Search Results

open access

Maximum Forces Applied by Pilots to Wheel-Type Controls

Description: "Measurements were made of the maximum push, pull, and tangential forces that could be applied to airplane wheel-type controls for a wide range of fore-and-aft positions of the wheel. The measurements were conducted with several sizes of wheels and several heights of the center of the wheel above the seat. Various one and two-hand grips with pilots both secure and free were studied for each of the two pilots used in the investigation" (p. 1).
Date: November 1937
Creator: McAvoy, William H.
Partner: UNT Libraries Government Documents Department
open access

Performance Characteristics of Venturi Tubes Used in Aircraft for Operating Air-Driven Gyroscopic Instruments

Description: "Wind tunnel and flight tests were made to determine the performance characteristics of two designs of commercially available venturi tubes used in airplanes to operate air-driven gyroscopic instruments. Data obtained at sea level may be used to make approximate predictions of performance at higher altitudes. There is some indication that this may also be done for single venturi tubes" (p. 1).
Date: November 1937
Creator: Sontag, Harcourt & Johnson, Daniel P.
Partner: UNT Libraries Government Documents Department
open access

Bending Tests of Circular Cylinders of Corrugated Aluminum-Alloy Sheet

Description: "Bending tests were made of two circular cylinders of corrugated aluminum-alloy sheet. In each test failure occurred by bending of the corrugations in a plane normal to the skin. It was found, after analysis of the effect of short end bays, that the computed stress on the extreme fiber of a corrugated cylinder is in excess of that for a flat panel of the same basic pattern and panel length tested as a pin-ended column. It is concluded that this increased strength was due to the effects of curva… more
Date: March 1937
Creator: Niles, Alfred S.; Buckwalter, John C. & Reed, Warren D.
Partner: UNT Libraries Government Documents Department
open access

Heat transfer from cylinders having closely spaced fins

Description: The heat-transfer coefficients have been determined for five steel cylinders having fins 1.22 inches wide and the spacing between the fins ranging from 0.022 to 0.131 inch. The cylinders were tested with and without baffles in a wind tunnel; they were also tested enclosed in jackets with the cooling air supplied by a blower. A maximum heat transfer was reached at a fin space of about 0.45 inch for the cylinders tested with each of the three methods of cooling investigated. The rise in temperatu… more
Date: May 1937
Creator: Biermann, Arnold E.
Partner: UNT Libraries Government Documents Department
open access

A preliminary study of flame propagation in a spark-ignition engine

Description: "The N.A.C.A. combustion apparatus was altered to operate as a fuel-injection, spark-ignition engine, and a preliminary study was made of the combustion of gasoline-air mixtures at various air-fuel ratios. Air-fuel ratios ranging from 10 to 21.6 were investigated. Records from an optical indicator and films from a high-speed motion-picture camera were the chief sources of data. Schlieren photography was used for an additional study" (p. 1).
Date: June 1937
Creator: Rothrock, A. M. & Spencer, R. C.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Curvature on the Transition From Laminar to Turbulent Boundary Layer

Description: "In the flow over the upper surface of a wing, a discrepancy between the predicted and actual point of transition from laminar to turbulent boundary layer was found. This effect may be due to the comparatively small radius of curvature of the upper surface of the wing. Tests were undertaken to investigate this effect. As far as the authors know, the present investigation is the first to show that curvature has a pronounced effect on the transition of the boundary layer from the laminar to the t… more
Date: September 1937
Creator: Clauser, Milton & Clauser, Francis
Partner: UNT Libraries Government Documents Department
open access

A Study of the Factors Affecting the Range of Airplanes

Description: A study was made of the most important factors affecting the range of airplanes. Numerical examples are given showing the effects of different variables on the range of a two-engine airplane. The takeoff problems of long-range airplanes are analyzed.
Date: February 1937
Creator: Biermann, David
Partner: UNT Libraries Government Documents Department
open access

Pressure drop across finned cylinders enclosed in a jacket

Description: The pressure drop across finned cylinders in a jacket for a range of air speeds from approximately 13 to 230 miles per hour has been investigated. Tests were made to determine the effect on the pressure drop of changes in fin space, fin width, jacket entrance and exit areas, skirt-approach radius, and the use of fillets and a separator plate at the rear of the cylinder. The pressure drop across the cylinder increased as the fin space decreased, the increase being very rapid at fin spaces smalle… more
Date: November 1937
Creator: Rollin, Vern G. & Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department
open access

