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Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle

Description: Memorandum presenting data from an investigation of the effect of curved speed brakes on the drag characteristics and on the longitudinal stability and control characteristics of a scale model of the MX-1554A airplane redesigned to incorporate a circular jet nozzle. The speed brakes were tested at several deflections,gaps, and locations on the landing configuration and the clean configuration.
Date: January 7, 1954
Creator: Solomon, Martin
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Interference Effects during Separation of a 1/40-Scale Model Convair B-58 Airplane and Store at Mach Numbers of 1.41, 1.61, and 2.01

Description: "An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a 1/40-sca!e pod-separation model of the Convair B-58 airplane at Mach numbers of 1.41, 1.61, and 2.01. The complete return component and the complete pod with its canard controls were tested, both alone and in the presence of each other, at Mach numbers of 1.61 and 2.01. The complete pod and various combinations of its components were tested alone at Mach numbers of 1.41, 1.61, and 2.01 and also in the presence of the return component at Mach numbers of 1.61 and 2.01" (p. 1).
Date: December 28, 1956
Creator: Driver, Cornelius
Partner: UNT Libraries Government Documents Department

Rocket-Model Measurements of Zero-Lift Damping in Roll of the Bell MX-776 Missile at Mach Numbers from 0.6 to 1.56

Description: 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.
Partner: UNT Libraries Government Documents Department

Stability and control characteristics at low speed of a modified 1/10-scale model of the MX-1554A design

Description: Report presenting an investigation of the low-speed stability and control characteristics of a modified scale model of the MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. The modifications of the design included an increase in slotted-flap span, a redesigned tip aileron, fuselage tail cone, and speed brakes.
Date: November 19, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Partner: UNT Libraries Government Documents Department

Stability and control characteristics at low speed of a 1/10-scale model of MX-1554A design

Description: Report presenting an investigation of the low-speed stability and control characteristics of a scale model of the proposed MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. Results regarding the effect of wing incidence, tail position, fences, and chord extensions on the longitudinal characteristics are provided.
Date: January 13, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Description: From Introduction: "Results from the tests in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 are presented in reference 1. Reported herein are results obtained from the tests in the Langley 8-foot transonic tunnel of the model with no control deflections at Mach numbers 0.6 to 1.12 for angles of attack up to 34^o
Date: March 18, 1954
Creator: Osborne, Robert S. & Wornom, Dewey E.
Partner: UNT Libraries Government Documents Department

Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Convair YF-102 Airplane in the Langley Free-Flight Tunnel

Description: From Summary: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Convair YF-102 airplane has been made in the Langley free-flight tunnel. The model was flown over a lift-coefficient range from 0.5 to the stall in its basic configuration and with several modifications involving leading-edge slats and increases in vertical-tail size. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect of freeing the controls."
Date: November 18, 1953
Creator: Johnson, Joseph L., Jr. & Boisseau, Peter C.
Partner: UNT Libraries Government Documents Department

A Cartesian grid embedded boundary method for Poisson`s equation on irregular domains

Description: The authors present a numerical method for solving Poisson`s equation, with variable coefficients and Dirichlet boundary conditions, on two-dimensional regions. The approach uses a finite-volume discretization, which embeds the domain in a regular Cartesian grid. They treat the solution as a cell-centered quantity, even when those centers are outside the domain. Cells that contain a portion of the domain boundary use conservation differencing of second-order accurate fluxes, on each cell volume. The calculation of the boundary flux ensures that the conditioning of the matrix is relatively unaffected by small cell volumes. This allows them to use multi-grid iterations with a simple point relaxation strategy. They have combined this with an adaptive mesh refinement (AMR) procedure. They provide evidence that the algorithm is second-order accurate on various exact solutions, and compare the adaptive and non-adaptive calculations.
Date: January 1997
Creator: Johansen, H. & Colella, P.
Partner: UNT Libraries Government Documents Department

Detonation propagation and Mach stem formation in PBXN-9

Description: PBXN-9 is an explosive that is less sensitive to certain insults, yet retains a high level of performance. As a result, PBXN-9 has been considered as an interim insensitive high explosive for conventional munitions systems. Certain of these systems incorporate wave control methodologies that require some form of reactive flow representation to achieve accurate predictions of the wave propagation. The authors have continued the use of Detonation Shock Dynamics (DSD) as a means to approximately account for reactive flow effects, yet retain the efficiency necessary for the munitions design process. To use DSD, they have taken the approach to calibrate explosives by measuring the detonation velocity as a function of local wave curvature. The DSD calibration, including the appropriate boundary conditions, can then be used to predict wave propagation in complex situations such as around obstacles, following wave-wave collisions, and so on. This paper describes the DSD calibration for PBXN-9, along with the methodologies used to obtain it, for both convergent and divergent flow (positive and negative wave curvatures). During the course of the calibration for convergent flow, Mach stem formation is observed in wave reflection experiments. The characteristics of the Mach stem formation and the subsequent growth are analyzed, presented and compared to similar measurements on other explosives. Illustrative examples of the use of DSD to predict wave propagation are provided.
Date: September 1, 1997
Creator: Hull, L.M.
Partner: UNT Libraries Government Documents Department

