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Wind Tunnel Investigation of Control Surface Characteristics: [Part] 12 - Various Cover-Plate Alinements on the NACA 0015 Airfoil With a 30 Percent Chord Flap and Large Sealed Internal Balance

Description: Report presenting force-test measurements in two-dimensional flow made in the 4- by 6-foot vertical tunnel to determine the aerodynamic effects of changing the alignment of the cover plates on a sealed internally balanced flap. Manufacturing imperfections in the alignment of the cover plates with the airfoil contour may have serious effects on the resultant hinge moment of a flap with a sealed internal balance. Results regarding lift, flap hinge moments, pitching moment, and drag are provided.
Date: January 1943
Creator: Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Control-Surface Characteristics: [Part] 18 - A Linked Overhang Aerodynamic Balance

Description: Report presenting wind-tunnel testing in two-dimensional flow to investigate the aerodynamic characteristics of a flap balanced by a large overhang linked to deflect more slowly than the flap. Three lengths of blunt-nose overhang were tested linked to a 0.30-airfoil-chord straight-contour flap on an NACA 66-009 airfoil. Results regarding lift, hinge moment, drag, pitching moment, and practical considerations are provided.
Date: February 1944
Creator: Sears, Richard I. & Liddell, Robert B.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics: [Part] 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 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 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 control-surface characteristics 1: effect of gap on the aerodynamic characteristics of an NACA 0009 airfoil with a 30-percent-chord plain flap

Description: From Summary: "Tests have been made to determine the effect of a gap at the flap nose upon the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap and tab. The results are presented in the form of airfoil and flap section characteristics for several flap deflections, tab deflections, and for four sizes of gap."
Date: June 1941
Creator: Sears, Richard I.
Partner: UNT Libraries Government Documents Department

Wind tunnel investigation of control surface characteristics 9: some analytical considerations and experimental test results for an internally balanced flap

Description: Report presenting an analysis of the probable aerodynamic section characteristics of a plain flap with various arrangements of internal balance. The results of the calculations previously obtained were found to be in agreement with the experiment. Some possible applications of the data to balancing tabs are also provided.
Date: July 1942
Creator: Sears, Richard I.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics 13: various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Description: Report presenting force tests in two-dimensional flow made on an NACA 66-009 airfoil with a flap having a chord 30 percent of the airfoil chord and a tab having a chord 20 percent of the flap chord. A plain flap and flaps having overhangs of 35 and 50 percent of the flap chord were tested with two gap variations: sealed and unsealed. Results regarding lift, flap hinge moments, pitching moments, drag, and tab characteristics are provided.
Date: July 1943
Creator: Gillis, Clarence L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics 19: a double flap with an overhang and an internal aerodynamic balance

Description: Report presenting wind-tunnel tests in two-dimensional flow to investigate the aerodynamic characteristics of a double flap with an internal and overhang balance. Three sizes of each type of balance were tested with three relative rates of deflection of the two flaps. Results regarding lift, hinge moment, drag, and pitching moment are provided.
Date: June 1944
Creator: Liddell, Robert B.
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 the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

Description: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
Date: February 1943
Creator: Purser, Paul E. & Toll, Thomas A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics 6: a 30-percent-chord plain flap on the NACA 0015 airfoil

Description: Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel of the characteristics of an NACA 0015 airfoil equipped with a plain flap with a chord 30 percent of the airfoil chord and a plain tab with a chord 20 percent of the flap chord. Results regarding lift, hinge moment of flap, pitching moment, drag, and tab characteristics are provided.
Date: June 1942
Creator: Sears, Richard I. & Liddell, Robert B.
Partner: UNT Libraries Government Documents Department

Wind tunnel investigation of control-surface characteristics 10: a 30-percent-chord plain flap with straight contour on the NACA 0015 airfoil

Description: Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the characteristics of an NACA 0015 airfoil equipped with a straight-contour plain flap with a chord 30 percent of the airfoil chord. Results regarding the lift, hinge moment of flap, pitching moment, and drag are provided.
Date: September 1942
Creator: Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics 17: beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil

Description: Report presenting force tests in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 airfoil with flaps having chord at 3 locations of the airfoil chord and three degrees of the beveled trailing edges. The results indicated that, with a smooth leading edge, the increased trailing-edge angle on the flaps with sealed gaps decreased the slope of the control-fixed lift curve and the lift effectiveness.
Date: April 1944
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department

Fatigue Strength of Flush-Riveted Joints for Aircraft Manufactured by Various Riveting Methods

Description: Report presenting the results of an investigation to determine the fatigue strength of flush-riveted joints manufactured by different riveting methods. Tests were made on a direct stress fatigue machine at room temperature. The results showed that the fatigue strength of the joints was directly affected by the method of riveting used.
Date: December 1945
Creator: Maney, G. A. & Wyly, L. T.
Partner: UNT Libraries Government Documents Department

Impact Properties at Different Temperatures of Flush-Riveted Joints for Aircraft Manufactured by Various Riveting Methods

Description: Report presenting the results of an investigation to determine the impact properties of flush-riveted joints manufactured by different riveting methods. Testing occurred on a pendulum impact machine at temperatures of 70, -50, and -70 degrees Fahrenheit using rivets made of aluminum alloy A17S-T and plates of aluminum alloy 24S-T.
Date: September 1945
Creator: Maney, G. A. & Wyly, L. T.
Partner: UNT Libraries Government Documents Department