Pressure Drop in Tubing in Aircraft Instrument Installations

Description: "The theoretical basis of calculation of pressure drop in tubing is reviewed briefly. The effect of pressure drop in connecting tubing upon the operation and indication of aircraft instruments is discussed. Approximate equations are developed, and charts and tables based upon them are presented for use in designing installations of altimeters, air-speed indicators, rate-of-climb indicators, and air-driven gyroscopic instruments" (p. 1).
Date: February 1937
Creator: Wildhack, W. A.
Partner: UNT Libraries Government Documents Department
open access

Spinning Characteristics of Wings 3: A Rectangular and Tapered Clark Y Monoplane Wing with Rounded Tips

Description: An investigation was made to determine the spinning characteristics of Clark Y monoplane wings with different plan forms. A rectangular wing and a wing tapered 5:2, both with rounded tips, were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. Also included is an estimate of the yawning moment that must be furnished by the parts of the airplane to balanc… more
Date: September 1937
Creator: Bamber, M. J. & House, R. O.
Partner: UNT Libraries Government Documents Department
open access

Tank tests of two models of flying-boat hulls to determine the effect of ventilating the step

Description: From Summary: "The results of tests made in the N.A.C.A. tank on two models of flying-boat hulls to determine the effect of ventilating the step are given graphically. The step of N.A.C.A. model 11-C was ventilated in several different ways and it was found that the resistance of the normal form is not appreciably affected by artificial ventilation in any of the forms tried. Further tests made with the depth of the step of model 11-C reduced likewise show no appreciable effect on the resistance… more
Date: February 1937
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department
open access

Flight tests of an airplane showing dependence of the maximum lift coefficient on the test conditions

Description: "Data are presented to show the extent to which the maximum lift coefficient and consequently the minimum speed of an airplane, determined by flight tests, may vary with test conditions. The data show that cl-max may vary as much as 14 percent, depending on the altitude and wing loading at which the tests were made, the position or motion of the propeller, and the rate at which the angle of attack is changing when the maximum lift coefficient is obtained. The variation of the maximum lift coeff… more
Date: November 1937
Creator: Soulé, H. A. & Hootman, James A.
Partner: UNT Libraries Government Documents Department
open access

Full-Scale Wind-Tunnel and Flight Tests of a Fairchild 22 Airplane Equipped With External-Airfoil Flaps

Description: "Wind-tunnel and flight tests have been made of a Fairchild 22 airplane equipped with a wing having external-airfoil flaps that also perform the function of ailerons. Lift, drag, and pitching-moment coefficients of the airplane with several flap settings, and the rolling- and yawing-moment coefficients with the flaps deflected as ailerons were measured in the full-scale tunnel with the horizontal tail surfaces and propeller removed. The effect of the flaps on the low speed and on the take-off a… more
Date: July 1937
Creator: Reed, Warren D. & Clay, William C.
Partner: UNT Libraries Government Documents Department
open access

Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5

Description: From Summary: "Results are presented of the drag tests of six bodies of revolution with systematically varying shapes and with a fineness ratio of 5. The forms were derived from source-sink distributions, and formulas are presented for the calculation of the pressure distribution of the forms. The tests were made in the N.A.C.A. variable-density tunnel over a range of values of Reynolds number from about 1,500,000 to 25,000,000. The results show that the bodies with the sharper noses and tails … more
Date: September 1937
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department
open access

Noise From Propellers With Symmetrical Sections at Zero Blade Angle

Description: "A theory has been deduced for the "rotation noise" from a propeller with blades of symmetrical section about the chord line and set at zero blade angle. Owing to the limitation of the theory, the equations give without appreciable error only the sound pressure for cases where the wave lengths are large compared with the blade lengths. With the aid of experimental data obtained from a two-blade arrangement, an empirical relation was introduced that permitted calculation of higher harmonics" (p.… more
Date: July 1937
Creator: Deming, A. F.
Partner: UNT Libraries Government Documents Department
open access

