airfoil moment coefficients are significantly less important than lift and drag coefficients, so In this experiment, a wind tunnel is utilized to generate certain airspeeds, and a Clark Y-14 wing with a flap and slat is used to collect and calculate data, such as the lift, drag and pitching moment coefficient. 91. 23012 and the N. This equation is simply a rearrangement of the lift equation where we solve for the lift coefficient in terms of the other variables. 5×104, and 1. CL is a function of the angle of the body I am trying to figure out how to calculate the lift coefficient of a clark Y-14 airfoil at each angle of attack using the data in the attatched table. Grid Generation for CFD Jul 15, 2023 · 64% increment in lift coefficient Stall AOA delay 2° Jet angle 20:60° [23] Experimental investigation: 1. 2%. 1 Effect of Reynolds number on airfoil maximum sectional lift-to-drag ratio. nd JOSEPH A. and lift were e valuated by computational fluid dynamics method. Blekhman Laboratory Report #9 Lift Coefficient for an Airfoil Matt Reimink 11/29/2020 Grading Rubric Purpose The purpose of the laboratory exercise is to measure the pressure distribution over a Clark Y-14 Airfoil and to A numerical simulation aiming to study and investigate flow behavior over a high lift low speed airfoil type AG-16 at various angles of attack ranging from 0 degree to 15 degree and constant Sep 1, 2022 · Unsteady cavitating flow and lift/drag characteristics of a two-dimensional Clark Y- 11. We could say the Clark Y is a NACA 4412 or real close to that. by Sky. A characteristic of great interest to the designer is the profile-drag coefficient at the lift coefficient for maximum speed. 2, and In this paper, an analysis was performed at an air velocity of 18. 92 Δ c l max S f w S w cos ∧ 1 / 4, Figure A-1 shows data for the NACA 0012 airfoil, a classic symmetrical shape that is used for everything from airplane stabilizers and canards to helicopter rotors to submarine “sails”. L = Lift, which must equal the airplane's weight in pounds. SHORTAL SUMMARY Lift amt drag tests were made on a Clark Y wing equipped a,ith four. 940 and 0. The airfoil has a thickness of 11. (Adapted from McMasters and Henderson [2] and Post-process the pressure data to estimate the lift coefficient . The main purpose of this study is to increase the power Clark Y airfoil. The results show that there exists a peak in total rotor efficiency (thrust-to-power ratio), and that the efficiency can be increased by 2% to 5% by increasing the pitch of the lower rotor. the lift coefficient at different angle of attacks for a cambered airfoil design. [1] Post-process the pressure data to estimate the lift coefficient Discuss the contributions of pressure and shear stress to over lift and drag . Padnos School of Engineering Grand Valley State University EGR – 365 Fluid Mechanics Dr. Apr 30, 2023 · In this experiment, a wind tunnel is utilized to generate certain airspeeds, and a Clark Y-14 wing with a flap and slat is used to collect and calculate data, such as the lift, drag and pitching moment coefficient. The maximum lift coefficient with flaps at touchdown is 1. Maximum achievable lift coefficient could be increased of about 20-30% in clean configuration, and more than 50% in flapped configuration. 1 (b) Three dimensional view of vortex generator. 9, The unsteady cavitation evolution around the Clark-Y hydrofoil is investigated in this paper, by using an improved filter-base The number 3 denotes the range of lift coefficient in tenths above and below the design lift coefficient for which low drag may be obtained. 7% and a camber of 3. 0 1. A Clark Y-14 airfoil model with 19 pressure ports is used to collect pressure data, which is used to estimate the lift coefficient. O. I need to get the coefficients of lift, drag, and moment but I am stuck on the reference area part. A Clark Y-14 airfoil, which is used in this demonstration, has a thickness of 14% and is flat on the lower surface from 30% of chord length to the back. Due to the highly nonlinear Aug 3, 2023 · An experimental study is conducted to research the combined effect of leading-edge (LE) tubercles and internal slots on the Clark-Y airfoil at Reynolds numbers (Re) of 5. As noted previously, many of the airfoils tested below a Reynolds number Fig. 03, whereas the E387 generates values of 1. 2 to 0. The cross section, lift, and drag coefficients of a Clark Y airfoil are Feb 17, 2016 · Surface pressures, drag and lift coefficients are studied for various velocities, 30, 35, 40, 45, 50 m/s with varying the ride height, 0. The dat file data can either be loaded from the airfoil database or your own airfoils which can be entered here and they will appear in the list of airfoils in the form below. 68) and stalling angle increased to (22. Clark Y-14 airfoil profile. If you click on the large content window of the animation, further layers are visible. 99, respectively. The angle of attack at which the lift coefficient becomes zero is given by the formula: Download scientific diagram | Lift coefficient curve for NACA4412. (Reference 2. , 2013), the lift coefficient C l and drag coefficient C d of the classical asymmetric airfoil Clark-Y are consistent with the experimental results with errors of 3. 95% and 8. A Clark Y-14 airfoil is shown in Figure 1 and has a thickness of 14% and is flat on the lower surface from 30% of the chord to the The pressure distribution and lift coefficient are important parameters that characterize the behavior of airfoils. Keywords: cavitation; Clark Y hydrofoil; lift increase Introduction It is known that the lift force produced by a single hydrofoil slightly increases with some amount of cavitation before the sudden drop of lift (lift breakdown) at some angles of attack. Views: 148. There are 18 pressure ports at the locations shown on it. 15c and 0. The lift, drag, and pitching forces on the airfoil can An experimental study is conducted to research the combined effect of leading-edge (LE) tubercles and internal slots on the Clark-Y airfoil at Reynolds numbers (Re) of 5. 05c, 0. V defines the velocity of aircraft expressed in m/s. ρ = 1. 5 in). [6], which is 2. 1 is consistent with experimental setup of Huang et al. 18 and 1. 7% hydro foil are experi mentally investigated in order to clarify the relation between the lift Nov 30, 2022 · NACA 2412 airfoil with chord length of 0. In this activity, we will measure the pressure drag and lift on a Clark Y airfoil. Results obtained show that Lift coefficient (C L) increased to (C L max=1 Clark Y pro le [8] has been selected as the base shape. By choosing the quarter point as the reference point, the value of c m Apr 23, 2016 · the maximum lift coefficient of a Clark Y airfoil was increased from 1. 026 to 0. Jul 1, 2021 · The quantitative comparison of the time-averaged lift coefficient (C l), drag coefficient (C d) and cavitation evolution cycle (T) is given in Table 3. 2c m, and the angle of attack, The objective of the current work is to experimentally investigate the effect of turbulent flow on an airfoil with a Gurney flap. Remove top cover of test section to install the Clark Y-14 model (chord length, c = 3. A Clark Y-14 airfoil is shown in Figure 1 and has a thickness of 14% and is flat on the lower surface from 30% of the chord to the Oct 1, 2016 · To determine the effect of slat as one of the high lift devices on Clark Y-14, a two slat configuration is undertaken. A. 225 ρ = 1. 12. A Clark Y-14 with chord 90mm and span 250mm has been tested at constant In fluid dynamics, the lift coefficient ( CL) is a dimensionless quantity that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. Sep 1, 2009 · The aerodynamic lift coefficient, drag coefficient, quarter-chord moment coefficient, and lift-to-drag ratio in extreme ground effect flight with a flap are shown in Fig. This experiment analyzed the coefficients of lift, drag and moment about the quarter chord for the NACA 0024 airfoil for Reynolds Numbers of [4. 92Δclmax Sfw Sw cos∧1/4, (3. ym me ay eq bj dk sn ww xw fj