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Longitudinal aerodynamic characteristics of various configurations of a revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01

Description: Report presenting an investigation of a model of the Republic F-105 airplane to determine the static longitudinal aerodynamic characteristics of a revised configuration. The revisions included a lengthened fuselage, a relocated canopy, a contoured fuselage afterbody, a ventral fin, and an enlarged vertical tail. Results regarding the effect of stores, effect of dive-brake flaps, effect of forebody modifications, gun blisters, and duct air bleed, and a comparison of the modified model with the original are provided.
Date: May 4, 1956
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and wake-flow characteristics of a twisted and cambered wing-fuselage combination of 45 degree sweepback and aspect ratio 8 with a horizontal tail and stall-control devices at a Reynolds number of 4.0 x 10(exp 6).

Description: Report presenting an investigation to determine the effects of a horizontal tail on the longitudinal stability characteristics of a swept-back, twisted, and cambered wing in combination with a fuselage and various combinations of high-lift and stall-control devices. The ideal placement of the horizontal tail appeared to be at 6 percent wing semispan below the wing-root-chord plane.
Date: June 8, 1953
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Investigation of the longitudinal aerodynamic characteristics of a trapezoidal-wing airplane model with various vertical positions of wing and horizontal tail at Mach numbers of 1.41 and 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel to determine the effects of various vertical positions of a wing and horizontal tail on the static longitudinal aerodynamic characteristics of a trapezoidal wing model. Results regarding effect of wing vertical position and tail-on characteristics are provided.
Date: March 6, 1958
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Effects of nose and afterbody modifications on aerodynamic characteristics of a body with and without a vertical tail at a Mach number of 2.01

Description: Report presenting the effects at Mach number 2.01 of various changes in nose and afterbody shape on the static aerodynamic characteristics of a body of revolution with a fineness ratio of 11 with an ogive nose, a cylindrical center section, and a boattail or cylindrical afterbody. Some body conditions were tested in combination with a vertical tail. Results regarding the effects of nose and afterbody modifications and vertical tail-on configurations are provided.
Date: April 15, 1958
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Effects of twist and camber, fences, and horizontal-tail height on the low-speed longitudinal stability characteristics of a wing-fuselage combination with a 45 degree sweptback wing of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)

Description: Report presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided.
Date: December 9, 1952
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Description: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Date: December 19, 1947
Creator: Conner, D. William & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Longitudinal-stability investigation of high-lift and stall-control devices on a 52 degree sweptback wing with and without fuselage and horizontal tail at a Reynolds number of 6.8 x 10(exp 6).

Description: Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ratio 2.88, taper ratio 0.625, and NACA 64 (sub 1)-112 airfoil sections normal to the 0.282-chord line, in combination with split flaps, leading-edge flaps, and upper-surface fences. Low-wing and midwing-fuselage aerodynamic characteristics are presented with and without a horizontal tail at various vertical locations. Tests were conducted at a Reynolds number of 6.8 x 10(exp 6).
Date: December 20, 1948
Creator: Foster, Gerald V. & Fitzpatrick, James E.
Partner: UNT Libraries Government Documents Department

Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions

Description: Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of a fuselage and a horizontal tail located at various vertical positions on the low-speed longitudinal characteristics of a circular-arc 52 degree sweptback wing. Results regarding the effect of fuselage on longitudinal characteristics of the wing, effect of tail position on stability and tail effectiveness, and air-flow characteristics are provided.
Date: June 19, 1951
Creator: Foster, Gerald V. & Griner, Roland F.
Partner: UNT Libraries Government Documents Department

Static lateral and directional stability and control characteristics of a revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01

Description: Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
Date: October 16, 1956
Creator: Robinson, Ross B. & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

A study of several factors affecting the stability contributed by a horizontal tail at various vertical positions on a sweptback-wing airplane model

Description: Report presenting a study in the 19-foot pressure tunnel to determine the effects of fuselage afterbody shape, split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing swept back 42 degrees.
Date: November 1956
Creator: Foster, Gerald V. & Griner, Roland F.
Partner: UNT Libraries Government Documents Department

