766 Matching Results

Search Results

Results: 1 - 24 next
open access

Investigations toward simplification of missile control systems

Description: Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date: November 12, 1953
Creator: Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Description: Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are pr… more
Date: October 7, 1953
Creator: Radin, Edward J. & Carpenter, Paul J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds

Description: Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Date: July 10, 1953
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26

Description: Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Date: October 30, 1953
Creator: Martz, C. William & Goslee, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowa… more
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental study of five annular air inlet configurations at subsonic and transonic speeds

Description: Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, … more
Date: August 19, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R.; Fleming, Frank F. & Bryan, Carroll R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85

Description: Report presenting the results of an investigation to determine the static longitudinal and lateral stability and control characteristics of a model of the Republic MX-1554 airplane at a specified Mach and Reynolds number. No analysis was provided in the paper in order to expedite publication.
Date: March 18, 1953
Creator: Dickey, Robert R. & Spahr, J. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Study of the Tunnel-Boundary Lift Interference Due to Slotted Walls in the Presence of the Trailing-Vortex System of a Lifting Model

Description: "The equations presented in this report give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular. The rectangular tunnel is used to demonstrate these methods. The equations are also extended to nonuniformly loaded wings" … more
Date: February 3, 1953
Creator: Matthews, Clarence W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated spanwise lift distributions, influence functions, and influence coefficients for unswept wings in subsonic flow

Description: Spanwise lift distributions have been calculated for nineteen unswept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were aerodynamic influence coefficients which pertain to a certain definite set of stations along the span, and several methods are presented for calculating aerodynamic influence func… more
Date: May 5, 1953
Creator: Diederich, Franklin W. & Zlotnick, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Charts for estimating tail-rotor contribution to helicopter directional stability and control in low-speed flight

Description: "Theoretically derived charts and equations are presented by which tail-rotor design studies of directional trim and control response at low forward speed can be conveniently made. The charts can also be used to obtain the main-rotor stability derivatives of thrust with respect to collective pitch and angle of attack at low forward speeds. The use of the charts and equations for tail-rotor design studies is illustrated. Comparisons between theoretical and experimental results are presented. The… more
Date: October 27, 1953
Creator: Amer, Kenneth B. & Gessow, Alfred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Prediction of Pressure Distributions on Nonlifting Airfoils at High Subsonic Speeds

Description: "Theoretical pressure distributions on nonlifting circular-arc airfoils in two-dimensional flows with high subsonic free-stream velocity are found by determining approximate solutions, through an iteration process, of an integral equation for transonic flow proposed by Oswatitsch. The integral equation stems directly from the small-disturbance theory for transonic flow. This method of analysis possesses the advantage of remaining in the physical, rather than the hodograph, variable and can be a… more
Date: November 19, 1953
Creator: Spreiter, John R. & Alksne, Alberta
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated Lateral Frequency Response and Lateral Oscillatory Characteristics for Several High-Speed Airplanes in Various Flight Conditions

Description: "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 … more
Date: December 10, 1953
Creator: Jaquet, Byron M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooperative Investigation of Relationship Between Static and Fatigue Properties of Wrought N-155 Alloy at Elevated Temperatures

Description: Report presents the correlation of extensive data obtained relating properties of wrought N-155 alloy under static, combined static and dynamic, and complete reversed dynamic stress conditions. Time period for fracture ranged from 50 to 500 hours at room temperature, 1,000 degrees, 1,200 degrees, and 1,500 degrees F.
Date: June 15, 1953
Creator: NACA Subcommittee on Power-Plant Materials
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61

Description: Report presents the results of an investigation conducted to determine the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA rm-10 without fins) at Mach number of 1.61 and over a Reynolds number range from 2.5 x 10(6) to 35 x 10(6). The maximum cooling of the model used in these tests corresponded to a temperature ratio (ratio of model-surface temperature to free-stream temperature) of 1.12, a value somewhat higher than the theoretical value required … more
Date: February 16, 1953
Creator: Czarnecki, K. R. & Sinclair, Archibald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Studies of the speed stability of a tandem helicopter in forward flight

Description: Flight-test measurements, related analytical studies, and corresponding pilots' opinions of the speed stability of tandem-rotor helicopter are presented. An undesirable instability, evidenced by rearward stick motion with increasing forward speed at constant power, is indicated to be caused by variations with speed of the front-rotor downwash at the rear rotor. An analytical expression for predicting changes in speed stability caused by changes in rotor geometry is derived and constants for use… more
Date: June 4, 1953
Creator: Tapscott, Robert J. & Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Plastic Deformation of Aluminum Single Crystals at Elevated Temperatures

Description: "This report describes the results of a comprehensive study of plastic deformation of aluminum single crystals over a wide range of temperatures. The results of constant-stress creep tests have been reported for the temperature range from 400 degrees to 900 degrees F. For these tests, a new capacitance-type extensometer was designed. This unit has a range of 0.30 inch over which the sensitivity is very nearly linear and can be varied from as low a sensitivity as is desired to a maximum of 20 mi… more
Date: December 29, 1953
Creator: Johnson, R. D.; Young, A. P. & Schwope, A. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theory of wing-body drag at supersonic speeds

Description: "The relation of Whitcomb's "area rule" to the linear formulas for wave drag at lightly supersonic speeds is discussed. By adopting an approximate relation between the source strength and the geometry of a wing-body combination, the wave-drag theory is expressed in terms involving the areas intercepted by oblique planes or Mach planes. The resulting formulas are checked by comparison with the drag measurements obtained in wind-tunnel experiments and in experiments with falling models in free ai… more
Date: July 8, 1953
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and Control Characteristics at Low Speed of a 1/10-Scale Model of MX-1554A Design

Description: Report discussing an investigation of the low-speed stability and control characteristics of a model of the proposed MX-1554A design with a triangular wing and triangular stabilizing surfaces. It also includes the effect of wing incidence, slotted flaps, wing and tail height, external tanks and speed brakes, ground board, spoilers, tip ailerons, flaps, differential tail deflection, and an unswept wing on stability, control, aerodynamic, longitudinal, and lateral characteristics.
Date: 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design

Description: Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stabilit… more
Date: November 9, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design

Description: Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
Date: October 29, 1953
Creator: Lockwood, Vernard E.; Luoma, Arvo A. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Aerodynamic and Trim Characteristics of 1/15-Scale Models of the Convair MX-1964 Airplane With Indented Fuselage

Description: Report presenting an investigation of two scale models of the MX-1964 airplane with indented fuselage conducted in the transonic tunnel. One model had a plane delta wing with full-span elevons and the other had a cambered delta wing with partial-span elevons. Results regarding the aerodynamic characteristics and effect of elevon deflection are provided.
Date: 1953
Creator: Allis, Arthur E.; Swihart, John M. & Foss, Willard E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion

Description: Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
Date: January 19, 1953
Creator: Karp, Irving M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation

Description: Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.
Date: March 9, 1953
Creator: Spooner, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control

Description: Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.
Date: January 12, 1953
Creator: Smith, Willard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen