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Cooling tests of a single-row radial engine with several NACA cowlings

Description: The cooling of a single-row radial air-cooled engine using several cowling arrangements has been studied in the NACA 20-foot wind tunnel. The results show the effect of the propeller and several cowling arrangements on cooling for various values of the indicated horsepower in the climb condition. A table giving comparative performance of the various cowling arrangements is presented. The dependence of temperature on indicated horsepower and pressure drop across the baffles is shown by charts. O… more
Date: August 20, 1936
Creator: Brevoort, M. J.; Stickle, George W. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
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Correction of Downwash in Wind Tunnels of Circular and Elliptic Sections

Description: The downwash velocity distribution behind the wing was determined for the free jet and for the closed tunnel of both circular and elliptic cross sections. The wing was placed at the center of the tunnel. The theory makes it possible to determine the downwash at any point in the jet. The computations were performed for points in the plane determined by the jet axis and the center-of-pressure line of the wing.
Date: July 1936
Creator: Lotz, Irmgard
Item Type: Refine your search to only Report
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Details of the Construction and Production of Fuel Pumps and Fuel Nozzles for the Airplane Diesel Engine

Description: This report presents investigations into the design and construction of fuel pumps for diesel engines. The results of the pump tests on the engines showed that, with a good cut-off, accurate injection, assured by the proper adjustment of the pump elements, there is a decrease in the consumption of fuel and hence an increase in the rated power of the engine. Some of the aspects investigated include: cam profile, coefficient of discharge, and characteristics of the injection system.
Date: September 1936
Creator: Lubenetsky, W. S.
Item Type: Refine your search to only Report
open access

Effect of changes in tail arrangement upon the spinning of a low-wing monoplane model

Description: "A series of tests was made in the N.A.C.A. free spinning tunnel to find the effect upon spinning characteristics of systematic changes in tail arrangement. The tests were made with a 1/16-scale made of a low-wing monoplane of modern design. The changes consisted of: (1) variation of the fuselage length; (2) variation of the fore-and-aft location of the vertical surfaces; and (3) variation of the vertical location of the horizontal surfaces. The spinning characteristics of the model, including … more
Date: June 1936
Creator: Zimmerman, C. H.
Item Type: Refine your search to only Report
open access

The effect of lateral controls in producing motion of an airplane as computed from wind-tunnel data

Description: This report presents the results of an analytical study of the lateral controllability of an airplane in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. The investigation was undertaken partly for the purpose of coordinating the results of a long series of wind-tunnel investigations with phenomena observed in flight tests; for this reason a hypothetical average airplane, embod… more
Date: April 20, 1936
Creator: Weick, Fred E. & Jones, Robert T.
Item Type: Refine your search to only Report
open access

Effect of nozzle design on fuel spray and flame formation in a high-speed compression-ignition engine

Description: "Fuel was injected from different type of injection nozzles into the combustion chamber of the NACA combustion apparatus, operated as a compression-ignition engine. High speed motion pictures were taken of the fuel sprays and combustion. Single-orifice nozzles of 0.008, 0.020, and 0.040 inch diameter, and multiorifice nozzles having 2, 6, and 16 orifices were tested. Nozzles having impinging jets and slit orifices were also included" (p. 327).
Date: March 19, 1936
Creator: Rothrock, A. M. & Waldron, C. D.
Item Type: Refine your search to only Report
open access

Effect of Several Factors on the Cooling of a Radial Engine in Flight

Description: "Flight tests of a Grumman Scout (XSF-2) airplane fitted with a Pratt & Whitney 1535 supercharged engine were conducted to determine the effect of engine power, mass flow of the cooling air, and atmospheric temperature on cylinder temperature. The tests indicated that the difference in temperature between the cylinder wall and the cooling air varied as the 0.38 power of the brake horsepower for a constant mass flow of cooling air, cooling-air temperature, engine speed, and brake fuel consumptio… more
Date: November 1936
Creator: Schey, Oscar W. & Pinkel, Benjamin
Item Type: Refine your search to only Report
open access

Electrical thermometers for aircraft

Description: Electrical thermometers commonly used on aircraft are the thermoelectric type for measuring engine-cylinder temperatures, the resistance type for measuring air temperatures, and the superheat meters of thermoelectric and resistance types for use on airships. These instruments are described and their advantages and disadvantages enumerated. Methods of testing these instruments and the performance to be expected from each are discussed. The field testing of engine-cylinder thermometers is treated… more
Date: December 15, 1936
Creator: Peterson, John B. & Womack, S. H. J.
Item Type: Refine your search to only Report
open access