Effects of leading-edge radius on the longitudinal stability of two 45 degree sweptback wings as influenced by Reynolds numbers up to 8.20 x 10(exp 6) and Mach numbers up to 0.303

Description: Report presenting an investigation to show the effects of systematic changes of leading-edge radius, aspect ratio, Reynolds number, and Mach number on the static longitudinal aerodynamic characteristics of sweptback wings in the 19-foot pressure tunnel. Results regarding the effects of leading-edge radius and aspect ratio and effect of Reynolds number and Mach number are provided.
Date: July 28, 1955
Creator: Foster, Gerald V. & Schneider, William C.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps

Description: Report presenting testing to determine the aerodynamic characteristics of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps. The wing had a straight trialing edge and a constant-chord center section. Results regarding lift and pitching-moment characteristics and stalling characteristics are provided.
Date: January 1946
Creator: Heely, Robert H. & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Effects of external stores on the static longitudinal aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations on the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Results regarding accuracy and remarks on effects of stores are provided.
Date: August 23, 1956
Creator: Foster, Gerald V. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department

Static lateral and directional stability and control characteristics of revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01: COORD No. AF-163

Description: Report presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.41 and 2.01 to determine the static lateral and directional stability and control characteristics of a scale model of the Republic F-105 airplane. Results regarding the static lateral and directional stability and lateral and directional control are provided.
Date: November 19, 1956
Creator: Robinson, Ross B. & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Static longitudinal aerodynamic characteristics of a 52 degree sweptback wing of aspect ratio 2.88 at Reynolds numbers from 2,000,000 to 11,000,000

Description: Report presenting the effects of changes in Reynolds number on the longitudinal aerodynamic characteristics of a 52 degree sweptback wing with an aspect ratio of 2.88 and NACA 64(sub 1)-112 airfoil sections. The model was tested with the leading edge both smooth and rough. Results regarding force and pitching-moment results, flow observations, and discussion of force and moment characteristics are provided.
Date: November 16, 1948
Creator: Fitzpatrick, James E. & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.41, 1.61, and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at three Mach numbers. The results indicate that the static margin, which was fairly constant through the lift range, decrease from 32 to 27 percent mean aerodynamic chord with increase in Mach number from 1.41 to 2.01.
Date: July 11, 1956
Creator: Driver, Cornelius & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Longitudinal Stability and Stalling Characteristics of a 1/8.33-Scale Model of the Republic XF-12 Airplane

Description: The XF-12 airplane is a high performance, photo-reconnaissance aircraft designed by the Republic Aviation Corporation for Army Air Forces. A series of tests of a 1/8.33-scale powered model was conducted in the Langley 9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. This report presents the results of tests to determine the static longitudinal stability and stalling characteristics of the model. From this investigation it was indicated that the airplane will possess a positive static margin for all probable flight conditions. The stalling characteristics are considered satisfactory in that the stall initiates near the root section and progresses toward the tips. Early root section stalling occurs, with the flaps retracted and may cause undesirable tail buffeting and erratic elevator control in the normal flight range. From considerations of sinking speed landing flap deflections of 40 degrees may be preferable to 55 degrees of 65 degrees.
Date: 1947
Creator: Pepper, Edward & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Lateral Stability Characteristics of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane is a high-performance photo-reconnaissance aircraft designed for the Army Air Forces by the Republic Aviation Corporation. An investigation of a 1/8.33 - scale powered model was made in the Langley l9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. The model was tested with and without the original vertical tail. and with two revised tails. For the revised tail no. 1, the span of the original vertical .tail was increased about 15 percent and the portion of the vertical tail between the stabilizer and fuselage behind the rudder hinge line was allowed to deflect simultaneously with the main rudder" (p. 1).
Date: February 27, 1947
Creator: Pepper, Edward & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack" (p. 1).
Date: April 8, 1947
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department