Transonic-Wind-Tunnel Tests of the Aerodynamic Characteristics of a 0.15-Scale Model of the North American Aviation 255-Inch Fin-Stabilized External Store, Coord No. AF-AM-4

Description: An investigation has been made in the Langley 8-foot transonic tunnels on the aerodynamic characteristics of a 0.15-scale model of the North American Aviation 255-inch fin-stabilized external store over a maximum Mach number range of 0.60 to 1.2 and on the effects of mounting lugs, of fin orientation, of fin aspect ratio, and of fixed-transition. The Reynolds number (based on a body length of 37.50 inches) varied from 9.8 x 10(exp 6) to 13.1 x 10(exp 6). The results indicate that the static margin of the finned store at low lift coefficients was only 9 percent of body length at subsonic Mach numbers and was reduced to zero at a Mach number of 1.0, Increasing the fin aspect ratio from 1.82 to 2.41 increased the subsonic static margin to 18 percent and provided a minimum margin of 9 percent near a Mach number of l.O. Store mounting lugs or fin orientation had only small effects on the aerodynamic characteristics of the basic store.
Date: February 9, 1958
Creator: Fischetti, Thomas L.
Partner: UNT Libraries Government Documents Department

Effects of Fuselage Modifications on the Drag Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds

Description: From Summary: "An investigation has been conducted in the Langley 8-foot transonic tunnel to determine the effects of several fuselage modifications on the transonic drag-rise characteristics of a 1/20-scale model of the Convair F-102 airplane. Tests covered an angle-of-attack range from 0 degrees to about 10 degrees and a Mach number range from 0.60 to 1.14."
Date: November 2, 1954
Creator: Kelly, Thomas C. & Osborne, Robert S.
Partner: UNT Libraries Government Documents Department

Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79

Description: From Summary: "Incipient spin characteristics have been investigated on a 1/35-scale dynamic model of the Convair F-102A airplane. The model was launched by a catapult apparatus into free flight with various control settings, and the motions obtained were photographed. The model was ballasted for the combat loading. All tests were made with the speed brakes and landing gear retracted, and engine effects were not simulated."
Date: February 11, 1958
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Free-Flight-Tunnel Investigation of the Dynamic Stability and Control Characteristics of a Chance Vought F7U-3 Airplane in Towed Flight

Description: "As part of a program to determine the feasibility of using a fighter airplane as a parasite in combination with a Consolidated Vultee RB-36 for long-range reconnaissance missions (project FICON), an experimental investigation has been made in the Langley free-flight tunnel to determine the dynamic stability and control characteristics of a 1/17.5-scale model of a Chance Vought F7U-3 airplane in several tow configurations. The investigation consisted of flight tests in which the model was towed from a strut in the tunnel by a towline and by a direct coupling which provided complete angular freedom. The tests with the direct coupling also included a study of the effect of spring restraint in roll in order to simulate approximately the proposed full-scale arrangement in which the only freedom is that permitted by the flexibility of the launching and retrieving trapeze carried by the-bomber" (p. 1).
Date: April 8, 1952
Creator: Grana, David C. & Shanks, Robert E.
Partner: UNT Libraries Government Documents Department

Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data

Description: "A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could tow a parasite fighter. In general, the theoretical results agree with the experimental results" (p. 1).
Date: June 24, 1958
Creator: Shanks, Robert E.
Partner: UNT Libraries Government Documents Department

Free-flight tests of 1/10-scale Republic F-105 airplane wings in the subsonic to low supersonic speed range to investigate the possibility of flutter : COORD. No. AF-224

Description: Report presenting an investigation of three pairs of 1/10-scale Republic F-105 airplane wings at subsonic to low supersonic speeds in free flight by utilizing rocket-propelled models to investigate the possibility of flutter. The wing plan form was swept back 45 degrees at the quarter-chord line and had an aspect ratio and taper ratio based on the exposed panels of 2.92 and 0.5, respectively. Testing did not show the existence of flutter for the full-scale wings in clean condition up to Mach number 1.47.
Date: February 20, 1956
Creator: O'Kelly, Burke R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90

Description: "This report presents the results of a wind-tunnel investigation of a 1/15-scale model of the Republic MX-1554 airplane at Mach numbers of 1.45 and 1.90 and at a Reynolds number of 3.0 million based on the mean aerodynamic chord of the wing. Tests were conducted to determine the static longitudinal and lateral stability of the model and the control effectiveness of the all-movable tail, elevators, rudder, aileron, and spoiler. All the results of this investigation are presented in graphic form and, in addition, the basic data have been cross-plotted to show the angle of attack, control deflection, and drag coefficient for the model balanced by the movable tail or the elevators" (p. 1).
Date: March 17, 1953
Creator: Smith, Willard G.
Partner: UNT Libraries Government Documents Department

Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane

Description: "An investigation was made of a 1/25-scale dynamically similar model of a 255,000-pound transport airplane in order to study its behavior when ditched. The model was free-launched from the Langley tank no. 2 monorail carriage into calm water. Various landing attitudes, flap settings, speeds, and configurations were investigated" (p. 1).
Date: July 13, 1955
Creator: Windham, John O.
Partner: UNT Libraries Government Documents Department

Rocket-Model Investigation of the Longitudinal Stability, Drag, and Duct Performance Characteristics of the North American MX-770 (X-10) Missile at Mach Numbers from 0.80 to 1.70

Description: "A free-flight 0.12-scale rocket-boosted model of the North American MX-770 (X-10) missile has been tested in flight by the Pilotless Aircraft Research Division of the Langley Aeronautical Laboratory. Drag, longitudinal stability, and duct performance data were obtained at Mach numbers from 0.8 to 1.7 covering a Reynolds number range of about 9 x 10(exp 6) to 24 x 10(exp 6) based on wing mean aerodynamic chord. The lift-curve slope, static stability, and damping-in-pitch derivatives showed similar variations with Mach number, the parameters increasing from subsonic values in the transonic region and decreasing in the supersonic region" (p. 1).
Date: April 16, 1953
Creator: Bond, Aleck C. & Swanson, Andrew G.
Partner: UNT Libraries Government Documents Department

Longitudinal and Lateral Stability, Control Characteristics, and Vertical-Tail-Load Measurements for 0.03-Scale Model of the Avro CF-105 Airplane at Mach Number 1.41

Description: "An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the aerodynamic characteristics of an 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, the aileron, and the rudder, as well as the vertical-tail-load characteristics. The results indicated a minimum drag coefficient of about 0.0270, and a maximum trimmed lift-drag ratio of about 4.25 which occurs at a lift coefficient of 0.16" (p. 1).
Date: August 20, 1956
Creator: Spearman, M. Leroy; Robinson, Ross B. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department

Drag and longitudinal trim characteristics of a low-tail version of the North American YF-100A airplane as determined from the flight test at low lift of a 0.11-scale rocket-powered model at Mach numbers between 0.75 and 1.78

Description: Report presenting drag and longitudinal trim characteristics at low lift of a low-tail version of the North American YF-100A airplane as obtained from the flight test of a 0.11-scale rocket model at a range of Mach numbers. Longitudinal stability data and some qualitative damping-in-pitch data are also provided.
Date: March 29, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

A summary of the drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.75 to 1.77 as determined by flight tests of 0.11-scale rocket models

Description: Report presenting longitudinal trim and drag at low lift of the North American YF-100A airplane at a range of Mach numbers as obtained with rocket-propelled models for an airplane, with the horizontal tail removed, and with wing removed conditions. Results regarding drag, longitudinal trim, longitudinal stability, and flutter and buffet are provided.
Date: January 29, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department

Flight Determination of the Longitudinal Stability and Control Characteristics of a 0.125-Scale Rocket-Boosted Model of the Mcdonnell F-101 Airplane at Mach Numbers from 0.82 to 1.84

Description: From Summary: "A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.125-scale model of the McDonnell F-101A airplane for the Mach number range between 0.82 and 1.84. The variation of lift-curve slope with Mach number was gradual with a maximum value of 0.107 occurring at a Mach number of 0.95. The minimum drag coefficient (including base and internal drag) has a value of 0.020 at a Mach number of 0.87. The drag rise begins at a Mach number of 0.90, and at Mach number of 1.10 the minimum drag is 0.070. Above this Mach number there is a gradual increase in minimum drag coefficient to a value of 0.074 when the Mach number is 1.83."
Date: July 5, 1955
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department

Effect of several jet-engine air-inlet configurations on the low-speed static longitudinal stability characteristics and quantity flow of a 1/6-scale model of the MX-1764 airplane

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a model of the MX-1764 airplane. The inlet configurations generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.
Date: January 12, 1954
Creator: Croom, Delwin R.
Partner: UNT Libraries Government Documents Department