Estimation of moments of inertia of airplanes from design data

Description: "A method of determining the moments of inertia of an airplane from design data pertaining to the weights and locations of the component parts is described. The computations required to ascertain the center-of-gravity position are incorporated with the calculations of moments of inertia. A complete set of data and calculations for a modern airplane is given to illustrate the procedure. From a comparison between calculated values and measured values it is believed that the moments of inertia can… more
Date: July 1936
Creator: Kirschbaum, H. W.
Item Type: Refine your search to only Report
open access

Experimental Studies of the Effective Width of Buckled Sheets

Description: The object of the present experiments is a more exact determination of the effective width for the case of pure compression and of the sheet clamped at the angle section. From the experimental data of the effective width the calculation of the buckling load of an angle joined to a thin sheet is then deduced. The test material consisted of spring-hardened brass sheet.
Date: December 1936
Creator: Lahde, R. & Wagner, H.
Item Type: Refine your search to only Report
open access

Flight measurements of the dynamic longitudinal stability of several airplanes and a correlation of the measurements with pilots' observations of handling characteristics

Description: The dynamic longitudinal stability characteristics of eight airplanes as defined by the period and damping of the longitudinal oscillations were measured in flight to determine the degree of stability that may be expected in conventional airplanes. An attempt was made to correlate the measured stability with pilots' opinions of the general handling characteristics of the airplanes in order to obtain an indication of the most desirable degree of dynamic stability. The results of the measurements… more
Date: July 15, 1936
Creator: Soulé, Hartley A.
Item Type: Refine your search to only Report
open access

Flow Phenomena on Plates and Airfoils of Short Span

Description: "Investigations on the flow phenomena at plates and cambered models were carried out with the aid of force measurements, some pressure distribution measurements, and photographic observation. The experimental methods are described and the results given. Section III of this work gives a comprehensive account of the results and enables us to see how nearly the lift line and lift surface theories agree with the experimental results" (p. 1).
Date: June 1936
Creator: Winter, H.
Item Type: Refine your search to only Report
open access

The Forces and Moments Acting on Parts of the XN2Y-1 Airplane During Spins

Description: "The magnitudes of the yawing moments produced by various parts of an airplane during spins have previously been found to be of major importance in determining the nature of the spin. Discrepancies in resultant yawing moments determined from model and full-scale tests, however, have indicated the probable importance of scale effect on the model. In order to obtain data for a more detailed comparison between full-scale and model results, flight tests were made to determine the yawing moments con… more
Date: February 20, 1936
Creator: Scudder, N. F.
Item Type: Refine your search to only Report
open access

The Forces and Moments on Airplane Engine Mounts

Description: "A resume of the equations and formulas for the forces and moments on an aircraft-engine mount is presented. In addition, available experimental data have been included to permit the computation of these forces and moments. A sample calculation is made and compared with present design conditions for engine mounts" (p. 1).
Date: December 1936
Creator: Donely, Philip
Item Type: Refine your search to only Report
open access

The Formation of Ice on Airplanes

Description: "The present report examines the problem of ice formation from the point of view of the pilot and the meteorologist. Their experiences prove the ice deposit to be first and foremost a navigational problem and only secondarily a question of de-icing devices. With correct utilization of the meteorological information by the flyer, ice hazard can in many cases be minimized or avoided. Ice formation and the different types of ice deposits are listed and discussed" (p. 1).
Date: February 1936
Creator: Noth, H. & Polte, W.
Item Type: Refine your search to only Report
open access

Friction of compression-ignition engines

Description: "The cost in mean effective pressure of generating air flow in the combustion chambers of single-cylinder compression-ignition engines was determined for the prechamber and the displaced-piston types of combustion chamber. For each type a wide range of air-flow quantities, speeds, and boost pressures was investigated. Supplementary tests were made to determine the effect of lubricating-oil temperature, cooling-water temperature, and compression ratio on the friction mean effective pressure of t… more
Date: August 1936
Creator: Moore, Charles S. & Collins, John H., Jr.
Item Type: Refine your search to only Report
open access

Fuel spray and flame formation in a compression-ignition engine employing air flow

Description: "The effects of air flow on fuel spray and flame formation in a high-speed compression-ignition engine have been investigated by means of the NACA combustion apparatus. The process was studied by examining high-speed motion pictures taken at the rate of 2,200 frames a second. The combustion chamber was of the flat-disk type used in previous experiments with this apparatus. The air flow was produced by a rectangular displacer mounted on top of the engine piston. Three fuel-injection nozzles were… more
Date: November 25, 1936
Creator: Rothrock, A. M. & Waldron, C. D.
Item Type: Refine your search to only Report
open access

Full-scale tests of NACA cowlings

Description: A comprehensive investigation has been carried on with full-scale models in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the physical functioning of the composite propeller-nacelle unit under all conditions of take-off, taxiing, and normal flight. This report deals exclusively with the cowling characteristics under condition of normal flight and includes the results of tests of numerous combinations of more than a dozen nose cowlings, about a… more
Date: May 18, 1936
Creator: Theodorsen, Theodore; Brevoort, M. J. & Stickle, George W.
Item Type: Refine your search to only Report
open access

Full-scale wind-tunnel and flight tests of a Fairchild 22 airplane equipped with a Fowler flap

Description: "Full-scale wind-tunnel and flight tests were made of a Fairchild 22 airplane equipped with a Fowler flap to determine the effect of the flap on the performance and control characteristics of the airplane. In the wind-tunnel tests of the airplane with the horizontal tail surfaces removed, the flap was found to increase the maximum lift coefficient from 1.27 to 2.41. In the flight test, the flap was found to decrease the minimum speed from 58.8 to 44.4 miles per hour" (p. 1).
Date: August 1936
Creator: Dearborn, C. H. & Soulé, H. A.
Item Type: Refine your search to only Report
open access

Full-scale wind-tunnel to determine a satisfactory location for a service Pitot-static tube on a low-wing monoplane

Description: Surveys of the air flow over the upper surface of four different airfoils were made in the full-scale wind tunnel to determine a satisfactory location for a fixed Pitot-static tube on a low-wing monoplane. The selection was based on small interference errors, less than 5 percent, and on a consideration of structural and ground handling problems. The most satisfactory location on the airfoils without flaps that were investigated was 10 percent of the chord aft and 25 percent of the chord above t… more
Date: March 1936
Creator: Parsons, John F.
Item Type: Refine your search to only Report
open access

Further Measurements of Normal Accelerations on Racing Airplanes

Description: This report details the acceleration data collected from racing airplanes during actual races. The data was collected in order to make recommendations regarding the structural safety of racing airplanes and the methods of operating racing airplanes that reduces the probability of subjecting them to extreme air loads. The records do not lead to any conclusions regarding maximum air loads.
Date: February 1936
Creator: Kirschbaum, H. W. & Scudder, N. F.
Item Type: Refine your search to only Report
open access

General Considerations on the Flow of Compressible Fluids

Description: This paper presents an introduction to the subject of the flow of compressible media. Information regarding steady potential flow, flows with "subsonic" velocities, higher approximations of subsonic velocities, flow with supersonic velocities, an approximate method for general two-dimensional supersonic flow, passage through the velocity of sound, and the application to airfoils is provided. Historical development and hydraulics are omitted.
Date: October 1936
Creator: Prandtl, L.
Item Type: Refine your search to only Report
open access

General instability criterion of laminar velocity distributions

Description: The present paper describes the results of a stability investigation on symmetrical velocity profiles in a channel and of boundary-layer profiles. The effect of friction was assumed to be vanishing and did not occur in the stability consideration so far as it had been resorted to for preparatory asymptotic considerations. Proceeding on very general premises as regards the form of the velocity distribution, a proof was deduced of the elementary theorem that velocity profiles with inflection poin… more
Date: April 1936
Creator: Tollmien, W.
Item Type: Refine your search to only Report
open access

A general tank test of a model of the hull of the British Singapore IIC flying boat

Description: A general test was made in the N.A.C.A. tank of a 1/12-size model of the hull of the British Singapore IIC flying boat loaned by the Director of Research, British Air Ministry. The results are given in charts and are compared with the results of tests of a model of an American flying-boat hull, the Sikorsky S-40. The Singapore hull has a greater hump resistance but a much lower high-speed resistance than the S-40.
Date: September 1936
Creator: Dawson, John R. & Truscott, Starr
Item Type: Refine your search to only Report
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