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Nitrided-steel piston rings for engines of high specific power

Description: Report presenting testing of several designs of nitrided-steel piston rings under variable conditions of output. Testing indicated the importance of good surface finish and conformity of the ring to the bore. Results regarding temperature tests, single-cylinder-engine tests, and multicylinder-engine tests are provided.
Date: April 1944
Creator: Collins, John H., Jr.; Bisson, Edmond E. & Schmiedlin, Ralph F.
Partner: UNT Libraries Government Documents Department
open access

Wall interference in a two-dimensional-flow wind tunnel with consideration of the effect of compressibility

Description: Report presenting tunnel-wall corrections for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid and is based on the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. The theoretical results are compared with the small amount of low-speed experimental data available and agreement is seen to be satisfactory, even for… more
Date: December 1944
Creator: Allen, H. Julian & Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department
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Single-Cylinder Oil-Control Tests of Porous Chrome Plated Cylinder Barrels for Radial Air-Cooled Engines

Description: Report presenting a series of single-cylinder engine tests run to determine a satisfactory method of reducing oil consumption in radial air-cooled engines with flat-face compression rings as standard parts and equipped with cylinder barrels salvaged by porous chrome plating. Testing was conducted using porous chrome-plated cylinders with straight and choke bores with standard flat-face compression rings.
Date: January 1946
Creator: Johnson, Robert L. & Swikert, Max
Partner: UNT Libraries Government Documents Department
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The Effect of Increased Cooling Surface on Performance of Aircraft-Engine Cylinders as Shown by Tests of the NACA Cylinder

Description: Report presenting a method of constructing fins of nearly optimum proportions to the point where a cylinder has been manufactured and tested. Data were obtained on cylinder temperature for a wide range of inlet-manifold pressures, engine speeds, and cooling-pressure differences. Results regarding cooling equations, cylinder-temperature relationships, and a comparison of three cylinder cooling performances are provided.
Date: July 1944
Creator: Schey, Oscar W.; Rollin, Vern G. & Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department
open access

A laboratory investigation of the icing characteristics of the Bendix-Stromberg carburetor model PD-12F5 with the Pratt and Whitney R-1830-C4 intermediate rear engine section

Description: Report presenting icing tests on a Bendix-Stromberg PD-12F5 carburetor mounted on a Pratt & Whitney R-1830-C4 intermediate rear engine section. Limiting icing conditions were established for simulated cruising power and simulated rated power over a range of carburetor-air temperatures, and relative humidities are provided.
Date: October 1944
Creator: Galvin, Herman B. & Essex, Henry A.
Partner: UNT Libraries Government Documents Department
open access

The Flow of a Compressible Fluid Past a Curved Surface

Description: Report presenting an iteration method employed to obtain the flow of a compressible fluid past a curved surface. For small Mach numbers and thin shapes, the results obtained by the iteration process agree with those obtained by the Poggi method.
Date: November 1943
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 18: A Design Manual for Exhaust Gas and Air Heat Exchangers

Description: Report presenting a summary of a series of reports regarding heat exchangers, and in particular, the design of exhaust gas and air heat exchangers. The four parts included are a summary of heat transfer equations, single pass heat exchangers, heater performance in flight, and appendicies with additional aerodynamic information.
Date: August 1945
Creator: Boelter, L. M. K.; Martinelli, R. C.; Romie, F. E. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department
open access

Air-consumption parameters for automatic mixture control of aircraft engines

Description: From Introduction: "The purpose of this analysis was to investigate the use of function of intake-manifold temperature and pressure, exhaust back pressure, and engine speed in place of a ventri as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date: September 1944
Creator: Shames, Sidney J.
Partner: UNT Libraries Government Documents Department
open access

Secondary Stresses in Open Box Beams Subjected to Torsion

Description: In open box beams subjected to torsion, secondary stresses arise owing to lateral bending of the spar caps. The present paper outlines a simple method for estimating the magnitude of these stresses and gives the results of tests of an open box beam in the neighborhood of a discontinuity where the cover changed from the top to the bottom of the box.
Date: November 1944
Creator: Kuhn, Paul; Batdorf, S. B. & Brilmyer, Harold G.
Partner: UNT Libraries Government Documents Department
open access

Stresses Near the Juncture of a Closed and an Open Torsion Box as Influenced by Bulkhead Flexibility

Description: Report discussing an open box joined to a closed box subjected to torsional loading. A stiff bulkhead and a flexible bulkhead were tested at the discontinuity and the results were compared to a previously published theory. Stress distribution was found to not be sensitive to bulkhead stiffness when the stiffness is large, but the calculations became sensitive to errors in estimating when the stiffness was small.
Date: August 1945
Creator: Kuhn, Paul & Brilmyer, Harold G.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 3: A Small Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil

Description: Report presenting tests in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a small amount of aerodynamic balance. In the investigation, the effect of balance nose shape and gap at the nose of the flap has been determined. The results indicate that, in general, the lift effectiveness of the flap was unaffected by the addition of a small amount of aerodynamic overhang, and the balance effectiveness of the flap was increased.
Date: August 1941
Creator: Ames, Milton B., Jr.
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Investigation of Control-Surface Characteristics 11: Various Large Overhang and Internal-Type Aerodynamic Balances for a Straight- Contour Flap 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 several different shaped overhang-type aerodynamic balances applied to a straight-contour flap mounted on an NACA 0015 airfoil. The flap with blunt-nose overhang was overbalanced throughout certain ranges of flap deflection. Results regarding precision, lift, flap hinge moments, pitching moment, and drag are provided.
Date: January 1943
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 4: A Medium Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil

Description: Report presenting tests made in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a medium amount of aerodynamic overhanging balance. In this investigation, the effects of the shape of the flap-nose overhang and the gap at the nose of the flap have been determined. The results indicate that, generally, the lift effectiveness of the aerodynamically balanced flap was increased slightly over that of a plain flap when a blunt or medium flap nose was use… more
Date: September 1941
Creator: Ames, Milton B., Jr. & Eastman, Donald R., Jr.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 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. 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
open access

Theory and preliminary flight tests of an all-movable vertical tail surface

Description: Report presenting flight testing of an improved type of all-movable tail surface. The particular arrangement tested provides control-free stability and a stable variation of the control forces during maneuvers. Results regarding rudder effectiveness, directional stability, rudder-free lateral motion, and rudder-free turns are provided.
Date: January 1943
Creator: Jones, Robert T. & Kleckner, Harold F.
Partner: UNT Libraries Government Documents Department
open access

Preliminary flight research on an all-movable horizontal tail as a longitudinal control for flight at high Mach numbers

Description: Report presenting flight tests of an all-movable horizontal tail installed on a Curtiss XP-42 airplane due to its possible advantages as a longitudinal control at high Mach numbers. The elevator control was found to be unsatisfactory with the control arrangements tested.
Date: March 1945
Creator: Kleckner, Harold F.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of control-surface characteristics 5: the use of a beveled trailing edge to reduce the hinge moment of a control surface

Description: Report presenting wind tunnel testing to investigate the possibility of reducing the hinge moments of a control surface by beveling the trailing edge. Tests were made with a 9-percent-thick airfoil with a 30-percent-chord plain flap. Results regarding the variations of lift and hinge moment, effect of shapes, and pitching moments are provided.
Date: March 1942
Creator: Jones, Robert T. & Ames, Milton B., Jr.
Partner: UNT Libraries Government Documents Department
open access

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
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Wind-tunnel investigation of control-surface characteristics II : a large aerodynamic balance of various nose shapes with a 30-percent-chord flap on an NACA 0009 airfoil

Description: Report presenting testing of an NACA 0009 airfoil with a 30-percent-chord flap with a 49.5-percent flap-chord balance with various nose shapes and two gaps. The results indicated that the flap is overbalanced when deflected, regardless of nose shape. Results regarding lift, hinge moment of flap, drag, pitching moment, and effect of differential balancing tab are provided.
Date: August 1941
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Wind-Tunnel Investigation of a Full-Span Retractable Flap in Combination With Full-Span Plain and Internally Balanced Ailerons on a Tapered Wing

Description: Report discusses the results of an investigation into a full-span retractable flap in combination with a full-span plain and internally balanced ailerons on a tapered wing of a typical fighter airplane.The flap was designed to improve lateral control during high lifts for landing and take-off. The effects on the maximum life coefficient, aileron effectiveness, estimated rates of roll, and stick forces are provided.
Date: August 1943
Creator: Rogallo, F. M.; Lowry, John G. & Fischel, Jack
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Description: Report presenting an investigation in the 19-foot pressure tunnel of two-tapered wings with NACA 230-series airfoil sections, straight leading edges, and constant-chord center sections. Lift, drag, and pitching-moment coefficients were determined for the plain wing and for each flap arrangement for a range of Reynolds numbers. The results indicated that the wing with the square center section has greater maximum lift coefficients and increments of maximum lift due to flap deflections than the w… more
Date: October 1943
Creator: Fairbanks, Richard W. & Alexander, Sidney R.
Partner: UNT Libraries Government Documents Department
open access

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
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