UNT Libraries Government Documents Department - 29 Matching Results

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Addition of Heat to a Compressible Fluid in Motion

Description: From Introduction: "The purpose of this report is to summarize, without extended proofs, the results of a study of a simplified model of nonadiabiatic, compressible fluid flow, both subsonic and supersonic, and to state these results in a form that will make them immediately useful in providing a theoretical background for current technical problems of high-speed combustion.
Date: February 1945
Creator: Hicks, Bruce L.
Item Type: Refine your search to only Report
open access

An Analysis of Jet-Propulsion Systems Making Direct Use of the Working Substance of a Thermodynamic Cycle

Description: From Summary: "The results of the analysis showed that the combined efficiency, which is unacceptably low at speeds less than 300 miles per hour, becomes nearly equal to that of conventional power plants of current design at 500 miles per hour. It was also shown that the efficiency will be increased considerably as the physical limitations on cycle temperature and blower speed are raised and as the efficiencies of the system components are improved."
Date: February 1945
Creator: Rubert, Kennedy F.
Item Type: Refine your search to only Report
open access

Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers

Description: Report presenting the calculated performance of four-, six-, and eight-blade single-rotating propellers compared with experimental results for blade angles ranging from 25 to 65 degrees. The data were obtained on propellers mounted in front of a streamline body with a spinner housing the hub.
Date: February 1944
Creator: Crigler, John L.
Item Type: Refine your search to only Report
open access

A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
Date: February 1944
Creator: Nitzberg, Gerald E.
Item Type: Refine your search to only Report
open access

Considerations of wake-excited vibratory stress in a pusher propeller

Description: Report presenting an equation based on simple blade-element theory and the assumption of a fixed wake pattern is derived and fitted to available data to show the first-order relation between the parameters of propeller operation and intensity of wake-excited periodic force acting on the blades of a pusher propeller. The derived equation indicates that the effect of power coefficient on the intensity of the wake-excited periodic force is small. Limited data also indicates that the wake-excited v… more
Date: February 1944
Creator: Corson, Blake W., Jr.
Item Type: Refine your search to only Report
open access

The Determination of Span Load Distribution at High Speeds by Use of High-Speed Wind-Tunnel Section Data

Description: Report presenting a tabular method for determining the span load distribution at high Mach numbers by utilizing high-speed airfoil section data. This method, which is also called the generalized method, is an easily applied process of successive approximations by which a general application of the lifting-line theory may be used to determine the span load distribution for wings composed of sections with arbitrary lift curves. An example is provided to show how the method is used.
Date: February 1944
Creator: Boshar, John
Item Type: Refine your search to only Report
open access

Determination of the Effect of Horizontal-Tail Flexibility on Longitudinal Control Characteristics

Description: Report presenting an iteration method for determining the longitudinal control characteristics of a flexible horizontal tail. The method permits factors such as the actual spanwise variation of elasticity and the aerodynamic induction effects due to three-dimensional flow to be accounted for to any degree of accuracy needed. An analysis is also included of the effects of horizontal-tail flexibility on the tail effectiveness, the hinge-moment characteristics, and the control-force gradients in a… more
Date: February 1945
Creator: Harmon, S. M.
Item Type: Refine your search to only Report
open access

Determination of the Stability and Control Characteristics of a Straight-Wing, Tailless Fighter-Airplane Model in the Langley Free-Flight Tunnel

Description: Report presenting an investigation to determine the stability and control characteristics of a straight-wing, tailless fighter model with a pusher propeller in the free-flight tunnel. The investigation consisted principally of force and flight tests of a powered dynamic model. Results regarding longitudinal stability, longitudinal control, trim at high angles of attack, lateral stability, and lateral control are provided.
Date: February 1946
Creator: Seacord, Charles L., Jr. & Ankenbruck, Herman O.
Item Type: Refine your search to only Report
open access

Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel

Description: Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Ele… more
Date: February 1945
Creator: Campbell, John P. & Seacord, Charles L., Jr.
Item Type: Refine your search to only Report
open access

An Electron-Diffraction Examination of Cast-Iron Piston Rings From Single-Cylinder Aircraft Engine Tests

Description: Report presenting an electron-diffraction examination of cast-iron piston rings used in a single-cylinder test engine, which showed the presence of a layer of graphite covering the surface. The wear curves from the rings studied had shown variation from high rates to very low rates of wear.
Date: February 1945
Creator: Nowick, A. S. & Brockway, L. O.
Item Type: Refine your search to only Report
open access

Flight Investigation of Boundary-Layer Control by Suction Slots on an NACA 35-215 Low-Drag Airfoil at High Reynolds Numbers

Description: Report presenting an investigation of the effectiveness of suction slots as a means of extending the laminar boundary layer in flight at high Reynolds numbers on an NACA 35-215 airfoil. The results showed that, with a slot spacing of about 5 percent of the chord, the laminar boundary layer could be maintained to or slightly beyond 45 percent of the chord.
Date: February 1944
Creator: Zalovcik, John A.; Wetmore, J. W. & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
open access

Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers

Description: Report presenting an investigation of the effectiveness of suction slots a a means of extending the laminar boundary layer in flight at high Reynolds numbers using an NACA 35-215 airfoil. Tests were made over a range of indicated airspeeds, lift coefficients, and Reynolds numbers. Results regarding boundary-layer control, air-intake distributions, character of the boundary layer, total-intake rate, and profile-drag coefficient are provided.
Date: February 1944
Creator: Zalovcik, John A.; Wetmore, J. W. & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
open access

Investigation of Boundary Layer Transition on Concave Walls

Description: Report presenting an investigation of the transition of the boundary layer from the laminar to the turbulent regime on the concave side of a plate with a radius of curvature of 8.5 feet. Results regarding the mean speed distribution, effect of curvature on the position of the transition point, effect of the pressure gradient on transition, and effect of free stream turbulence on transition are provided.
Date: February 1945
Creator: Liepmann, H. W.
Item Type: Refine your search to only Report
open access

Knock-limited performance of several internal coolants

Description: Report presenting the effect of internal cooling on the knock-limited performance of AN-F-28 fuel in a CFR engine with the following internal coolants: water, methyl alcohol-water mixture, ammonia-methyl alcohol-water mixture, monomethyllamine-water mixture, dimethylamine-water mixture, and trimethylamine-water mixture.
Date: February 1944
Creator: Bellman, Donald R. & Evvard, John C.
Item Type: Refine your search to only Report
open access

NACA Radio Ground-Speed System for Aircraft

Description: Report presenting a method utilizing the Doppler effect on radio signals for determining the speed and distance traveled of an airplane. The method is called the NACA radio ground-speed system and uses the standard radio transmitter already found in most aircraft. Flight tests were made in which the method was used and the results were consisted with calibrated airspeed indications and stop-watch measurements.
Date: February 1943
Creator: Hastings, Charles E.
Item Type: Refine your search to only Report
open access

NACA Radio Ground-Speed System for Aircraft, Special Report

Description: "A method that utilizes the Doppler effect on radio signals for determining the speed of an airplane and the distance traveled by the airplane has been developed and found to operate satisfactorily. In this method, called the NACA radio ground-speed system, standard readily available radio equipment is used almost exclusively and extreme frequency stability of the transmitters is not necessary. No complicated equipment need be carried in the airplane, as the standard radio transmitter is usuall… more
Date: February 1943
Creator: Hastings, Charles E.
Item Type: Refine your search to only Report
open access

Occurrence of Iron Oxides on Cast-Iron Engine Surfaces After Operation

Description: Report presenting an examination of the surfaces of used cast-iron piston rings from various single-cylinder aircraft engine tests by electron diffraction. Generally, the oxide patterns were obtained to an appreciable extent from only the top compression ring of the piston-ring assembly; the other rings gave predominately a graphite pattern.
Date: February 1946
Creator: Nowick, A. S. & Brockway, L. O.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Description: "Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2" (p. 1).
Date: February 1943
Creator: Stack, John; Fedziuk, Henry A. & Cleary, Harold E.
Item Type: Refine your search to only Report
open access

The reduction of nonuseful pressure losses on air-cooled engine cylinders by means of improved finning and baffling

Description: Report presenting an analysis of the pressure drop that is required to cool a typically baffled radial engine, which shows that a total pressure drop of 58 pounds per square foot is necessary at sea level and 112 pounds per square foot is required at an altitude of 40,000 feet.
Date: February 1943
Creator: Wood, George P.
Item Type: Refine your search to only Report
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