Motion of the Two-Control Airplane in Rectilinear Flight After Initial Disturbances With Introduction of Controls Following an Exponential Law

Description: "An airplane in steady rectilinear flight was assumed to experience an initial disturbance in rolling or yawing velocity. The equations of motion were solved to see if it was possible to hasten recovery of a stable airplane or to secure recovery of an unstable airplane by the application of a single lateral control following an exponential law. The sample computations indicate that, for initial disturbances complex in character, it would be difficult to secure correlation with any type of expon… more
Date: September 1937
Creator: Klemin, Alexander
Partner: UNT Libraries Government Documents Department
open access

Strain Measurements on Small Duralumin Box Beams in Bending

Description: "Extensive strain-gage measurements were made chiefly on the tension side of five small rectangular box beams constructed of sheet duralumin. The main conclusion was that within the test range the tension cover may be considered as being fully effective but that at any given point on the beam there may be unaccountable variations of 5 percent from the calculated stresses on the thicker sheets tested (0.044 and 0.023 inch) and of 10 percent or more on the thinnest sheet tested (0.014 inch)" (p. … more
Date: January 1937
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department
open access

Discharge characteristics of a double injection-valve single-pump injection system

Description: The discharge characteristics of two similar injection valves operated by a single-cylinder fuel-injection pump were determined with an apparatus that measured the quantity of fuel discharged from each valve during every 0.5 degrees of pump rotation. It was found that similar discharges took place from the two valves at all pump speeds when the valve-opening pressures, the nozzle-orifice diameters, and the injection-tube lengths were the same for both valves. Under these conditions, the effects… more
Date: May 1937
Creator: Lee, Dana W. & Marsh, E. T.
Partner: UNT Libraries Government Documents Department
open access

The lateral instability of deep rectangular beams

Description: "Experimental and analytical studies were made of solid and hollow deep rectangular beams to study their lateral instability under various conditions of loading and restraint. The tests were made on bars and tubes of 17ST aluminum alloy. Failure by lateral buckling occurred only in tests on the solid beams. It was found that, within the elastic range, the test results were in agreement with the classical theory for the lateral buckling of deep beams as given by Prandtl, Mitchell, and Timoshenko… more
Date: May 1937
Creator: Dumont, C. & Hill, H. N.
Partner: UNT Libraries Government Documents Department
open access

The sonic altimeter for aircraft

Description: Discussed here are results already achieved with sonic altimeters in light of the theoretical possibilities of such instruments. From the information gained in this investigation, a procedure is outlined to determine whether or not a further development program is justified by the value of the sonic altimeter as an aircraft instrument. The information available in the literature is reviewed and condensed into a summary of sonic altimeter developments. Various methods of receiving the echo and t… more
Date: August 1937
Creator: Draper, C. S.
Partner: UNT Libraries Government Documents Department
open access

Compression-ignition engine performance at altitudes and at various air pressures and temperatures

Description: From Summary: "Engine test results are presented for simulated altitude conditions. A displaced-piston combustion chamber on a 5- by 7-inch single cylinder compression-ignition engine operating at 2,000 r.p.m. was used. Inlet air temperature equivalent to standard altitudes up to 14,000 feet were obtained. Comparison between performance at altitude of the unsupercharged compression-ignition engine compared favorably with the carburetor engine."
Date: November 1937
Creator: Moore, Charles S. & Collins, John H., Jr.
Partner: UNT Libraries Government Documents Department
open access

Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model

Description: A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that cooling can be improved by 20 percent by using a correctly designed baffle. Such a gain is as effective as a 65 percent increase in pressure drop across the standard baffle, which had a 1/4 inch clearance between baffle and fin tips.
Date: October 1937
Creator: Brevoort, Maurice J.
Partner: UNT Libraries Government Documents Department
open access

The measurement of air speed in airplanes

Description: Various methods of measuring the air speed of airplanes are described. Particular emphasis is placed on the procedure required to obtain precise measurements of speed by the use of the suspended Pitot-static head or the suspended static head. Typical calibration curves for service installations of Pitot-static heads are shown and the relation between errors in air speed and corresponding errors in observed altitude for such installations is discussed. There is included a brief discussion of var… more
Date: October 1937
Creator: Thompson, F. L.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen