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Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."
Date: August 11, 1958
Creator: Stoney, William E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls

Description: Report discussing an investigation to determine the aerodynamic characteristics of hypersonic missile configurations with cruciform trailing-edge flaps with all-movable control surfaces. The all-movable controls were found to produce much larger values of trim lift and normal acceleration than the trailing-edge-flap configuration.
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96

Description: Report presenting a 45 degree sweptback wing of aspect ratio 3, with twist and a distributed type of camber, tested in combination with a body of fineness ratio 12.5 to determine the lift, drag, and pitching-moment characteristics.
Date: August 11, 1958
Creator: Sammonds, Robert I. & Reynolds, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0

Description: Report presenting an investigation of two internal-contraction inlets in the block tunnel. The fixed inlet was tested at Mach number 2.94 with a conventional ram-scoop bleed and a shock-trap bleed. Results regarding the fixed-capture-area inlet and variable-capture-area inlet are provided.
Date: August 14, 1958
Creator: Luidens, Roger W. & Flaherty, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of the low-speed characteristics of a 45 degree swept-wing fighter-type airplane with blowing boundary-layer control applied to the trailing edge flaps

Description: Report presenting a flight investigation to determine the low-speed flight characteristics of a 45 degree swept-wing fighter-type airplane with boundary-layer control on the trailing-edge flaps. The effectiveness of the flap with and without boundary-layer control was determined in conjunction with several slat modifications. The study also included low-speed flying qualities and a pilot evaluation of the operational use of the boundary-layer control system in landing approaches.
Date: August 4, 1958
Creator: Quigley, Hervey C.; Anderson, Seth B. & Innis, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Forces and pitching moments on an aspect-ratio-3.1 wing-body combination at Mach numbers from 2.5 to 3.5 and sublimation studies of the effect of single-elements roughness on the boundary-layer flow

Description: Report presenting lift, drag, and pitching-moment characteristics for a wing-body combination for a range of Mach numbers. The wing had an aspect ratio of 3.1, a sweepback of the leading edge of 19.1 degrees, a taper ratio of 0.39, and a biconvex profile with a thickness of 3 percent of the chord. Results regarding aerodynamic characteristics and visual-flow studies are provided.
Date: August 26, 1958
Creator: Hopkins, Edward J.; Keating, Stephen J., Jr. & Muhl, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic lateral behavior of high-performance aircraft

Description: Report presenting a study of several proposed high-performance aircraft to define some problem areas in dynamic lateral behavior of high-speed aircraft which require specific attention. Aileron control problems and Dutch roll characteristics with and without artificial damping were explored in depth.
Date: August 6, 1958
Creator: Moul, Martin T. & Paulson, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of the effect of yaw on rates of heat transfer to transverse circular cylinders in a 6500-foot-per-second hypersonic air stream

Description: Report describing equipment that can be used to shock-compress air by helium to 3660 degrees Rankine to generate a 6500-foot-per-second air stream with a flow duration of 40 milliseconds. The influence of yaw on rates of heat transfer to the same circular cylinders was investigated at angles of yaw up to 70 degrees.
Date: August 26, 1958
Creator: Cunningham, Bernard E. & Kraus, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of effects of interceptor roll performance and maneuverability on success of collision-course attacks

Description: From Introduction: "In the present paper, calculations are presented to show the relative effects of wide variations in the roll performance and normal-accleration capability. Brief analyses are also included to show the effect on the success of attacks of other design factors such as speed and radar range."
Date: August 6, 1958
Creator: Phillips, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds

Description: Report presenting a wind-tunnel investigation performed in the high-speed tunnel to study the effect of wing sweep and taper ratio on spoiler-slot-deflector control effectiveness. All of the wings tested were aspect-ratio-4 and had NACA 65A004 airfoil sections as well as a variety of sweep angles, taper ratios, and spoiler projections. The results are presented without analysis.
Date: August 14, 1958
Creator: Hammond, Alexander D. & McKinney, Linwood W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Low-Speed Stability and Performance Characteristics of a Jet-Powered Low-Aspect-Ratio Vertical-Take-Off-and-Landing Configuration With Engines Buried in Tiltable Wings

