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Rocket-Model Measurements of Zero-Lift Damping in Roll of the Bell MX-776 Missile at Mach Numbers from 0.6 to 1.56
The zero-lift damping in roll of the Bell MX-776 missile has been measured by a sting-mounted rocket-model technique at Mach numbers from 0.6 to 1.56. The damping-in-roll data, in general, show no unusual variation with Mach number. Aileron rolling-moment effectiveness derived from these data and previously obtained rolling-effectiveness data appear reasonable,.
Date:
December 31, 1953
Creator:
Bland, William M., Jr. & Purser, Paul E.
System:
The UNT Digital Library
Calibration of the Friez Aerovane, Wind Measuring Set AN/GMQ-11
Calibrations of the Friez Aerovane, Wind Measuring Set AN/GMQ-11, manufactured by the Friez Instrument Division of the Bendix Aviation Corporation, were made in the Langley 300 MPH 7- by 10-foot tunnel at the request of the Signal Corps, U, S. Army. Two propellers snd two generators were tested through a speed range of 15 to 190 knots, The results indicated that at airspeeds greater than 80 knots the instrument indicated airspeeds higher than the tunnel airspeed..
Date:
December 29, 1953
Creator:
McKee, John W.
System:
The UNT Digital Library
The Results of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
Report presenting a wind-tunnel investigation to study the effects of operating propellers on the low-speed longitudinal characteristics of a four-engine tractor airplane configuration. The coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are provided. Tests were conducted at a range of Mach and Reynolds numbers.
Date:
December 21, 1953
Creator:
Edwards, George G.; Buell, Donald A. & Dickson, Jerald K.
System:
The UNT Digital Library
Effects of additives on pressure limits of flame propagation of propane-air mixtures
Report presenting a study of seven additives in 0.5-volume-percent concentration for their effects on the low-pressure limits of flame propagation of propane-air mixtures. Limits were measured in a flame tube of new design. Results regarding propane-air mixtures, propane-air-additive mixtures, and flame propagation qualities are provided.
Date:
December 18, 1953
Creator:
Belles, Frank E. & Simon, Dorothy M.
System:
The UNT Digital Library
Experimental Investigation of Laminar-Boundary-Layer Control on an Airfoil Section Equipped With Suction Slots Located at Discontinuities in the Surface Pressure Distribution
Memorandum presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.
Date:
December 15, 1953
Creator:
Loftin, Laurence K., Jr. & Horton, Elmer A.
System:
The UNT Digital Library
Experimental investigation of laminar-boundary-layer control on an airfoil section equipped with suction slots located at discontinuities in the surface pressure distribution
Report presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The airfoil section was designed to have favorable pressure gradients between the suction slots. Results indicated that the laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the surface condition as has been observed in other similar investigations.
Date:
December 15, 1953
Creator:
Loftin, Laurence K., Jr. & Horton, Elmer A.
System:
The UNT Digital Library
Effect of Large Deflection of a Canard Control and Deflections of a Wing-Tip Control on the Static-Stability and Induced-Roll Characteristics of a Cruciform Canard Missile at a Mach Number of 2.01
Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the static stability and control characteristics of a canard-type missile configuration with large deflections of the canard controls and with deflection of wing-tip controls. The results of the investigation indicated that with a 30 degree deflection of the canard control a maximum trim normal-force coefficient of 0.4 and a maximum trim angle of attack of 12 degrees might be obtained for the optimum center-of-gravity location.
Date:
December 14, 1953
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library
Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio
Report presenting testing of supersonic compressor blades with rounded leading edges with an 8-percent mean thickness-chord ratio and a solidity of about 2.5 were incorporated in a 16-inch-diameter rotor with and without guide vanes. Results regarding the overall performance, rotor-blade-element performance, and rotor without guide vanes are provided.
Date:
December 11, 1953
Creator:
Goldberg, Theodore J.; Boxer, Emanuel & Bernot, Peter T.
System:
The UNT Digital Library
Flow Coefficients for Orifices in Base of Transpiration-Cooled Turbine Rotor Blade
Static tests on a segment of a transpiration-cooled turbine rotor blade with a wire-cloth shell were conducted to determine the flow coefficients associated with some representative metering orifices. Average flow coefficients from 0.96 to 0.79 were obtained for orifices of 0.031 to 0.102 inch diameter.
Date:
December 11, 1953
Creator:
Donoughe, Patrick L. & Prasse, Ernst I.
System:
The UNT Digital Library
Investigation at transonic speeds of aerodynamic characteristics of a semielliptical air inlet in the root of a 45 degree sweptback wing
Report presenting an investigation in the transonic blowdown tunnel at a range of Mach numbers to determine the increments in lift, drag, and pitching moments due to the installation of a semielliptical-shaped air inlet in the root of a 45 degree sweptback wing and to study the internal flow characteristics of the inlet. Results regarding the internal pressure measurements, effect of inlet installation on external aerodynamic characteristics, effect of boundary-layer removal on internal pressure recovery, and inlet performance are provided.
Date:
December 11, 1953
Creator:
Howell, Robert R. & Trescot, Charles D., Jr.
System:
The UNT Digital Library
An Investigation of Continuous Boundary-Layer Removal in an Axial Flow Compressor With Porous Walls
Report presenting an investigation made to improve compressor performance by bleedoff of detrimental boundary layer through a porous compressor casing. The results were compared to the performance characteristics of the original engine. Bleedoff was found to increase the efficiency of the compression process, but the overall performance of the turbojet suffered.
Date:
December 11, 1953
Creator:
Wlodarski, John
System:
The UNT Digital Library
Calculated Lateral Frequency Response and Lateral Oscillatory Characteristics for Several High-Speed Airplanes in Various Flight Conditions
"Calculations have been made to determine the effects of Mach number and altitude on the lateral frequency response, the lateral response to a lateral sinusoidal gust distribution, and the period and damping of the lateral oscillation for the North American F-86A, Grumman F9F-2, Republic F-84, Douglas D-558-II, and Bell X-1 airplanes without autopilots. Aeroelastic and unsteady lift effects have not been included in the calculations and may have a large effect on the results for certain flight conditions. The results of the investigation are presented, without analysis, for reference purposes" (p. 1).
Date:
December 10, 1953
Creator:
Jaquet, Byron M.
System:
The UNT Digital Library
Effects of External Store Mounting on the Buffet, Trim, and Drag Characteristics of Rocket-Powered Fuselage and Store Combinations Between Mach Numbers of 0.7 and 1.4
Memorandum presenting an investigation made of the effects of store mounting on the buffet, trim, and drag characteristics of fuselage-mounted external stores between Mach numbers of 0.7 and 1.4 by the use of the rocket-propelled-model technique. Results of the tests are presented in the incremental accelerations in the stores due to buffeting, trim normal- and side-force coefficients, tail helix angles, and drag coefficients plotted against Mach number.
Date:
December 10, 1953
Creator:
Mason, Homer P.
System:
The UNT Digital Library
An experimental investigation of the transonic-flow-generation and shock-wave-reflection characteristics of a two-dimensional wind tunnel with 24-percent-open, deep, multislotted walls
Report presenting the flow-generation and shock-wave-reflection characteristics of a two-dimensional tunnel with 24-percent-open, deep, multislotted walls. The deep multislotted wall proved unsatisfactory as a means of reducing boundary-reflected disturbances, because a mixed disturbance was reflected from the wall. Results regarding flow generation, shock-wave reflection, subsonic operation of test section with deep multislotted walls, and outflow requirements are provided.
Date:
December 10, 1953
Creator:
Sellers, Thomas B.; Davis, Don D. & Stokes, George M.
System:
The UNT Digital Library
The Influence of the Control-Surface-Servo Natural Frequency Upon the Transient Characteristics of a Flight-Path-Angle Control System Incorporating a Supersonic Missile
Report presenting a theoretical investigation to determine the effects of control-surface-servo natural frequency on the transient characteristics of a flight-path-angle control system for three values of airframe static margin and five flight conditions. Results regarding response time, attitude accuracy, total volume of oil flow, peak rate of oil flow, and maximum normal acceleration for the missiles tested are provided.
Date:
December 10, 1953
Creator:
Passera, Anthony L. & Bridgland, Thomas F., Jr.
System:
The UNT Digital Library
The Use of a Leading-Edge Area-Suction Flap to Delay Separation of Air Flow From the Leading Edge of a 35 Degrees Sweptback Wing
"An investigation was conducted on a 35 degree swept-wing model to determine the aerodynamic characteristics and suction requirements of a model having a leading-edge area-suction flap deflected 40 degrees" (p. 1). The procedures, corrections needed, force characteristics, suction requirements, and pressure distributions are described.
Date:
December 10, 1953
Creator:
Holzhauser, Curt A. & Martin, Robert K.
System:
The UNT Digital Library
Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack
Report presenting a method to estimate the incompressible-flow surface pressures of compressor airfoils in cascade at design angle of attack by modifying the known pressure distribution as an isolated airfoil. The interference between airfoils was found to vary in a systematic manner. Testing performed on NACA 65-series compressor blade sections appears to agree with estimated values.
Date:
December 9, 1953
Creator:
Erwin, John R. & Yacobi, Laura A.
System:
The UNT Digital Library
Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack
"A method was devised for estimating the incompressible-flow pressure distribution over compressor blade sections at design angle of attack. The theoretical incremental velocities due to camber and thickness of the section as an isolated airfoil are assumed proportional to the average passage velocity and are modified by empirically determined interference factors. Comparisons were made between estimated and test pressure distributions of NACA 65-series sections for typical conditions. Good agreement was obtained" (p. 1).
Date:
December 9, 1953
Creator:
Erwin, John R. & Yacobi, Laura A.
System:
The UNT Digital Library
Preliminary Investigation of the Total-Pressure-Recovery Characteristics of a Symmetric and Asymmetric Nose Inlet Over a Wide Range of Angle of Attack at Supersonic Mach Numbers
Report presenting an investigation of the total-pressure-recovery characteristics over a wide range of angles of attack of an axially symmetric nose inlet at a Mach number of 1.42 and an asymmetric nose inlet at Mach numbers of 1.42 and 1.84.
Date:
December 9, 1953
Creator:
Carter, Howard S. & Merlet, Charles F.
System:
The UNT Digital Library
A Preliminary Investigation at Mach Number 1.91 of a Diffuser Employing a Pivoted Cone to Improve Operation at Angle of Attack
Report presenting an investigation to determine the performance of a conical-nose supersonic diffuser at angle of attack. The inlet had a pivoting cone which could be oriented to any of several angles independent of the angle of attack of the diffuser. Results regarding total-pressure recovery and mass-flow characteristics, cowl lip position, cone position relative to angle of attack, shadowgraphs, and contour maps are provided.
Date:
December 8, 1953
Creator:
Beheim, Milton A.
System:
The UNT Digital Library
A Preliminary Study by Means of Electrical Frequency-Analysis Techniques of the Response of an Airplane Structure During Buffeting
Report presenting a flight investigation to study in detail the response of an airplane structure during buffeting. Measurements of acceleration on selected points were made during buffeting for two different conditions of lift coefficient and Mach number and the time histories of acceleration were studied using electrical frequency-analysis techniques. Results regarding the ground response measurements, response to buffeting excitation, verification of the measured results, and the pilot's observation of the buffeting are provided.
Date:
December 8, 1953
Creator:
Yeates, John E., Jr. & Thompson, Jim Rogers
System:
The UNT Digital Library
Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing
Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a spoiler-slot-deflector combination in producing rolling moments in the transonic speed range at angles of attack as high as 24 degrees over a range of Mach numbers. The wing had an aspect ratio of 4, a taper ratio of 0.6, an unswept quarter-chord line, and NACA 65A006 airfoil sections.
Date:
December 8, 1953
Creator:
Vogler, Raymond D.
System:
The UNT Digital Library
Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 1: Rotor Design and Over-All Performance at Tip Speeds From 60 to 100 Percent of Design
Memorandum presenting an inlet-type axial-flow compressor rotor with a hub-tip diameter ratio of 0.4 at the rotor leading edge, which was designed, fabricated, and experimentally investigated. The results of the investigation indicated that stages with inlet hub-tip ratios as low as 0.4 can be designed within known practical aerodynamic specifications to produce satisfactory values of stage pressure ratio and efficiency at high specific weight flows.
Date:
December 7, 1953
Creator:
Serovy, George K.; Robbins, William H. & Glaser, Frederick W.
System:
The UNT Digital Library
Investigation of a Related Series of Turbine-Blade Profiles in Cascade
From Summary: "An application of airfoil design methods was used to design series of related turbine-blade profiles to satisfy the conditions of inlet flow angle and turning angle encountered in the usual range of turbine operation. A series of blade profiles applicable to most turbine blading requirements and a secondary series with particular reference to impulse conditions were designed. Five blade sections from these series ranging in mean-line turning angles from 63 deg. to 120 deg. were tested in low-speed cascade tunnels."
Date:
December 7, 1953
Creator:
Dunavant, James C. & Erwin, John R.
System:
The UNT Digital Library