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Investigation of an Approximately 0.178-Chord-Thick NACA 6-Series-Type Airfoil Section Equipped With Sealed Internally Balanced 0.20-Chord Ailerons and With a 0.05-Chord Tab

Description: Note presenting hinge-moment, lift, and drag measurements made on an approximately 0.178-chord-thick NACA 6-series-type airfoil section equipped with sealed internally balanced 0.20-chord ailerons and with a 0.05-chord tab. The purpose of the investigation was to obtain the effects of aileron contour and internal-balance chord on the aileron section hinge-moment characteristics and to determine the tab effectiveness in reducing the aileron section hinge moments.
Date: May 1948
Creator: Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section

Description: Report presenting an investigation at low speed and high Reynolds number to determine the air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section. Results indicated that the loads on the flap change slowly with variation of angle of attack but quickly with the flap deflected. The main effect of the double-slotted flap is that it causes the airfoil to carry a greater load without stalling.
Date: April 9, 1947
Creator: Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Further experimental studies of area suction for the control of the laminar boundary layer on a porous bronze NACA 64A010 airfoil

Description: Report presenting a low-turbulence wind-tunnel investigation of an NACA 64A010 airfoil with a porous surface to determine the reduction in section total-drag coefficient that can be obtained at large Reynolds numbers by using area suction. While previous testing has been reported on, the focus of this paper is primarily the results of additional tests of the same airfoil model equipped with a porous skin of lower porosity.
Date: May 1950
Creator: Braslow, Albert L. & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of the static stability characteristics of a 1/8-scale ejectable pilot-seat combination at a Mach number of 0.8

Description: Report presenting an investigation of a model of an ejectable pilot seat combination with and without stabilizing fins. The main purpose of the investigation was to determine the static aerodynamic characteristics and effectiveness of various stabilizing fins at a high subsonic Mach number. Results regarding stability and force characteristics for the combinations are provided.
Date: December 7, 1951
Creator: Visconti, Fioravante & Nuber, Robert J.
Partner: UNT Libraries Government Documents Department

Two-dimensional wind-tunnel investigation of two NACA 7-series type airfoils equipped with a slot-lip aileron, trailing-edge frise aileron, and a double slotted flap

Description: Report presenting a wind-tunnel investigation of two NACA 7-series type airfoils, one with 17.7-percent chord thickness and one with 15.4-percent chord thickness, each quipped with a 30-percent-airfoil-chord double slotted flap, a slot-lip aileron, and a trailing-edge Frise aileron with two amounts of overhang balance. Measurements of airfoil lift and drag, Frise aileron hinge moment, and slot-lip aileron hinge moment were obtained through a large range of deflection of flap, Frise aileron, and slot-lip aileron and section angle of attack. Satisfactory lateral control can be obtained by using this combination of airfoils, flaps, and ailerons.
Date: March 28, 1949
Creator: Braslow, Albert L. & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Investigation of boundary-layer Reynolds number for transition on an NACA 65(215)-114 airfoil in the Langley two-dimensional low-turbulence pressure tunnel

Description: A low-turbulence investigation was made of an aerodynamically smooth NACA airfoil with faired surfaces back to 37 percent chord to determine the magnitude of boundary-layer Reynolds number at various points of transition in flow along different airfoil surfaces. Values of the section drag coefficient were also obtained by means of the wake-survey method.
Date: October 1948
Creator: Braslow, Albert L. & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Further Experimental Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil

Description: Note presenting a low-turbulence wind-tunnel investigation of an NACA 64A010 airfoil with a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of area suction. This report primarily deals with additional tests of the same airfoil model equipped with a porous skin of lower porosity.
Date: May 1950
Creator: Braslow, Albert L. & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Investigation of Boundary-Layer Reynolds Number for Transition on an NACA 65 (Sub 215)-114 Airfoil in the Langley Two-Dimensional Low-Turbulence Pressure Tunnel

Description: Note presenting a low-turbulence wind-tunnel investigation made of an aerodynamically smooth NACA 65(sub 215)-114 airfoil with faired surfaces back to 37 percent chord to determine the magnitude of the boundary-layer Reynolds number at various positions of transition from laminar to turbulent flow along both airfoil surfaces. In addition to boundary-layer measurements, values of the section drag coefficient were obtained by means of the wake-survey method.
Date: October 1948
Creator: Braslow, Albert L. & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. The surface of the airfoil that was tested had a lot of waves and irregularities, but the theoretically predicted stabilizing effect of area suction on a smooth flat plate was still observed.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

Experimental and theoretical studies of area suction for the control of the laminar boundary layer on an NACA 64A010 airfoil

Description: From Summary: "A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of suction to produce continuous inflow through the surface of the airfoil (area suction). In addition to the experimental investigation, a related theoretical analysis was made to provide a basis of comparison for the test results."
Date: March 30, 1951
Creator: Braslow, Albert L.; Burrows, Dale L.; Tetervin, Neal & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil

Description: Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department