UNT Libraries Government Documents Department - 154 Matching Results

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Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Item Type: Refine your search to only Report
open access

An Investigation of Loads on Ailerons at Transonic Speeds

Description: "Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. … more
Date: May 27, 1955
Creator: Runckel, Jack F. & Gray, W. H.
Item Type: Refine your search to only Report
open access

An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are i… more
Date: October 27, 1955
Creator: Gapcynski, John P.
Item Type: Refine your search to only Report
open access

Simplified procedures for estimating flap-control loads at supersonic speeds

Description: Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.
Date: May 27, 1955
Creator: Czarnecki, K. R. & Lord, Douglas R.
Item Type: Refine your search to only Report
open access

The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers

Description: Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.
Date: May 27, 1955
Creator: Polentz, Perry P.; Page, William A. & Levy, Lionel L., Jr.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Static Longitudinal and Lateral Stability of the Bell X-1A at Supersonic Speeds

Description: "An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).
Date: October 27, 1955
Creator: Henderson, Arthur, Jr.
Item Type: Refine your search to only Report
open access

Investigation of a Three-Stage Transonic Research Axial-Flow Compressor: Aerodynamic Design and Overall Performance

Description: Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.
Date: October 27, 1955
Creator: Savage, Melvyn & Beatty, Loren A.
Item Type: Refine your search to only Report
open access

A Theoretical Analysis of a Simple Aerodynamic Device to Improve the Longitudinal Damping of a Cruciform Missile Configuration at Supersonic Speeds

Description: Memorandum presenting a theoretical analysis of a cruciform missile configuration equipped with floating controls to determine if such controls can be utilized to improve the airframe transient response characteristics.The investigation covers either forward or aft locations of the floating controls at supersonic speeds. The results indicate that a substantial increase in airframe damping can be obtained through a proper selection of hinge-moment coefficients and through the use of a fixed-rate… more
Date: October 27, 1955
Creator: Clements, James E.
Item Type: Refine your search to only Report
open access

Flight measurements of the vertical-tail loads on the Convair XF-92A delta-wing airplane

Description: Report presenting the aerodynamic loads acting over the vertical tail, which were determined during an investigation of the lateral stability and control characteristics of the Convair XF-92A. Results regarding the vertical-tail panel characteristics, vertical-tail load parameters, and vertical-tail bending and normal-force coefficients are provided.
Date: October 27, 1955
Creator: Johnson, Clinton T.
Item Type: Refine your search to only Report
open access

Some Recent Experimental Data on Three-Dimensional Oscillating Air Forces

Description: Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.
Date: June 27, 1955
Creator: Leadbetter, Sumner A. & Clevenson, Sherman A.
Item Type: Refine your search to only Report
open access

Performance characteristics of hemispherical target-type thrust reversers

Description: Report presenting an investigation to determine the reverse-thrust performance of hemispherical target-type thrust reversers over a wide range of geometric variables. Several factors were found that increased the flow turn angle and reverse-thrust ratio, primarily the hemisphere diameter. Results regarding operating characteristics, relation of flow turn angle and reverse-thrust ratio, reverse-flow velocities and pressures along boattail, effect of boattail shape on reverse-thrust ratio, and mo… more
Date: September 27, 1955
Creator: Steffen, Fred W.; McArdle, Jack G. & Coats, James W.
Item Type: Refine your search to only Report
open access

The Effect of Wing Profile on the Transonic Characteristics of Rectangular and Triangular Wings Having Aspect Ratios of 3: Transonic Bump Technique

Description: Report presenting an investigation to determine the effect of wing profile on the transonic aerodynamic characteristics of rectangular and triangular wings with aspect ratios of 3. Five wings were compared over a range of Mach and Reynolds number. Results regarding the rectangular and triangular wings and use of transonic area rule are provided.
Date: October 27, 1954
Creator: Nelson, Warren H. & Frank, Joseph L.
Item Type: Refine your search to only Report
open access

Low-Speed Measurements of Rolling and Yawing Stability Derivatives of a 60 Degree Delta-Wing Model

Description: Memorandum presenting an investigation in the free-flight tunnel to determine the low-speed rolling and yawing stability derivatives of a 60 degree delta-wing model from 0 to 30 degrees angle of attack. The derivatives were measured by the free-to-damp oscillation technique and by the steady-roll technique.
Date: December 27, 1954
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
open access

Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models: TED No. NACA AD 398

Description: Report presenting testing of two scale models of the Chance Vought Regulus II missile to investigate its drag characteristics for a range of Mach numbers from 0.8 to 2.2. Due to some of the differences between the observed drag values and previous testing, the exact drag level of the configuration tested is still in question. Results regarding total drag and external drag are provided.
Date: July 27, 1954
Creator: Church, James D.
Item Type: Refine your search to only Report
open access

Performance of a 16-inch ram-jet engine with a can-type combustor at Mach numbers of 1.50 to 2.16

Description: Report presenting an investigation in the supersonic wind tunnel to evaluate the performance of a 16-inch ramjet engine using a can-type-combustor configuration. Data were obtained over a range of fuel-air ratios, free-stream Mach numbers, and angles of attack. Combustion efficiencies were generally unaffected by free-stream Mach number and varied between 60 and 90 percent with JP-4 fuel.
Date: August 27, 1954
Creator: Hearth, Donald P. & Perchonok, Eugene
Item Type: Refine your search to only Report
open access

Effect of rotation of a NACA 1-series E-type cowling on the internal flow and force characteristics of the cowling at Mach numbers up to 0.84 and at an angle of attack of 0 degrees

Description: Report presenting an investigation to determine the effect of rotation on the internal flow and force characteristics of an NACA 1-series E-type cowl, designed to operate with a four-blade single-rotation propeller. Results regarding internal-flow characteristics, force characteristics, and velocity distributions are provided.
Date: October 27, 1954
Creator: Sammonds, Robert I. & Reynolds, Robert M.
Item Type: Refine your search to only Report
open access

Experimental Investigation at High Subsonic Speeds to Determine the Rolling-Stability Derivatives of Three Wing-Fuselage Configurations

Description: Memorandum presenting rolling-stability derivatives for three wing configurations, which were tested on the same fuselage, over a range of Mach numbers and angles of attack. The wings were assorted plan-form configurations of current interest and were not part of a geometrically related series of plan forms. Results regarding basic damping-in-roll results, estimation of rolling derivatives, and estimated effects of Reynolds number are provided.
Date: October 27, 1954
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
open access

Longitudinal Stability Characteristics in Accelerated Maneuvers at Subsonic and Transonic Speeds of the Douglas D-558-II Research Airplane Equipped with a Leading-Edge Wing Chord-Extension

Description: Memorandum presenting an investigation of the Douglas D-558-II swept-wing research airplane with various modifications designed to alleviate swept-wing instability and pitch-up. In this study, the airplane was modified to include wing-chord extensions and was flight-tested.
Date: October 27, 1954
Creator: Fischel, Jack & Brunn, Cyril D.
Item Type: Refine your search to only Report
open access

Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds

Description: "The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
Date: June 27, 1955
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
open access

Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers Up to 1.9

Description: "Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by 6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions" (p. 1).
Date: March 27, 1957
Creator: Petersen, Robert B.
Item Type: Refine your search to only Report
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