National Advisory Committee for Aeronautics (NACA) - 1,263 Matching Results

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Lift and Drag Tests of Three Airfoil Models With Fowler Flaps Submitted by Consolidated Aircraft Corporation

Description: Report presenting lift and drag tests made in the two-dimensional tunnel of three airfoil models. The models represented intermediate sections on alternative wings of the XB-32 airplane and were equipped with 0.30 Fowler flaps. Results regarding the Davis model, the C.A.C. model, and low-drag model are provided.
Date: December 1941
Creator: Abbott, Ira H. & Turner, Harold R., Jr.
Partner: UNT Libraries Government Documents Department
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Pressure-Distribution Measurements of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: "Pressure-distribution measurements were made at the request of the Materiel Division, U.S. Army Air Corps, on a 24-inch-chord wooden model equipped with a slotted flap and submitted by the Curtiss-Wright Corporation. The tests were made in the Langley two-dimensional tunnel at a Reynolds number of about 5,600,000" (p. 1).
Date: December 1941
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department
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Pressure distribution over an airfoil with a balanced split flap

Description: Report presenting a pressure-distribution investigation conducted in the 4- by 6-foot vertical wind tunnel to determine the air loads on an airfoil with a 22.1-percent-chord balanced split flap. Results regarding section pressure distribution and aerodynamic section coefficients are provided.
Date: December 1941
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department
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Tank Tests of a 1/5 Full-Size Dynamically Similar Model of the Army OA-9 Amphibian With Motor-Driven Propellers: NACA Model 117

Description: Report presenting an investigation of the influence of running propellers on the hydrodynamic characteristics of a model of a seaplane in the tank to evaluate the importance of power in tests of dynamically similar models. The powered propellers were found to have a large effect on the aerodynamic characteristics of the model and consequently on the hydrodynamic stability, which depends to a certain extent on these characteristics. Generally, the magnitude of the effects of a given increment of… more
Date: December 1941
Creator: Parkinson, John B. & Olson, Roland E.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil

Description: Report presenting an investigation of several modifications of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil in the 7- by 10-foot wind tunnel. Static rolling, yawing, and hinge moments were determined for several angles of attack.
Date: December 1941
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Spoiler-Slot Aileron on an NACA 23012 Airfoil With a Full-Span Fowler Flap

Description: Report presenting an investigation of a spoiler-slot aileron on an NACA 23012 airfoil with a full-span 30-percent-chord Fowler flap. The static rolling, yawing, and hinge moments were determined for several angles of attack and flap deflections. The ineffective region could be eliminated by a provision in the aileron linkage that would automatically uprig the ailerons as the flap is deflected.
Date: December 1941
Creator: Rogallo, F. M. & Spano, Bartholomew S.
Partner: UNT Libraries Government Documents Department
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Investigation of Drag and Pressure Distribution of Windshields at High Speeds

Description: Report presenting tests in the 8-foot high-speed wind tunnel to determine the loads and the load distributions at high speeds for a number of windshields of the cockpit-canopy type. Ten windshields of various designs similar to those in general use were included in these tests. Results regarding drag, loads, and design considerations are provided.
Date: January 1942
Creator: Delano, James B. & Wright, Ray H.
Partner: UNT Libraries Government Documents Department
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Maximum permissible engine performance of eight representative fuels of 100-octane number

Description: Report presenting knock-limited performance tests made with eight representative fuels rated at 100-octane number using the CFR aviation method. All eight fuels were mixtures of representative blending agents and bases. Results regarding the effect of inlet-temperature air changes, effect of octane numbers in a full-scale single-cylinder engine, effect of addition of aromatics to the fuels, and type of spark plug used are provided.
Date: January 1942
Creator: Rothrock, Addison M.; Biermann, Arnold E. & Corrington, Lester C.
Partner: UNT Libraries Government Documents Department
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Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Date: January 1942
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department
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Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Description: Report presenting pressure distribution measurements on two 24-inch chord models equipped with Fowler flaps in the two-dimensional low-turbulence pressure tunnel. Results regarding pressure-distribution diagrams and normal-force and moment coefficients are provided.
Date: January 1942
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department
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An investigation of diffuser-resistance combinations in duct systems

Description: Report presenting an investigation to determine the properties of diffuser-resistance combinations. The work applies to the design of airplane cooling ducts in which air is expanded in front of resistances, such as radiators, oil coolers, intercoolers, or the cylinders of an air-cooled engine.
Date: February 1942
Creator: McLellan, Charles H. & Nichols, Mark R.
Partner: UNT Libraries Government Documents Department
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Principles and Methods of Rating and Testing Centrifugal Superchargers

Description: "A discussion of the general principles involved in the rating and testing of centrifugal superchargers, a statement and discussion of present standard methods in rating and testing, and reasons for the adoption of these standards are given" (p. 1).
Date: February 1942
Creator: Ellerbrock, Herman H., Jr. & Goldstein, Arthur W.
Partner: UNT Libraries Government Documents Department
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Progress Summary Number 1: Mechanical Properties of Flush-Riveted Joints Submitted by Five Airplane Manufacturers

Description: Summary presenting information on flush-riveted joints for aircraft construction, including the strength, occurrence of defects, and effect of the angle of rivet head. The current tests covers specimens from 15 manufacturers of which 5 series have been completed and are described in this report.
Date: February 1942
Creator: Brueggeman, William Charles
Partner: UNT Libraries Government Documents Department
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A theoretical analysis of the effect of aileron inertia and hinge moment on the maximum rolling acceleration of airplanes in abrupt aileron rolls

Description: Report presenting data on the rolling accelerations of airplanes of different types and sizes in abrupt aileron rolls in connection with a number of maneuverability and flying qualities investigations. An analysis was made to determine the relation between the torque applied to the aileron system by the pilot, the motion of the system, and the subsequent rolling motion of the airplane in abrupt aileron roll.
Date: February 1942
Creator: Bailey, F. J., Jr. & O'Sullivan, William J.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of an NACA 23012 Airfoil with a Handley Page Slat and Two Flap Arrangements

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of an NACA 23012 airfoil equipped with a Handley Page slat and a slotted and a split flap. The purpose of the investigation was to determine the aerodynamic section characteristics of the airfoil with and without flaps as affected by the location of the Handley Page slat. A range of slat-nose locations was investigated both with and without flaps at a constant slat gap.
Date: February 1942
Creator: Schuldenfrei, Marvin J.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Carburetor-Air Inlets

Description: Report presenting an investigation of the internal and external airflow characteristics of carburetor-air inlets for liquid-cooled engine installations in the full-scale wind tunnel. Full-scale models of two representative pursuit airplanes were used in the investigation of nine carburetor-air inlets differing in shape, size, and location. Results regarding air flow and ram, drag, and compressibility are provided.
Date: February 1942
Creator: Nelson, W. J. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of single- and dual-rotating pusher propellers having from three to eight blades

Description: Report presenting tests of 10-foot-diameter, single- and dual-rotating pusher propellers with three to eight blades that were conducted in the 20-foot propeller research tunnel as a continuation of previous investigations of tractor propellers. The propellers were mounted at the rear end of a streamline body in spinners that covered the hubs and part of the shanks. The effects as compared to previous testing differed only in degree of effect size.
Date: February 1942
Creator: Gray, W. H.
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Tests of Three Edo Floats for the SB2U-3, 0S2U-2, and XSB2C-2 Seaplanes - NACA Models 106-K, 107-K, and 125-AH

Description: Report presenting aerodynamic testing of scale models of the Edo seaplane floats for the SB2U-3, OS2U-2, and XSB2C-2 seaplanes. Various coefficients, pitching moment, yawing moment, and drag coefficients are provided.
Date: March 1942
Creator: Liddell, Robert B.
Partner: UNT Libraries Government Documents Department
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Characteristics of plain and balanced elevators on a typical pursuit fuselage at attitudes simulating normal-flight and spin conditions

Description: Report presenting lift and elevator hinge-moment characteristics of a horizontal tail with various plain and balanced elevators and mounted on a typical pursuit fuselage as measured in the 7- by 10-foot wind tunnel at attitudes simulating normal-flight and spin conditions. The lift effectiveness of the elevator was practically independent of the size of the aerodynamic balance. Results regarding the fuselage alone and fuselage interference, lift characteristics of fuselage-tail combinations, li… more
Date: March 1942
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of Flow Across Tube Banks

Description: Flow across tube banks was investigated by surveys of total dynamic and static pressure by visualization of the flow through the use of titanium tetrachloride smoke, by thermocouple surveys of heated tubes, and by hot-wire surveys of both heated and unheated tubes. It was found that turbulence increased as the depth of the bank increased and that the broad wake behind each tube affected flow over the succeeding tubes.
Date: March 1942
Creator: Brevoort, M. J. & Tifford, A. N.
Partner: UNT Libraries Government Documents Department
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Full-scale wind-tunnel and flight tests of a Fairchild XR2K-1 airplane with a zap flap and upper-surface aileron-wing installation

Description: Report presenting testing of a Fairchild XR2K-1 airplane equipped with a wing having a full-span Zap flap and upper-surface ailerons in the full-scale wind tunnel and in flight to determine the characteristics of the flap and ailerons. Results regarding the lift, drag, and pitching-moment coefficients of the airplane and the aileron rolling, yawing, and hinge-moment coefficients were measured at various flap deflections are provided. Maximum rolling velocity and acceleration, yawing velocity, t… more
Date: March 1942
Creator: Clousing, L. A.; Lehr, Robert R. & O'Sullivan, William J.
Partner: UNT Libraries Government Documents Department
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A Method for the Design of Cooling Systems for Aircraft Power-Plant Installations

Description: Report presenting a method of organizing design calculations for the cooling systems of aircraft power-plant installations for use by representatives of airplane and engine companies invited to participate in the NACA power-plant installation section.
Date: March 1942
Creator: Rubert, Kennedy F. & Knopf, George S.
Partner: UNT Libraries Government Documents Department
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Notes on the Effects of Trailing-Edge Shapes of Low-Drag Airfoils on Profile Drag and the Trim and Balance of Control Surfaces

Description: Report presenting measurements of drag, lift, and aileron hinge moments on a 100-inch-chord model with various modifications to the trailing edge of the 0.20c Frise type aileron. The purpose of the data is to show qualitatively the effects of comparatively small modifications to the trailing edge of an aileron.
Date: March 1942
Creator: Underwood, W. J.
Partner: UNT Libraries Government Documents Department
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