Description: Report presenting an investigation in the full-speed tunnel to determine the low-speed stability and performance characteristics of a model of a jet-powered airplane configuration capable of vertical takeoff and landing with engines in a tiltable low-aspect-ratio wing. Static longitudinal and lateral characteristics were obtained for various angles of attack, wing tilt angles, and thrust coefficient suitable for takeoff and landing.
Date: August 6, 1958
Creator: Scallion, William I. & Cone, Clarence D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge

Description: From Introduction: "The results obtained in the wind-tunnel tests at Mach numbers 2.36 and 2.87 for several configurations utilizing this wing, including results on the wing alone are presented."
Date: August 4, 1958
Creator: Hallissy, Joseph M., Jr. & Hasson, Dennis F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests

Description: Memorandum presenting a flight investigation to determine the thrust and pumping characteristics of a family of aircraft exhaust ejectors. Information was obtained on the variation of these characteristics with changes in engine power, flight Mach number, and ejector spacing ratio, and these results were compared to small-scale tests. Results were also obtained showing how a swinging survey probe can be used as a device for calibrating a tail-pipe pressure probe for the measurement of thrust an… more
Date: August 26, 1958
Creator: Havill, C. Dewey & Wingrove, Rodney C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of an All-Internal Conical Compression Inlet with Annular Throat Bleed at Mach Number 5.0

Description: From Summary: "An all-internal conical compression inlet with annular bleed at the throat was investigated at Mach 5.0 and zero angle of attack. The minimum contraction ratio of the supersonic diffuser, coincident with a mass-flow ratio of 1.0, was determined to be 0.084 as compared with the isentropic contraction ratio of 0.04 at Mach 5.0. The over-all inlet performance was very sensitive to the amount of annular bleed at the throat because of the extensive boundary layer."
Date: August 6, 1958
Creator: Stitt, Leonard E. & Obery, Leonard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08

Description: Report presenting an investigation in the 9- by 9-inch Mach number 4 blowdown jet on a generalized body-wing-tail missilelike configuration to determine the source of the adverse rolling moment due to yaw experienced by this type of configuration with lifting surfaces and ventral and dorsal tail surfaces. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: August 14, 1958
Creator: Smith, Fred M.; Ulmann, Edward F. & Dunning, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression

Description: Report presenting an investigation of the internal-flow characteristics of two novel designs of internal-compression air inlets in the supersonic blowdown tunnel. A longitudinally slotted contracting channel and effective contracting channel formed by the natural thickening of the boundary layer in a confined channel can be used to obtain pressure recoveries at a satisfactory level.
Date: August 14, 1958
Creator: Howell, Robert R. & Trescot, Charles D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight

Description: Report presenting the results of an investigation of the dynamic stability and controllability of a proposed supersonic-cruise, vertical-take-off-and-landing airplane configuration with a tilting wing and engines. The configuration tested was found to have satisfactory take-off, landing, and hovering characteristics. Information about transition flight, including stability and control characteristics, is provided.
Date: August 26, 1958
Creator: Kirby, Robert H. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane

Description: Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
Date: August 1, 1958
Creator: McKinney, Marion O. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls

Description: Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree … more
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability of Ballistic Reentry Bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands

Description: Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date: August 11, 1958
Creator: Stoney, William E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile

Description: Report discussing the longitudinal static and dynamic stability, overall duct performance, drag, and some static and dynamic lateral-stability data obtained from testing of the Chance Vought Regulus II missile. Five different models with various modifications were used in the investigation.
Date: August 19, 1958
Creator: Wineman, Andrew R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental and Analytical Investigation of the Transonic and Supersonic Divergence Characteristics of a Delta-Plan-Form All-Movable Control

Description: "The static aeroelastic divergence characteristics of a delta-plan-form model of the canard control surface of a proposed air-to-ground missile have been studied both analytically and experimentally in the Mach number range from 0.6 to 3.0. The experiments indicated that divergence occurred at a nearly constant value of dynamic pressure at Mach numbers up to 1.2. At higher Mach numbers somewhat higher values of dynamic pressure were required to produce divergence" (p. 1).
Date: August 4, 1958
Creator: Rainey, A. Gerald; Hanson, Perry W. & Martin, Dennis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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