Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models (open access)

Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models

Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each airplane type.
Date: July 23, 1957
Creator: Smith, Willard G. & Intrieri, Peter F.
System: The UNT Digital Library
Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98 (open access)

Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98

Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.
Date: August 23, 1955
Creator: Jorgensen, Leland H. & Perkins, Edward W.
System: The UNT Digital Library
Effects of Taper Ratio on the Longitudinal Characteristics at Mach Numbers From 0.6 to 1.4 of a Wing-Body-Tail Combination Having an Unswept Wing of Aspect Ratio 3 (open access)

Effects of Taper Ratio on the Longitudinal Characteristics at Mach Numbers From 0.6 to 1.4 of a Wing-Body-Tail Combination Having an Unswept Wing of Aspect Ratio 3

Report presenting the results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at a variety of Mach numbers. The wings had an aspect ratio of 3, an unswept midchord line, and an NACA 64A003 profile. Results regarding the lift and pitching-moment characteristics and drag characteristics are provided.
Date: March 23, 1955
Creator: Summers, James L.; Treon, Stuart L. & Graham, Lawrence A.
System: The UNT Digital Library
A method for evaluating the loads and controllability aspects of the pitch-up problem (open access)

A method for evaluating the loads and controllability aspects of the pitch-up problem

Report presenting a procedure for estimating the range of peak airplane load factors and maneuvering tail loads likely to be experienced in pitch-up maneuvers. Results of computations indicated that though the load factors and maneuvering tail loads were not critical in pitch-up maneuvers at 35,000 feet, they were likely to exceed design levels at 15,200 feet.
Date: August 23, 1955
Creator: Sadoff, Melvin; Matteson, Frederick H. & Havill, C. Dewey
System: The UNT Digital Library
Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron (open access)

Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron

Report presenting an investigation in the full-scale tunnel to determine the effects on the aerodynamic characteristics of a 49.1 degree sweptback wing of blowing a high-energy stream of air over a trailing-edge flap and an aileron. The results indicated that significant increases in lift coefficient and an improvement in aileron effectiveness may be obtained by the blowing method of boundary-layer control.
Date: April 23, 1954
Creator: Whittle, Edward F., Jr. & Lipson, Stanley
System: The UNT Digital Library
Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane (open access)

Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane

Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
Date: April 23, 1958
Creator: Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
System: The UNT Digital Library
Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds (open access)

Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds

Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.
Date: August 23, 1955
Creator: Neely, Robert H. & Griner, Roland F.
System: The UNT Digital Library
Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51 (open access)

Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51

Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date: June 23, 1958
Creator: Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
System: The UNT Digital Library
Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model (open access)

Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model

Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.
Date: August 23, 1956
Creator: Paulson, John W. & Boisseau, Peter C.
System: The UNT Digital Library
Material Compatibility With Gaseous Fluorine (open access)

Material Compatibility With Gaseous Fluorine

Report presenting static tests on the compatibility of gaseous fluorine with various liquids, solid plastics, waxes, and greases at pressures of 0 and 1500 pounds per square inch gage and atmospheric temperature. Several materials were found to be compatible at atmospheric pressure, but only Teflon and ruby were compatible under static conditions at 1500 pounds per square inch gage.
Date: January 23, 1957
Creator: Price, Harold G., Jr. & Douglass, Howard W.
System: The UNT Digital Library
Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7 (open access)

Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7

Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.
Date: September 23, 1952
Creator: Chubb, Robert S.
System: The UNT Digital Library
Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control (open access)

Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control

Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.
Date: August 23, 1957
Creator: Luoma, Arvo A.
System: The UNT Digital Library
An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System (open access)

An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System

Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible to the pilots.
Date: November 23, 1956
Creator: Douvillier, Joseph G., Jr.; Foster, John V. & Drinkwater, Fred J., III
System: The UNT Digital Library
Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95 (open access)

Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95

Memorandum presenting the effect of blunting on the internal performance of a two-cone inlet with an internally cylindrical cowl investigated experimentally at Mach number 4.95. Total-pressure-recovery and mass-flow data were obtained for a range of spike and cowl bluntness.
Date: September 23, 1958
Creator: Weston, Kenneth C.
System: The UNT Digital Library
Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet (open access)

Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet

Report presenting an investigation of the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in the supersonic wind tunnel. The investigation was carried out to determine the performance penalties associated with spike-tip and cowl-lip blunting. Results regarding the effect of rounding the spike tip on inlet performance, overall drag coefficients, flow distortion, and Schileren photographs are provided.
Date: September 23, 1958
Creator: Cubbison, R. W. & Samanich, N. E.
System: The UNT Digital Library
Experimental Investigation of Boundary-Layer Suction Through Slots to Obtain Extensive Laminar Boundary Layers on a 15 Percent-Thick Airfoil Section at High Reynolds Numbers (open access)

Experimental Investigation of Boundary-Layer Suction Through Slots to Obtain Extensive Laminar Boundary Layers on a 15 Percent-Thick Airfoil Section at High Reynolds Numbers

Memorandum presenting a two-dimensional wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and difficulties encountered in obtaining extensive laminar flow are provided.
Date: June 23, 1952
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
System: The UNT Digital Library
Experimental Study of Isothermal Wake-Flow Characteristics of Various Flame-Holder Shapes (open access)

Experimental Study of Isothermal Wake-Flow Characteristics of Various Flame-Holder Shapes

"An investigation of the isothermal wake-flow characteristics of several flame-holder shapes was carried out in a 4- by 4-inch flow chamber. The effects of flame-holder-shape changes on the characteristics of the Karman vortices and thus on the recirculation zones to which experimenters have related the combustion process were obtained for several flame holders. The results may furnish a basis of correlation, of combustion efficiency and stability for similarly shaped flame holders in combustion studies" (p. 1).
Date: January 23, 1952
Creator: Younger, George G.; Gabriel, David S. & Mickelsen, William R.
System: The UNT Digital Library
Some Flight Data for the Chance Vought Regulus 2 Missile (open access)

Some Flight Data for the Chance Vought Regulus 2 Missile

Report discussing tests of a model of the Chance Vought Regulus II missile to determine the lift, static stability, dynamic stability, trim, duct information, and drag for a range of Mach numbers.
Date: April 23, 1956
Creator: Wineman, Andrew R.
System: The UNT Digital Library
Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds (open access)

Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds

Control trailing-edge thickness and aspect ratio effect on oscillating hinge-moment and flutter characteristics of flap-type controls. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date: April 23, 1958
Creator: Moseley, William C., Jr. & Thompson, Robert F.
System: The UNT Digital Library
Experimental Study of Ballistic-Missile Base Heating with Operating Rocket (open access)

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

"A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor" (p. 1).
Date: September 23, 1958
Creator: Nettles, J. Cary
System: The UNT Digital Library
Summary of NACA Research on Afterburners for Turbojet Engines (open access)

Summary of NACA Research on Afterburners for Turbojet Engines

Report presenting a summary of NACA research on afterburners for turbojet engines during the past 5 years. The references present over 1000 afterburner configurations and about 3500 hours of operation. The report covers the following topics: burner-inlet diffusers, fuel-injection systems, flameholders, combustion space, combustion instability, starting and transient performance, effects of diluents, and burner-shell cooling.
Date: March 23, 1956
Creator: Lundin, Bruce T.; Gabriel, David S. & Fleming, William A.
System: The UNT Digital Library
Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0 (open access)

Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0

"Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg" (p. 1).
Date: September 23, 1958
Creator: Anderson, Bernhard H. & Bowditch, David N.
System: The UNT Digital Library
Aerodynamic Loads on Tails at High Angles of Attack and Sideslip (open access)

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

"Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).
Date: July 23, 1957
Creator: Spahr, J. Richard & Polhamus, Edward C.
System: The UNT Digital Library
Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09 (open access)

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09

Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.
Date: March 23, 1956
Creator: Carmel, Melvin M. & Gregory, Donald T.
System: The UNT Digital Library