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The effect of Reynolds number on the stalling characteristics and pressure distributions of four moderately thin airfoil sections

Description: Report presenting low-speed measurements of the lift, drag, pitching moment, and pressure distribution of 4 airfoil sections over a range of Reynolds numbers. Results indicated that the nature of the stalls depends on the Reynolds number. Low Reynolds numbers tend to be favorable to the thin-airfoil type of stall while high Reynolds numbers are favorable to to the leading-edge type of stall.
Date: November 1955
Creator: McCullough, George B.
Partner: UNT Libraries Government Documents Department

Stick-Fixed Stability and Control Characteristics of the Consolidated Vultee Model 240 Airplane as Estimated from Tests of a 0.092-Scale Powered Model

Description: From Summary: "Estimates of the static stick-fixed stability and control characteristics of the Consolidated Vultee model 240 airplane are presented in this report. The estimates are based on tests of a 0.092-scale powered model in the 10-foot wind tunnel of the Guggenheim Aeronautical Laboratory of the California Institute of Technology. Results of the analysis are evaluated in terms of the Army specifications for stability and control characteristics which are more specific and, in general, equal to or more rigid than the Civil Aeronautics Administration requirements."
Date: June 27, 1947
Creator: McCullough, George B.; Weiberg, James A. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department

Low-speed characteristics of four cambered, 10-percent-thick NACA airfoil sections

Description: Report presenting a two-dimensional low-speed investigation of four thin, cambered airfoil sections. The data included measurements of lift, drag, pitching moment, and chordwise distribution of pressure. The maximum lift section coefficients, stall, effect of Reynolds number on maximum lift, surface roughness, and increment of maximum lift by a simulated split flap are described in detail.
Date: August 1950
Creator: McCullough, George B. & Haire, William M.
Partner: UNT Libraries Government Documents Department

Boundary-layer and stalling characteristics of the NACA 64A006 airfoil section

Description: Report presenting the boundary-layer and stalling characteristics on an NACA 64A006 airfoil section at a Reynolds number of 5,800,000. Data included measurements of lift, drag, and pitching moment, chordwise distributions of pressure, visual studies of the boundary-layer flow, and surveys of the static-pressure and velocity distribution within the boundary layer. Results regarding force and moment characteristics, pressure distributions, and boundary-layer characteristics are provided.
Date: August 1949
Creator: McCullough, George B. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department

Tests of a heated low-drag airfoil

Description: Report discusses the results of an experimental investigation into the NACA 65,2-016 heated wing. Information about the effect of heating on the drag coefficients, Reynolds numbers, and stability of the laminar boundary layer.
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Partner: UNT Libraries Government Documents Department

Examples of three representative types of airfoil-section stall at low speed

Description: Report presenting force, moment, pressure-distribution, and boundary-layer measurements for a series of five airfoil sections. The stalling characteristics of the three airfoil sections at low speeds can be separated into three types. A deeper discussion of the role of boundary-layer flow and separation processes in relation to stalling and the sensitivity of stall to factors that influence boundary-layer growth is provided.
Date: September 1951
Creator: McCullough, George B. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department

Flying qualities of a twin-engine patrol airplane as estimated from wind-tunnel tests

Description: Report presenting an estimate of the flying qualities of a twin-engine patrol airplane from wind-tunnel test results in comparison with flight observations as a possible guide in determining changes which would be necessary to improve these qualities. Results regarding the longitudinal and lateral stability and control of this airplane are provided.
Date: October 1943
Creator: Stevens, Victor I., Jr.
Partner: UNT Libraries Government Documents Department

An experimental investigation of an NACA 631-012 airfoil section with leading-edge suction slots

Description: Report presenting an NACA 63(sub 1)-012 airofil section equipped with a single suction slot near the leading edge to determine whether the maximum lift coefficient could be increased by delaying the separation of flow at the leading edge characteristics of the basic section. Maximum lift increased with increasing flow through the slot, rapidly at first, and then at a diminishing rate. Results regarding the effect of boundary layer section and the optimum slot are provided.
Date: August 1948
Creator: McCullough, George B. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department

An experimental investigation of the NACA 631-012 airfoil section with leading-edge and midchord suction slots

Description: Report presenting an investigation of using two suction slots in order to determine the effectiveness of a nose slot at higher values of lift. The suction through the midchord slot in conjunction with the nose slot resulted in substantial gains in the maximum lift over that obtainable with nose suction alone. Results regarding the lift, drag, and moment characteristics, pressure distribution, boundary-layer measurements, and plenum-chamber pressures are provided.
Date: February 1950
Creator: McCullough, George B. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the delay of turbulent flow separation by means of wedge-shaped bodies

Description: Report presenting an experimental investigation of pyramidal, wedge-like bodies as devices for delaying separation of a turbulent boundary layer. Within certain limits, effective boundary-layer control was obtainable with wedges of different geometry, but the drag of the wedges was high, making it desirable to keep their size to a minimum. Greater maximum lift was obtainable by placing the wedges well forward along the chord and by allowing open spaces between adjacent wedges.
Date: March 1, 1951
Creator: McCullough, George B.; Nitzberg, Gerald E. & Kelly, John A.
Partner: UNT Libraries Government Documents Department

A method for determining the rate of heat transfer from a wing or streamline body

Description: From Summary: "A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude, for example."
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Partner: UNT Libraries Government Documents Department

A method for determining the rate of heat transfer from a wing or streamline body

Description: A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude. To illustrate the method, the total rate of heat transfer from an airfoil is calculated and compared with the experimental results.
Date: 1945
Creator: Frick, Charles W. & McCullough, George B.
Partner: UNT Libraries Government Documents Department

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 boundary, and comparison of the rotors are provided.
Date: September 1958
Creator: McCloud, John L., III & McCullough, George B.
Partner: UNT Libraries Government Documents Department

Boundary-Layer Measurements on Several Porous Materials With Suction Applied

Description: Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.
Date: June 18, 1952
Creator: McCullough, George B. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department