UNT Libraries Government Documents Department - 222 Matching Results

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Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Description: From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."
Date: September 20, 1955
Creator: Whittle, Edward F., Jr. & McLemore, H. Clyde
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 45^o, aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section parallel to the stream."
Date: July 20, 1949
Creator: Spreemann, Kenneth P.; Morrison, William D., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)

Description: Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle o… more
Date: July 20, 1950
Creator: Luidens, Roger W. & Simon, Paul C.
Item Type: Refine your search to only Report
open access

Aerodynamic control of supersonic inlets for optimum performance

Description: From Introduction: "The purpose of this paper is to discuss and evaluate some of the input signals or control parameters which have been experimentally employed to operate turbojet inlet-control systems. These include the normal-shock position, the oblique-shock position, and the diffuser-exit Mach number. The discussion is based on results obtained at the NACA Lewis laboratory during control investigations of ram-jet engines (ref. 1 to 5) and during a study on the control of a supersonic inlet… more
Date: February 20, 1956
Creator: Wilcox, Fred A. & Perchonok, Eugene
Item Type: Refine your search to only Report
open access

Aerodynamic Load Distribution on a 45 Degree Sweptback Wing With Leading-Edge Chord-Extensions at Transonic Speeds, Including Effects of a Spoiler-Slot-Deflector Aileron

Description: Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.
Date: February 20, 1958
Creator: Schmeer, James W.; Whitcomb, Charles F. & West, F. E., Jr.
Item Type: Refine your search to only Report
open access

Air Force Tests of Sperry Messenger Model With Six Sets of Wings

Description: From Summary: "The purpose of this test was to compare six well-known airfoils, the R.A.F 15, U.S.A. 5, U.S.A. 27, U.S.A. 35-B, Clark Y, and Gottingen 387, fitted to the Sperry Messenger model, at full scale Reynolds number as obtained in the variable density wind tunnel of the National Advisory Committee for Aeronautics; and to determine the scale effect on the model equipped with all the details of the actual airplane. The results show a large decrease in minimum drag coefficient upon increas… more
Date: January 20, 1927
Creator: Shoemaker, James M.
Item Type: Refine your search to only Report
open access

Altitude Performance of a Turbojet Engine Using Pentaborane Fuel

Description: Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments a… more
Date: May 20, 1957
Creator: Sivo, Joseph N.
Item Type: Refine your search to only Report
open access

Altitude performance of a turbojet engine using pentaborane fuel

Description: From Summary: "The primary objectives of the investigation reported herein were to determine the effect of this new combuster design on boric oxide deposition on engine parts and to determine the effect of boric oxide on the performance of multistage turbine. Pentaborance fuel (approx. 130 lb) was used in the engine performance evaluation reported herein. The data presented herein show the engine component and over-all performance deterioration with operation on pentaborane fuel".
Date: May 20, 1957
Creator: Sivo, Joseph N.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet-Propulsion Engines 2 - Analysis of Turbine Performance of the 19B-8 Engine

Description: "Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from an investigation of the complete engine in the Cleveland altitude wind tunnel. The investigation covered a range of simulated altitudes from 5000 to 30,000 feet and flight Mach numbers from 0.05 to 0.46 for various tail-cone positions over the entire operable range of engine speeds. The characteristics of the turbine are presented as functions of the total-pressure ratio across the turbine and th… more
Date: January 20, 1947
Creator: Krebs, Richard P. & Suozzi, Frank L.
Item Type: Refine your search to only Report
open access

Analysis and modification of theory for impact of seaplanes on water

Description: From Summary: "An analysis of available theory on seaplane impact and a proposed modification thereto are presented. In previous methods the overall momentum of the float and virtual mass has been assumed to remain constant during the impact but the present analysis shows that this assumption is rigorously correct only when the resultant velocity of the float is normal to the keel."
Date: August 20, 1945
Creator: Mayo, Wilbur L.
Item Type: Refine your search to only Report
open access

Analysis of performance of four symmetrical-diagram-type subsonic inlet-stage axial-flow compressors

Description: Report presenting an investigation of four axial-flow single-stage compressors with a hub-tip radius ratio of 0.5 with three objectives related to the ideal symmetrical-velocity-diagram design, the comparison of blade-element turning angle and loss data with cascade data, and the validity of the simplified radial-equilibrium equation. Results regarding the overall performance, blade-element performance, and radial equilibrium considerations are provided.
Date: January 20, 1954
Creator: Jackson, Robert J.
Item Type: Refine your search to only Report
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 1: liquid-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.
Date: February 20, 1953
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Item Type: Refine your search to only Report
open access

Approximate Stress Analysis of Multistringer Beams With Shear Deformation of the Flanges

Description: "The problem of the skin-stringer combinations used as axially loaded panels or as covers for box beams is considered from the point of view of the practical stress analyst. By a simple substitution the problem is reduced to the problem of the single-stringer structure, which has been treated in NACA Report no. 608. The method of making this substitution is essentially empirical; in order to justify it, comparisons are shown between calculations and strain-gage tests of three beams tested by th… more
Date: April 20, 1938
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
open access

Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-Body-Tail Configuration in Combination With Leading-Edge Devices

Description: Report presenting an investigation in the full-scale tunnel to determine the effects of the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. Results regarding half-span flaps and full-span flaps, pitching-moment and longitudinal trim characteristics, drag characteristics, lift-drag ratio, and lateral control are provided.
Date: July 20, 1956
Creator: McLemore, H. Clyde & Fink, Marvin P.
Item Type: Refine your search to only Report
open access

Calculated condenser performance for a steam turbine power plant for aircraft

Description: Report presenting calculations to determine the effect of several operating conditions on the performance of condensers for steam-turbine power plants. The analysis covered a range of turbine-inlet pressures and turbine-outlet pressures for various condenser cooling-air pressure drops, flight speeds, and altitudes. Results regarding steam-cycle performance, effect of turbine-outlet pressure on condenser performance, effect of cooling-air pressure drop on condenser performance, effect of turbine… more
Date: May 20, 1948
Creator: Humble, Leroy V. & Doyle, Ronald B.
Item Type: Refine your search to only Report
open access

Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58

Description: Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date: June 20, 1958
Creator: Hollinger, James A.
Item Type: Refine your search to only Report
open access

Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58: Coord. No. AF-204

Description: Memorandum presenting a longitudinal stability and control investigation made over a range of Mach numbers of a scale model of the Convair B-58 external store. Normal force, chord force, and static and dynamic stability derivatives formed an important part of the results. Results regarding the hinge moments and longitudinal trim and force coefficients are also provided.
Date: June 20, 1958
Creator: Hollinger, James A.
Item Type: Refine your search to only Report
open access

The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel

Description: An investigation of a large group of related airfoils was made in the NACA variable-density wind tunnel at a large value of the Reynolds number. The tests were made to provide data that may be directly employed for a rational choice of the most suitable airfoil section for a given application. The variation of the aerodynamic characteristics with variations in thickness and mean-line form were systematically studied. (author).
Date: December 20, 1932
Creator: Jacobs, Eastman N.; Ward, Kenneth E. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
open access

Coking of JP-4 fuels in electrically heated metal tubes

Description: A limited exploratory investigation of the rate of coking of four JP-4 fuels in electrically heated metal tubes was conducted in order to provide design information for fuel prevaporizers for turbojet-engine combustors. The fuels tested included two production and two minimum-quality JP-4 type fuels. The heating tube was operated at fuel pressures of approximately 500, 400, and 50 pounds per square inch. The operating fuel temperature was varied between approximately 600 degrees and 1200 degree… more
Date: November 20, 1956
Creator: Smith, Arthur L.; Cook, William P. & Hlavin, Vincent F.
Item Type: Refine your search to only Report
open access

Comparison Between Analytical and Wind-Tunnel Results on Flutter of Several Low-Aspect-Ratio, High-Density, Unswept Wings at High Subsonic Speeds and Zero Angle of Attack

Description: Memorandum presenting experimental flutter Mach numbers for several solid, thin, rectangular cantilever wings with uniform section properties, low aspect ratio, and high relative density estimated from the results of previous tests at zero angle of attack. The experimental values are considered estimates, rather than determinations, in the high subsonic speed range because in that range the amplitude criterion was necessarily arbitrary. Results regarding conservatism of standard analysis relati… more
Date: September 20, 1955
Creator: Warner, Robert W.
Item Type: Refine your search to only Report
open access

Comparison of Measured Efficiencies of Nine Turbine Designs with Efficiencies Predicted by Two Empirical Methods

Description: Empirical methods of Ainley and Kochendorfer and Nettles were used to predict performances of nine turbine designs. Measured and predicted performances were compared. Appropriate values of blade-loss parameter were determined for the method of Kochendorfer and Nettles. The measured design-point efficiencies were lower than predicted by as much as 0.09 (Ainley and 0.07 (Kochendorfer and Nettles).
Date: August 20, 1951
Creator: English, Robert E. & Cavicchi, Richard H.
Item Type: Refine your search to only Report
open access

Component Performance Investigation of J71 Type II Turbines 3 - Overall Performance of J71 Type IIA Turbine

Description: "The over-all component performance characteristics of the J71 Type IIA three-stage turbine were experimentally determined over a range of speed and over-all turbine total-pressure ratio at inlet-air conditions af 35 inches of mercury absolute and 700 deg. R. The results are compared with those obtained for the J71 Type IIF turbine, which was previously investigated, the two turbines being designed for the same engine application. Geometrically the two turbines were much alike, having the same … more
Date: January 20, 1955
Creator: Schum, Harold J.; Davison, Elmer H. & Petrash, Donald A.
Item Type: Refine your search to only Report
open access

Compressible-Flow Solutions for the Actuator Disk

Description: Report presenting generalized solutions for the actuator disk in subsonic compressible flow and the compressible- and incompressible-flow phenomena are compared. Results regarding the ideal solutions of flow variables, effect of additional losses, and actuator disks in tandem are provided. Large differences in flow variables were observed across the actuator disk.
Date: March 20, 1953
Creator: Delano, James B. & Crigler, John L.
Item Type: Refine your search to only Report
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