Technical Report Archive and Image Library (TRAIL) - 1,263 Matching Results

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Wind-tunnel investigation of control-surface characteristics of plain and balanced flaps on an NACA 0009 elliptical semispan wing

Description: Report discusses a series of force tests of a NACA 0009 elliptical semispan wing equipped with a flap that is either 50 percent of the wing area or 30 percent of the wing area. Information about the lift, hinge moment, and drag and pitching moment is provided.
Date: February 1946
Creator: Tamburello, Vito; Smith, Bernard J. & Silvers, H. Norman
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics [part] 14: NACA 0009 airfoil with a 20-percent-chord double plain flap

Description: Report discusses the results of force testing of the aerodynamic characteristics of an NACA 0009 airfoil with a double plain flap; it consisted of a plain forward flap with a chord 20 percent of the airfoil chord and a plan rearward flap with a chord 15 percent of the airfoil chord. Comparisons were made to the characteristics of a 0.50c single plain flap. The lift, hinge moments, drag, and pitching moments are described.
Date: June 1943
Creator: Sears, Richard I. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics [part] 16: pressure distribution over an NACA 0009 airfoil with 0.30-airfoil-chord beveled-trailing-edge flaps

Description: Report discusses pressure-distribution tests of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. From Summary: "The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces."
Date: April 1944
Creator: Hoggard, H. Page, Jr. & Bulloch, Marjorie E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics [part] 22: medium and large aerodynamic balances of two nose shapes and a plain overhang used with a 0.20-airfoil-chord flap on an NACA 0009 airfoil

Description: From Summary: "Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical overhang of 0.35 flap chord."
Date: June 1945
Creator: Riebe, John M. & McKinney, Elizabeth G.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Control-Surface Characteristics XX : Plain and Balanced Flaps on an NACA 0009 Rectangular Semispan Tail Surface

Description: Correlation is established between aerodynamic characteristics of control surfaces in two-dimensional and three-dimensional flow. Slope of lift curve was affected little by overhang and balance-nose shape, but increased by sealing flap-nose gap. Effectiveness of balancing tab was same for sealed plain flap and unsealed overhang flap. Changes in hinge-moment coefficient were diminished by sealing gap. Values measured by three-dimensional flow disagreed with two-dimensional flow values until aspect ratio corrections were made.
Date: October 1944
Creator: Garner, I. Elizabeth
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of devices for improving the diving characteristics of airplanes

Description: Report discussing testing on a model of a pursuit type airplane to determine the effect of several devices that may be applied to improve the high-speed pitching-moment characteristics. Auxiliary flaps, a controllable stabilizer, and a change in wing contour were all found to help increase the amount of control when recovering from high-speed dives.
Date: April 1943
Creator: Erickson, Albert L.
Partner: UNT Libraries Government Documents Department

Wind tunnel investigation of effect of yaw on lateral-stability characteristics 4: symmetrically tapered wing with a circular fuselage having a wedge-shaped rear and a vertical tail

Description: Report presenting testing of combinations of an NACA 23012 tapered wing and a circular fuselage with a wedge-shaped rear to determine the effect of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. Results regarding the lateral stability at small and large angles of yaw are provided.
Date: March 1942
Creator: Recant, I. G. & Wallace, Arthur R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of effect of yaw on lateral-stability characteristics [part] 5: symmetrically tapered wing with a circular fuselage having a horizontal and a vertical tail

Description: Report discussing testing to determine the effect of a horizontal tail on the lateral-stability characteristics of a high-wing, a midwing, and a low-wing monoplane. The model was created from a circular fuselage, an NACA 23012 tapered wing, and an NACA 0009 horizontal tail surface. Information about the effective aspect ratio of the tail, restoring moment of yaw, and vertical-tail effectiveness as compared to the wing position is provided.
Date: June 1943
Creator: Wallace, Arthur R. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing

Description: Report presenting some of the effects of pusher-propeller operation on the aerodynamic characteristics of a flapped wing in the propeller-research tunnel. The effects are primarily related to the effects of propeller inflow on the aerodynamic characteristics of the wing.
Date: April 1945
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of perforated split flaps for use as dive brakes on a rectangular NACA 23012 airfoil

Description: Report presenting an investigation of the aerodynamic characteristics of a rectangular NACA 23012 airfoil with single and double perforated split flaps in the NACA 7- by 10-foot wind tunnel. A large range of flap spans and deflections and a large range of spanwise and chordwise locations of the flaps were investigated. Results regarding the double split flaps, single split flaps, diving speed, and aileron control are provided.
Date: July 1941
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA 23012 Airfoil

Description: Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated that single or double perforated split flaps may be used to obtain satisfactory dive control without undue buffeting effects and that single or double perforated split flaps may also be used as fighter brakes. The perforated split flaps had approximately the same effects on the aerodynamic and wake characteristics of the tapered airfoil as on a comparable rectangular airfoil.
Date: November 1941
Creator: Purser, Paul E. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of plain ailerons for a wing with a full-span flap consisting of an inboard Fowler and an outboard retractable split flap

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of three plain ailerons on an NACA 23012 wing with full-span combinations of Fowler and split-type flaps. Static rolling, yawing, and hinge moments were determined and are presented for several angles of attack and flap deflection. The results indicated that a plain sealed aileron with internal balance will provide lateral control for airplanes equipped with full-span combinations of slotted and split-type flaps.
Date: March 1941
Creator: Harris, Thomas A. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Description: Report presenting the results of flight investigations showing that a beveled trailing-edge aileron gives as low or a lower profile drag than a contour aileron. Section profile drag and lift coefficients with two different types of ailerons were obtained at 3 different Reynolds numbers.
Date: January 1943
Creator: Abbott, Frank T., Jr. & Underwood, William J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of rear underslung fuselage ducts

Description: Report discussing an investigation of cooling ducts at various positions on a model of a typical pursuit airplane in the NACA full-scale tunnel. Results in the report are given for a duct located on the bottom of the fuselage with the inlet behind the leading edge of the wing. Due to the thick boundary layers at the inlets of the rear underslung fuselage duct and the serious pressure losses that resulted, a special vane was also installed to avoid boundary-layer separation.
Date: September 1943
Creator: Czarnecki, K. R. & Nelson, W. J.
Partner: UNT Libraries Government Documents Department