(clarkk-il) CLARK K AIRFOIL CLARK K airfoil Max thickness 11.7% at 29.7% chord. Max camber 3.3% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format: CLARK K AIRFOIL 14. 14.Parser. (clarkz-il) CLARK Z AIRFOIL. CLARK Z airfoil. Max thickness 11.8% at 30% chord. Max camber 4% at 40% chord. Source UIUC Airfoil Coordinates Database. Source dat file. The dat file is in Lednicer format. CLARK Z AIRFOIL 17.Calculate the lift and moment coefficients using thin airfoil theory approximations for a range of angle of attacks for the following airfoils below. 1. NACA 0008 2. NACA 0018 3. AG04 4. Clark-Y 5. NACA 2415 Angle of attacks taken to be between 0 degree to 15 degree. Also calculate value of Cm at quarter chord. (Cm at 0.25c) for each. Reynolds ...Parser. (clarkx-il) CLARK X AIRFOIL. CLARK X airfoil. Max thickness 11.7% at 30% chord. Max camber 3.3% at 40% chord. Source UIUC Airfoil Coordinates Database. Source dat file. The dat file is in Lednicer format. CLARK X AIRFOIL 17.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. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at ... The airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber). Airfoils were examined for lift and drag performance as well as surface pressure and flow field characteristics.\ \ \ \ \ \ \ Eppler E330 flying wing airfoil \ \ \ \ \ Eppler E331 flying wing airfoil \ \ Eppler E333 flying wing airfoil \ \ \ \ \ Eppler E335 flying wing airfoil \ \ \ \ \ Eppler E342 flying wing airfoil \ \ \ \ \ Eppler E426 airfoil \ \ Eppler E432 sailplane airfoil \ \ \ \ \ Eppler E433 sailplane airfoil \ \ \ \ \ Eppler E435 sailplane air... Hi. I'm new at the board and I,m needing the X,Y coordinates for a Clark Y airfoil with the following dimensions. Wingspan = 10 meters. Center chord = 2102 mm. with a Clark Y 20% thickness at 30% of chord. Wingtip chord = 1002mm. with a Clark Y 9% thickness at 30% of chord. The rounded wingtips will be added on the wingtip chord.Back to Results. Characteristics of Clark Y airfoils of small aspect ratios 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 0.5 to 3. An airfoil of rectangular plan form was tested with rectangular tips, flared ...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”. Note that for the symmetrical shape the lift coefficient is zero at zero angle of attack. These graphs show test results for several different Reynolds ... Airfoil comparison; Reynolds number calc; NACA 4 digit generator; NACA 5 digit generator; Information. Airfoil data; Lift/drag polars; Generated airfoil shapes; Searches. Symmetrical airfoils; NACA 4 digit airfoils; NACA 5 digit airfoils; NACA 6 series airfoils; Airfoils A to Z. A a18 to avistar (88) B b29root to bw3 (22) C c141a to curtisc72 ... of Clark Y basic section, were made of laminated mahogany; the auxiliary airfoils, because of their small size, were made of aluminum alloy. The ordi- nates of the wooden sections were held accurate to within 10.01 inch and those of the metal portion, to within 3 0.003 inch. The metal auxiliary airfoils were The airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber). Airfoils were examined for lift and drag performance as well as surface pressure and flow field characteristics.Figure 1.—Diagrams of wind and force vectors acting at airfoil sections of fan and wind turbine blades. Appendix A presents a review of the nomenclature and interaction of wind and force vectors in these figures. Appendix B contains the contours of the NREL S809 and Clark-Y airfoils in the sampleParser. (clarkz-il) CLARK Z AIRFOIL. CLARK Z airfoil. Max thickness 11.8% at 30% chord. Max camber 4% at 40% chord. Source UIUC Airfoil Coordinates Database. Source dat file. The dat file is in Lednicer format. CLARK Z AIRFOIL 17. the aerodynamic data .for airfoils tested in th_'_variable-density tunnel since January 1, 1931. INTRODUCTION A large number of miscellaneous airfoils not included in the systematic investigations reported in references 1 and 2 have been tested in the variable-density tunnel. The larger part of these airfoils consists of unrelatedJan 26, 2022 · If I were to want better than 2 significant digits of accuracy, I'd turn to someone that wins contests with his air foils on model gliders versus trying to use full-scale foils like NACA Laminar flow foils, NACA 4-digit, or even Clark-Y airfoils. Abstract: This note gives the aerodynamic characteristics of the N.A.C.A. 97, Clark Y, and N.A.C.A.-M6 airfoil sections as determined in the variable density wind tunnel al Langley Field, Virginia. Particular attention is called to the relation of the characteristics to the angle of attack in their use in airplane design NACA 63-412 AIRFOIL - NACA 63 (1)-412 airfoil. Plot and print the shape of an airfoil (aerofoil) for your specific chord width and transformation. 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.3.3 Clark Y-14 Airfoil and Wing Models ..... 39 Chapter 4: Two-Dimensional Wall Corrections for the Clark Y-14 Airfoil ... 3 for a number of bodies ...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. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at velocities between 25 and 118 miles per hour, and the characteristics were obtained for Reynolds numbers (based on the airfoil chord) in the ...analysis of the Clark Y airfoil’s behavior under medium speed conditions. IJERT Figure 3. Geometry of the selected airfoil B. Meshing Meshing is the discretization or dividing the geometry into number of nodes and elements. The value change in the adjacent elements drastically vary near the solid object,University of Illinois Urbana-Champaign Jan 26, 2022 · If I were to want better than 2 significant digits of accuracy, I'd turn to someone that wins contests with his air foils on model gliders versus trying to use full-scale foils like NACA Laminar flow foils, NACA 4-digit, or even Clark-Y airfoils. clark y airfoil 61. 61. 0.000000 0.000000 0.000500 0.002339 0.001000 0.003727 0.002000 0.005803 0.004000 0.008924 0.008000 0.013735 0.012000 0.017858 0.020000 0.025374 0.030000 0.033022 0.040000 0.039128 0.050000 0.044275 0.060000 0.048757 0.080000 0.056431 0.100000 0.062998 0.120000 0.068620 0.140000 0.073436 0.160000 0.077571 0.180000 0.081069 0.200000 0.083920 0.220000 0.086143 0.240000 0. ... Calculate the lift and moment coefficients using thin airfoil theory approximations for a range of angle of attacks for the following airfoils below. 1. NACA 0008 2. NACA 0018 3. AG04 4. Clark-Y 5. NACA 2415 Angle of attacks taken to be between 0 degree to 15 degree. Also calculate value of Cm at quarter chord. (Cm at 0.25c) for each. Reynolds ...The Clark-Y is a cambered airfoil that performs well at low and medium Reynolds numbers, having a maximum thickness of 11.7% at 28% of the chord. Five different test models are the subjects of ...University of Illinois Urbana-Champaign Dearborn, Clinton H The effect of rivet heads on the characteristics of a 6 by 36 foot Clark Y metal airfoil NACA TN-461 May 1933; Theodorsen, Theodore Clay, William C Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil NACA Report 403 1933The NACA 4 digit and 5 digit airfoils were created by superimposing a simple meanline shape with a thickness distribution that was obtained by fitting a couple of popular airfoils of the time: +- y = (t/0.2) * (.2969*x0.5 - .126*x - .3537*x2 + .2843*x3 - .1015*x4) 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. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at ... Abstract: This note gives the aerodynamic characteristics of the N.A.C.A. 97, Clark Y, and N.A.C.A.-M6 airfoil sections as determined in the variable density wind tunnel al Langley Field, Virginia. Particular attention is called to the relation of the characteristics to the angle of attack in their use in airplane designThe Clark Y airfoil is a great choice for the RC model airplane designer. The Clark Y has high camber, which allows for an efficient lift to drag ratio on a typical lightweight RC model. For the benefit of all users of this airfoil, the Clark Y offers predictable and gentle stall characteristics. Finished Clark Y outline and two examples of a ...Reynolds number - These range from 50,000 to 1,000,000 in approximatly logarithmic steps. The Reynolds number is a dimensionless value that depends on the velocity, wing chord and fluid. There is more information on the Reynolds number calculator page. Ncrit value - This is used to model of the turbulence of the fluid or roughness of the airfoil.Airfoil comparison; Reynolds number calc; NACA 4 digit generator; NACA 5 digit generator; Information. Airfoil data; Lift/drag polars; Generated airfoil shapes; Searches. Symmetrical airfoils; NACA 4 digit airfoils; NACA 5 digit airfoils; NACA 6 series airfoils; Airfoils A to Z. A a18 to avistar (88) B b29root to bw3 (22) C c141a to curtisc72 ...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 0.5 to 3. An airfoil of rectangular plan form was tested with rectangular tips, flared tips, and semicircular tips. Tests were also made on one airfoil of circular plan form and two airfoils of elliptical plan form ...the aerodynamic data .for airfoils tested in th_'_variable-density tunnel since January 1, 1931. INTRODUCTION A large number of miscellaneous airfoils not included in the systematic investigations reported in references 1 and 2 have been tested in the variable-density tunnel. The larger part of these airfoils consists of unrelatedCLARK Y AIRFOIL - CLARK Y airfoil. Plot and print the shape of an airfoil (aerofoil) for your specific chord width and transformation. 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. Open full size plan in new window. Parser. (clarkx-il) CLARK X AIRFOIL. CLARK X airfoil. Max thickness 11.7% at 30% chord. Max camber 3.3% at 40% chord. Source UIUC Airfoil Coordinates Database. Source dat file. The dat file is in Lednicer format. CLARK X AIRFOIL 17.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”. Note that for the symmetrical shape the lift coefficient is zero at zero angle of attack. These graphs show test results for several different Reynolds ... Parser. (clarky-il) CLARK Y AIRFOIL. CLARK Y airfoil. Max thickness 11.7% at 28% chord. Max camber 3.4% at 42% chord. Source UIUC Airfoil Coordinates Database. Source dat file. The dat file is in Lednicer format. the aerodynamic data .for airfoils tested in th_'_variable-density tunnel since January 1, 1931. INTRODUCTION A large number of miscellaneous airfoils not included in the systematic investigations reported in references 1 and 2 have been tested in the variable-density tunnel. The larger part of these airfoils consists of unrelated 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 profile was designed in 1922 by Virginius E. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. [1]NACA 4412 - NACA 4412 airfoil. Details. Dat file. Parser. (naca4412-il) NACA 4412. NACA 4412 airfoil. Max thickness 12% at 30% chord. Max camber 4% at 40% chord. Source UIUC Airfoil Coordinates Database. Jan 26, 2022 · If I were to want better than 2 significant digits of accuracy, I'd turn to someone that wins contests with his air foils on model gliders versus trying to use full-scale foils like NACA Laminar flow foils, NACA 4-digit, or even Clark-Y airfoils. ate the Clark Y or RAF 6 airfoil series during the initial 50% of the blade transitionlmg to the NACA 16 series which has a high drag divergence Mach number in the outer segment of the propeller where the resultant Mach numbers can approach unity. Bocci (Ref. 13) in a paper published in 1977 described a new series ofThe airfoil for aerodynamic analysis (figure 1.3) is derived from Clark Y, has the characteristics shown in Table 1.1 and is often used in the construction of flying wings due to stability characteristics (due to reflex flight board) but also low speed aircraft in classic aerodynamic configuration.The airfoil shapes may vary with span. Capability exists to smoothly “splice” together widely different airfoil shapes. The dominant basis for the primary airfoil shape used in most APC propellers is similar to the NACA 4412 and Clark-Y airfoils, except the leading edge is somewhat lower. Also, the aft region is somewhat thicker.The Aerodynamic Characteristics of Full-Scale Propellers Having 2, 3 and 4 Blades of Clark Y and R.A.F. 6 Airfoil Sections, NACA Report No. 640., NACA-TR-640, January 1938. Theorie Generale de l ...The airfoil shapes may vary with span. Capability exists to smoothly “splice” together widely different airfoil shapes. The dominant basis for the primary airfoil shape used in most APC propellers is similar to the NACA 4412 and Clark-Y airfoils, except the leading edge is somewhat lower. Also, the aft region is somewhat thicker.APC Slowflyer is well made for speeds at low Reynolds number due to its blade's design composed of 2 airfoils (i.e. the Eppler E63 and Clark Y). The Eppler E63 airfoil will be replaced with seven ... p--Reynolds Number, where 1 is a linear dimension. e. g., for a model airfoil 3 in. chord, 100 mi./hr. normal pressure, at 15’ C., the D correspondkg number is 334,000 ; Pb or for a model of 10 cm chord 40 m/s, D the corresponding number is 274,000. qs C,, Center of pressure coefficient (ratio ofthe aerodynamic data .for airfoils tested in th_'_variable-density tunnel since January 1, 1931. INTRODUCTION A large number of miscellaneous airfoils not included in the systematic investigations reported in references 1 and 2 have been tested in the variable-density tunnel. The larger part of these airfoils consists of unrelatedClark Y airfoil Pros and Cons: The flat bottom streamlines the angle measurements for propellers and makes it simple to create wings. For several applications, the Clark Y was a suitable airfoil segment; it offers fair overall efficiency in terms of its lift-to-drag ratio and has soft and relatively benign stall characteristics.Input Value 1 Velocity of Flow 18.77 m/s Fig 5: Medium Meshing on Clark Y Airfoil 2 Mach Number 0.05 Mach 3 Operating Temperature 288.16 K Operating Pressure 101325 Pa. 4 Type of Flow Turbulent 5 Regime Subsonic 6 Density of Flow 1.225 kg/m3 7 Kinematic Viscosity 1.4607 x 10-5 m2/s 8 Angle of Attack 0° - 18° 9 Reynolds’s number 3.2 x 105 10 ...The Clark Y airfoil is a great choice for the RC model airplane designer. The Clark Y has high camber, which allows for an efficient lift to drag ratio on a typical lightweight RC model. For the benefit of all users of this airfoil, the Clark Y offers predictable and gentle stall characteristics. Finished Clark Y outline and two examples of a ...system consists of a series of 4, 5 and 6 digit airfoils. 4-digit airfoils ( e.g. NACA 2415): 2 - maximum camber is 0.02% over the chord, 4 - the location of the maximum camber along the chord line given as 0.4c 15 - the maximum thickness, here 0.15c 5-digit airfoils (e.g. NACA 23021): 2 - maximum camber is 0.02% over the chord, Airfoil comparison; Reynolds number calc; NACA 4 digit generator; NACA 5 digit generator; Information. Airfoil data; Lift/drag polars; Generated airfoil shapes; Searches. Symmetrical airfoils; NACA 4 digit airfoils; NACA 5 digit airfoils; NACA 6 series airfoils; Airfoils A to Z. A a18 to avistar (88) B b29root to bw3 (22) C c141a to curtisc72 ...Jan 26, 2022 · If I were to want better than 2 significant digits of accuracy, I'd turn to someone that wins contests with his air foils on model gliders versus trying to use full-scale foils like NACA Laminar flow foils, NACA 4-digit, or even Clark-Y airfoils. Airfoil database search; My airfoils; Airfoil plotter; Airfoil comparison; Reynolds number calc; NACA 4 digit generator; NACA 5 digit generator; Information. Airfoil data; Lift/drag polars; Generated airfoil shapes; Searches. Symmetrical airfoils; NACA 4 digit airfoils; NACA 5 digit airfoils; NACA 6 series airfoils; Airfoils A to Z. A a18 to ...3.3 Clark Y-14 Airfoil and Wing Models ..... 39 Chapter 4: Two-Dimensional Wall Corrections for the Clark Y-14 Airfoil ... 3 for a number of bodies ...If I were to want better than 2 significant digits of accuracy, I'd turn to someone that wins contests with his air foils on model gliders versus trying to use full-scale foils like NACA Laminar flow foils, NACA 4-digit, or even Clark-Y airfoils.results that use the original “flat bottom” airfoil definitions. Just a few examples using the Clark Y airfoil in my collect are NACA R 427, R 428 and R 431. If you use these results you need to understand the proper airfoil reference lines. To complete the story, take a look at Whitcomb’s Supercritical Airfoils. To get the lift he wantedThe NACA 4 digit and 5 digit airfoils were created by superimposing a simple meanline shape with a thickness distribution that was obtained by fitting a couple of popular airfoils of the time: +- y = (t/0.2) * (.2969*x0.5 - .126*x - .3537*x2 + .2843*x3 - .1015*x4) Oct 10, 2000 · Dearborn, Clinton H The effect of rivet heads on the characteristics of a 6 by 36 foot Clark Y metal airfoil NACA TN-461 May 1933; Theodorsen, Theodore Clay, William C Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil NACA Report 403 1933 Airfoils. Airfoils of U S and Canadian Aircraft. by David Lednicer. Conventional Aircraft: Wing Root Airfoil Wing Tip Airfoil Abrams Explorer NACA 23018 NACA 23009 Ace Baby Ace Clark Y mod Clark Y mod Adam Aircraft A500 CarbonAero Hatfield SC-309-0119 Hatfield SC-309-0117 Aero 145 Aero 58-64 Aero 58-64 Aero Commander 1121 NACA 64A212 NACA ... 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 ... The NACA 4 digit and 5 digit airfoils were created by superimposing a simple meanline shape with a thickness distribution that was obtained by fitting a couple of popular airfoils of the time: +- y = (t/0.2) * (.2969*x 0.5 - .126*x - .3537*x 2 + .2843*x 3 - .1015*x 4 )ate the Clark Y or RAF 6 airfoil series during the initial 50% of the blade transitionlmg to the NACA 16 series which has a high drag divergence Mach number in the outer segment of the propeller where the resultant Mach numbers can approach unity. Bocci (Ref. 13) in a paper published in 1977 described a new series ofUser page server for CoEThe airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber). Airfoils were examined for lift and drag performance as well as surface pressure and flow field characteristics.Oct 10, 2000 · Dearborn, Clinton H The effect of rivet heads on the characteristics of a 6 by 36 foot Clark Y metal airfoil NACA TN-461 May 1933; Theodorsen, Theodore Clay, William C Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil NACA Report 403 1933 Analysis of an NACA - Global JournalsThe airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber).The result of shape evolution based on the Clark Y airfoil, showing the profile and calculated performance comparison. The parameters are B = 1.8761, T = 0.1138, P = 3, 041, C = 0.03869, E = 0. ...Abstract: This note gives the aerodynamic characteristics of the N.A.C.A. 97, Clark Y, and N.A.C.A.-M6 airfoil sections as determined in the variable density wind tunnel al Langley Field, Virginia. Particular attention is called to the relation of the characteristics to the angle of attack in their use in airplane designNov 25, 2020 · They became the NACA 4-digit airfoils. The NACA 2412 is almost exactly the same as the Clark Y. Later, the 5-digit series was created from mathematical analysis. The 6-series so-called "laminar flow" sections took it even further, with airfoils very high lift/drag ratios, but only in a narrow AOA range.
CLARK Y AIRFOIL - CLARK Y airfoil. Plot and print the shape of an airfoil (aerofoil) for your specific chord width and transformation. 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. Open full size plan in new window. . Ribbed white tank top men
They became the NACA 4-digit airfoils. The NACA 2412 is almost exactly the same as the Clark Y. Later, the 5-digit series was created from mathematical analysis. The 6-series so-called "laminar flow" sections took it even further, with airfoils very high lift/drag ratios, but only in a narrow AOA range.Analysis of an NACA - Global Journals \ \ \ \ \ \ \ Eppler E330 flying wing airfoil \ \ \ \ \ Eppler E331 flying wing airfoil \ \ Eppler E333 flying wing airfoil \ \ \ \ \ Eppler E335 flying wing airfoil \ \ \ \ \ Eppler E342 flying wing airfoil \ \ \ \ \ Eppler E426 airfoil \ \ Eppler E432 sailplane airfoil \ \ \ \ \ Eppler E433 sailplane airfoil \ \ \ \ \ Eppler E435 sailplane air... Dec 15, 2017 · The airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber). Airfoils were examined for lift and drag performance as well as surface pressure and flow field characteristics. Mar 27, 2013 · Views: 128. Pic 2 The Clark Y chord is lower and parallel to the 2412 chord. An attempt at matching the airfoils thickness (height) together. We could say the Clark Y is a NACA 4412 or real close to that. Views: 145. Pic 3 While matching the thickness the Clark Y is rotated for the chord front to coincide. naca m2 airfoil m20: naca m20 airfoil m21: naca m21 airfoil m22: naca m22 airfoil m23: naca m23 airfoil m24: naca m24 airfoil m25: naca m25 airfoil m26: naca m26 airfoil m27: naca m27 airfoil m3: naca m3 airfoil m4: naca m4 airfoil m5: naca m5 airfoil m6: naca m6 airfoil m665: m6 (65%) m685: m6 (85%) m7: naca m7 airfoil m8: naca m8 airfoil m9Airfoil comparison; Reynolds number calc; NACA 4 digit generator; NACA 5 digit generator; Information. Airfoil data; Lift/drag polars; Generated airfoil shapes; Searches. Symmetrical airfoils; NACA 4 digit airfoils; NACA 5 digit airfoils; NACA 6 series airfoils; Airfoils A to Z. A a18 to avistar (88) B b29root to bw3 (22) C c141a to curtisc72 ... Consider a 3-bladed propeller, D = 2.5 m with a Clark-Y airfoil whose characteristics are described in NACA TR-640 (see Propellers folder on Canvas). (Watch for number of blades! Use Figs. 9-11). The propeller is mounted on a single engine airplane cruising at 134 m/s (~300 mph) in air that has a density of 0.909 kg/m' and temperature of 269 K ...Changes in plan form of the flat-plate airfoils gave erroneous indications of the effect to be expected from changes in plan form of an airfoil of Clark Y section. The minimum drag characteristics of the circular Clark Y airfoils were found to be substantially the same as for a Clark Y airfoil of conventional aspect ratio.University of Illinois Urbana-Champaign Federal Aviation AdministrationOct 1, 2016 · An experimental wind tunnel investigation was undertaken to determine the effect of Gurney flap on the aerodynamic characteristics of Clark y-14 airfoil wing at a Reynolds number of 2.1x10 5. The ... inches where they connect to the airfoil. Three metal Clark Y airfoils with 4-, 6-, (ml 8-foot chords and of aspect ratio 6 were used. The airfoil covering of J&inch Aminum sheet wns attached to o rigid internal structure by means of flush countersunk screws. The sparsweresteelbeams and theprofilewas formed by aluminum ribs spaced at M-inch ....