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Ultraviolet spectrochemical analysis for aromatics in aircraft fuels

Description: Report presenting tests to verify and extend ultraviolet spectroscopic techniques for applications to the analysis of aviation fuels for their aromatic constituents. Results regarding photographic absorption spectra, spectrophotometric absorption spectra, and spectrophotometric analyses are provided.
Date: March 1945
Creator: Cleaves, Alden P.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of aircraft heaters 14: an air and heat flow analysis of a ram-operated heater and duct system

Description: Report presenting a method of graphical analysis that allows for the prediction of the thermal and aerodynamic performance of a ram-operated heater and duct system, for cabin heating or wing de-icing, at any altitude and airplane speed. Performance can be predicted from the isothermal total pressure drop across the components of the duct system at several ventilating air rates and the thermal output of the heater at various air and exhaust gas rates.
Date: March 1944
Creator: Boelter, L. M. K.; Morrin, E. H.; Martinelli, R. C. & Poppendiek, H. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of aircraft heaters 10: measured and predicted performance of a fluted-type exhaust gas and air heat exchanger

Description: Report presenting performance data on a small exhaust gas and air heat exchanger. The heat transfer rates were measured using about 8000 pounds per hour of exhaust gas and 4300 pounds per hour of ventilating air. The thermal performance of heater no. 2 can be estimated to 3 to 17 percent by use of the method described in the report.
Date: March 1943
Creator: Boelter, L. M. K.; Dennison, H. G.; Guibert, A. G. & Morrin, E. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Aircraft Heaters 8: A Simplified Method for the Calculation of the Unit Thermal Conductance Over Wings

Description: Report presenting a simplified approximate method of calculating the unit thermal conductance along an airfoil as a function of distance from the leading edge, by use of heat transfer data for smooth cylinders and smooth flat plates. Several examples are used in order to show the effectiveness of the method.
Date: March 1943
Creator: Martinelli, R. C.; Guibert, A. G.; Morrin, E. H. & Boelter, L. M. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 21: Medium and Large Aerodynamic Balances of Two Nose Shapes and a Plain Overhang Used With a 0.40-Airfoil-Chord Flap on an NACA 0009 Airfoil

Description: Report discusses the results of an investigation of an NACA 0009 airfoil with a 40-percent-chord flap with medium and large aerodynamic balances of elliptical and blunt nose shapes and a plain overhang. The results are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed and unsealed.
Date: March 1945
Creator: Riebe, John M. & Church, Oleta
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

On the Shear Strength of Skin-Stiffener Panels With Inspection Cut-Outs

Description: "Strength tests and strain measurements were made of 19 long shear panels with rectangular inspection cut-outs; that is, cut-outs obtained by removing the sheet between two adjacent stringers without cutting any stringer. The test results indicated that the stress concentration existing at low stresses tends to disappear at very high stresses and that the assumption of uniform stress distribution leads to a satisfactory correlation of the test results. Stiffening of the sheet bay containing the… more
Date: March 1945
Creator: Kuhn, Paul & Diskin, Simon H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of a numerical procedure to stress analysis of stringer-reinforced panels

Description: From Introduction: "In the present paper a numerical procedure for the stress analysis of flat-sheet and stringer combinations of arbitrary construction and loading is presented and applied to axially loaded panels and to the reinforced covers of box beams."
Date: March 1945
Creator: Kempner, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Correlation of the Dimensions, Proportions, and Loadings of Existing Seaplane Floats and Flying Boat Hulls

Description: Report presenting a study to determine what loadings and proportions have been chosen by designers of seaplanes and flying boats and what, if any, interrelations exist between the loadings and proportions. The characteristics considered include the beam, getaway speed, forebody length, afterbody length, hull length, center of gravity, and brake horsepower necessary.
Date: March 1943
Creator: Locke, Fred W. S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Continuous Knock on the Endurance of an Aircraft Engine Cylinder

Description: Report presenting an investigation to determine any injurious effects of knock on engine parts. Endurance tests were run on a single-cylinder engine to compare the conditions of cylinders operated with and without knock. Results regarding the history of the tests, conditions of pistons and cylinders, absence of surface ignition, and effect of knock on cylinder temperatures are provided.
Date: March 1944
Creator: Sanders, J. C.; Hilgendorf, J. A. & Peters, M. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tensile-Strength Investigation of Cast-Iron Piston Rings of Various Strengths

