National Advisory Committee for Aeronautics (NACA) - 4,107 Matching Results

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Wind-tunnel investigation of two airfoils with 25-percent-chord Gwinn and plain flaps

Description: Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the overall chord and of an NACA 23015 airfoil with a plain flap having a 25-percent chord were conducted to determine the relative merits of the Gwinn and the plain flaps. The tests indicated that, based on speed-range ratios, the plain flap was more effective than the Gwinn flap. At small flap deflections, the plain flap had lower drag coefficients at lift-coefficient values less than 0.70. For lif… more
Date: May 1940
Creator: Ames, Milton B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of unshielded horn balances on a horizontal tail surface

Description: Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a horizontal tail surface with various amounts of unshielded horn balance and with the surface condition similar to that of a typical fabric-covered elevator.
Date: July 1947
Creator: Lowry, John G. & Crandall, Stewart M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Results regarding the methods of analysis and vertical-tail contributions are provided.
Date: November 1956
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Measurements of Air Loads on Split Flaps

Description: Note presenting tests in a wind tunnel to determine the control forces and air loads acting on split flaps. Clark Y wing models were used with two different sizes of full-span split flaps, one with a medium chord and one with a narrow chord. The results indicated that at angles of attack and flap deflections for maximum lift, the lift loads on the split flaps were only 5 percent and 9 percent of the total lift for the narrow and medium-chord flaps respectively.
Date: May 1934
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel of Three Lateral-Control Devices in Combination With a Full-Span Slotted Flap on an NACA 23012 Airfoil

Description: "A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section, and two-dimensional flow was approximated. The model was fitted with a full-span slotted flap having a chord 25.66 percent of the airfoil chord. The ailerons investigated extended over the entire span and each had a chord 10 percent of the airfoil chord" (p. 1).
Date: August 1938
Creator: Wenzinger, Carl J. & Bamber, Millard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Pressure Distribution Tests on a Series of Biplane Wing Models Part I: Effects of Changes in Stagger and Gap

Description: This report is on the changes in forces on each wing of a biplane cellule when either the stagger or the gap is varied. Since each test was carried up to a 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning as well as in the structural design of biplane wings.
Date: July 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel pressure distribution tests on a series of biplane wing models Part II: effects of changes in decalage, dihedral, sweepback and overhang

Description: This preliminary report furnishes information on the changes in the forces on each wing of a biplane cellule when the decalage, dihedral, sweepback and overhang are separately varied. The data were obtained from pressure distribution tests made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. Since each test was carried up to 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning and in the structural design of biplane wi… more
Date: October 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel pressure distribution tests on a series of biplane wing models Part III: effects of charges in various combinations of stagger, gap, sweepback, and decalage

Description: A concept for the calculation of the vortex lift of sharp-edge delta wings is presented and compared with experimental data. The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge. This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent predi… more
Date: December 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Pressure Distribution Tests on an Airfoil With Trailing Edge Flap

Description: "This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement" (p. 1).
Date: October 1929
Creator: Wenzinger, Carl J. & Loeser, Oscar, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 8: Straight and Skewed Ailerons on Wings With Rounded Tips

Description: Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, as well as on the lateral control and stability characteristics. The hinge moments were not measured but the approximate values are given in the first report of the series.
Date: February 1933
Creator: Weick, Fred E. & Shortal, Joseph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 9: Tapered Wings With Ordinary Ailerons

Description: Tests were made with ordinary flap-type ailerons on two wings with different amounts of taper, one medium and the other extreme. On each wing both medium sized tapered ailerons and short wide tapered ailerons were tested.
Date: February 1933
Creator: Weick, Fred E. & Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel research comparing lateral control devices, particularly at high angles of attack 10: various control devices on a wing with a fixed auxiliary airfoil

Description: Results are given of a series of systemic tests comparing lateral control devices with particular reference to their effectiveness at high angles of attack. These tests were made with two sizes of ordinary ailerons and different sizes of spoilers on a Clark Y wing model having a narrow auxiliary airfoil fixed ahead and above the leading edge, the chords of the main and auxiliary airfoils being parallel. In addition, the auxiliary airfoil itself was given angular deflection. The purpose was to p… more
Date: March 1933
Creator: Weick, Fred E. & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel research comparing lateral control devices, particularly at high angles of attack 11: various floating tip ailerons on both rectangular and tapered wings

Description: Discussed here are a series of systematic tests being conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present tests were made with six different forms of floating tip ailerons of symmetrical section. The tests showed the effect of the various ailerons on the general performance characteristics of the wing, and on the lateral controllability and stability characteristics. In addition, the hinge moments were mea… more
Date: May 1933
Creator: Weick, Fred E. & Harris, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Research Concerning Lateral Control Devices, Particularly at High Angles of Attack 7: Handley Page Tip and Full-Span Slots With Ailerons and Spoilers

Description: Tests were made with ordinary ailerons and different sizes of spoilers on rectangular Clark Y wing models with Handley Page tip and full span slots. The tests showed the effect of the control devices on the general performance of the wings as well as on the lateral control and lateral stability characteristics.
Date: January 1933
Creator: Weick, Fred E. & Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Standardization Disk Drag

Description: Note presenting the resistances of a series of three similar disks placed normal to the wind as determined in the atmospheric wind tunnel. The curves of drag coefficient plotted against Reynolds number for this tunnel show discrepancies between overlapping values which are to be attributed to the presence of the tunnel walls.
Date: December 1926
Creator: Knight, Montgomery
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel studies of the performance of multirotor configurations

Description: Report presenting the power requirements measured in static thrust and in level forward flight for two helicopter rotor configurations. One is a coaxial rotor arrangement with the rotors spaced approximately 19 percent of the rotor radius; the other is a tandem configuration in which the rotor-shaft spacing is 3 percent greater than the rotor diameter and in which the rotors lie in the same plane.
Date: August 1954
Creator: Dingeldein, Richard C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Technique for Simultaneous Simulation of External Flow Field About Nacelle Inlet and Exit Airstreams at Supersonic Speeds

Description: Report presenting an investigation of several ways of simultaneously simulating the external pressure field generated by an engine exhaust jet and an air inlet. The results indicated that the pressure field in the vicinity of the exit station and external to a real exhaust jet could be adequately simulated while keeping the inlet at critical or supercritical mass flow. Results for a target probe, a perforated probe, and the pressure and airflow required in the probes are provided.
Date: January 1957
Creator: Englert, Gerald W. & Luidens, Roger W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests and Analysis of Two 10-Foot-Diameter Six-Blade Dual-Rotating Tractor Propeller Differing in Pitch Distribution

Description: Report presenting an investigation to determine the efficiency at low tip speeds of two 10-foot-diameter six-blade dual-rotating propellers differing only in pitch distribution. Propeller forces were determined from wind tunnel testing and by using an analytical method using two-dimensional airfoil section data. Results regarding propeller characteristics, analysis of energy losses, and design considerations are provided.
Date: June 1948
Creator: Gilman, Jean, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests at low speed of swept and yawed wings having various plan forms

Description: Results are presented of wind-tunnel tests made at low speed of various small-scale models of sweptback, sweptforward, and yawed wings. The tests covered changes in aspect ratio, taper ratio, and tip shape. Some data were obtained with high-lift devices on sweptback wings and with ailerons on sweptforward wings. The data have been briefly analyzed and some comparisons have been made with the available theory.
Date: December 1951
Creator: Purser, Paul E. & Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a 2-Engine Airplane Model as a Preliminary Study of Flight Conditions Arising on the Failure of the Engine

Description: "Wind tunnel tests of a 15-foot-span model of a two-engine low wing transport airplane were made as a preliminary study of the emergency arising from the failure of one engine in flight. Two methods of reducing the initial yawing moment resulting from the failure of one engine were investigated and the equilibrium conditions were explored for two basic modes on one engine, one with zero angle of sideslip and the other with several degrees of sideslip. The added drag resulting from the unsymmetr… more
Date: April 1938
Creator: Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of a Clark Y Wing Having Split Flaps With Gaps

Description: "Tests were made of the Clark Y wing having split flaps with a gap between the flap and the lower surface of the wing. Lift, drag, and pitching moments were measured for the wing with three different sizes of flap. It was found that any gap between the flap and the wing reduced the lift, the drag, and the pitching moments, but that the center-of-pressure movement and the ratio of lift to drag were little affected" (p. 1).
Date: May 1938
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a Clark Y wing with "Maxwell" leading-edge slots

Description: Aerodynamic force tests of a Clark Y wing equipped with "Maxwell" type leading-edge slots were conducted in the N.A.C.A. 7- by 10-foot tunnel to ascertain the aerodynamic characteristics, which involved the determination of the best slot-gap opening, the effects of slat width, and the effect of a trailing-edge flap. The Maxwell wing with a wide-chord slat (0.30 c(sub w)) and with a 0.211 c(sub w) split flap deflected 60 degrees had a C(sub L sub max) of 2.53 or about twice that of the plain win… more
Date: April 1937
Creator: Gauvain, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a cyclogiro rotor

Description: During an extensive study of all types of rotating wings, the NACA examined the cyclogiro rotor and made an aerodynamic analysis of that system (reference 1). The examination disclosed that such a machine had sufficient promise to justify an experimental investigation; a model with a diameter and span of 8 feet was therefore constructed and tested in the 20-foot wind tunnel during 1934. The experimental work included tests of the effect of the motion upon the rotor forces during the static-lift… more
Date: May 1935
Creator: Wheatley, John B. & Windler, Ray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a full-scale helicopter rotor with symmetrical and with cambered blade sections at advance ratios from 0.3 to 0.4

Description: Report presenting wind tunnel testing of a 44-foot-diameter, three-bladed helicopter rotor to investigate the performance gains made available by delaying retreating blade stall by the use of blade sections with increased maximum lift. Comparison of the stall boundaries showed that blades with cambered sections were superior to blades with symmetrical sections due to the increase in lifting capacity and forward speed capacity. Results regarding the determination of retreating blade stall, stall… more
Date: September 1958
Creator: McCloud, John L., III & McCullough, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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