Description: Report discusses an investigation into the tensile strength of cast-iron piston rings, NACA microtensile specimens, and bar specimens. Photographs showing the relation between graphite-flake size and tensile strength and radiographs showing the shrinkage cavities in the piston rings are provided. Piston rings tend to be one of the first parts of an aircraft engine to fail, so discovering the ideal material composition and foundry treatment is very important.
Date: March 1945
Creator: Bisson, Edmond E. & Kessler, Harold D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Compression Ratio, Cooled Exhaust Gas Mixed With Inlet Air, and Inlet-Air Temperature on the Knock-Limited Performance of a Full-Scale Single-Cylinder Engine

Description: Report presenting a study to determine the effect on the knock-limited permissible power output on the indicated specific fuel consumption and on the cylinder temperatures of exhaust-gas dilution of the inlet-air charge, inlet-air temperature without exhaust-gas dilation, and of compressible ratio.
Date: March 1944
Creator: Bolz, Ray E. & Breitwieser, Roland
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Response of Helicopter Rotors to Periodic Forces

Description: Report explores the periodic forces that helicopter rotors are subjected to, both horizontal and vertical, and several configurations and material combinations of blades are described. The vibrations and exciting forces are demonstrated through calculations and explored with combinations of one, two, three, and four blades.
Date: March 1945
Creator: Kelley, Bartram
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Rotor-Tip Speed on Helicopter Hovering Performance and Maximum Forward Speed

Description: Report presenting a study of several sample helicopters in order to evaluate the effect of rotor-tip speed on hovering performance and limiting forward speed. The main purpose of the study was to determine whether hovering performance could be increased by the use of lower tip speeds without undue sacrifice in maximum forward speed. Results regarding typical helicopters, low-solidity helicopters, and high-speed helicopters are provided.
Date: March 1946
Creator: Gustafson, F. B. & Gessow, Alfred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A method for studying piston friction

Description: From Introduction: "The purpose of this investigation was to develop a method for determining directly the friction force between the piston and cylinder of an internal combustion engine. The method consists in elastically mounting the cylinder barrel so that it can have a small motion parallel to its axis, and providing suitable means for recording its instantaneous displacement."
Date: March 1943
Creator: Forbes, J. E. & Taylor, E. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Artificial Running-in of Piston Rings

Description: Report presenting a consideration of the performance of sliding surfaces, such as piston rings, cylinders, journals, and bearings in aircraft engines with reference to the surface characteristics that they possess before and after running-in, prior to service operation. The phenomena accompanying the running-in process are analyzed.
Date: March 1944
Creator: Bobrowsky, A. R. & Machlin, E. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudde… more
Date: March 1946
Creator: Kayten, Gerald G. & Koven, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a dynamic model in NACA tank number 1 to determine the effect of length of afterbody, angle of afterbody keel, gross load, and a pointed step on landing and planning stability

Description: Report presenting testing in tank no. 1 to determine the effect of length of afterbody, angle of afterbody keel, and gross load on the limits of stable trims and landing characteristics of a model of a flying boat with conventional steps. The studies were made with four lengths of afterbody, four angles of afterbody keel, and five gross loads. Results regarding the trim limits of stability and landing stability are provided.
Date: March 1943
Creator: Land, Norman S. & Lina, Lindsay J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics: [Part] 4 - Symmetrically Tapered Wing With a Circular Fuselage Having a Wedge-Shaped Rear and a Vertical Tail

Description: Report presenting testing of combinations of an NACA 23012 tapered wing and a circular fuselage with a wedge-shaped rear to determine the effect of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. Results regarding the lateral stability at small and large angles of yaw are provided.
Date: March 1942
Creator: Recant, I. G. & Wallace, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Frequency of occurrence of critical gust loads on overloaded airplanes

Description: Report presenting statistical gust-frequency data used to determine the effect of overloading an airplane on the frequency of occurrence of gust loads that stress the airplane to or above its design applied bending moment. The analysis was made for three transport-type airplanes operating at cruising power with overloads varying from 0 to 50 percent of the design gross weight. The probability of structural failure was found to increase rapidly with overload.
Date: March 1945
Creator: Reisert, Thomas D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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