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Wind-Tunnel Investigation at High Subsonic Speeds of the Effects on Static Stability Characteristics of Various Modifications to a Swept-Wing Fighter-Type Airplane Model

Description: Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.
Date: April 30, 1957
Creator: Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations

Description: Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a chord-plane tail, a T tail, and a biplane tail. A discussion regarding the pitching-moment characteristics, lift and drag characteristics, and stabilizer characteristics is provided.
Date: January 10, 1957
Creator: Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some effects of ailerons on the variation of aerodynamic characteristics with sideslip at low speed

Description: Report presenting an investigation at low speed of a complete-model configuration with a wing of aspect ratio 4, taper ratio 0.3, and 45 degrees sweepback and had inboard and outboard ailerons. The model was tested over a range of sideslip and angles of attack to determine variations of the aerodynamic coefficients, especially pitching-moment coefficient, with sideslip angle. The results indicate that with ailerons deflected, an appreciable variation of pitching moment with sideslip angle can e… more
Date: March 12, 1956
Creator: Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static lateral characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations

Description: Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a wing-chord-plane tail, a T tail, and a biplane tail. A discussion regarding the lateral derivatives and sideslip characteristics is provided.
Date: October 28, 1957
Creator: Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral stability and control characteristics of an airplane model having 42.8 degree sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces

Description: Report presenting testing in the 300 mph 7- by 10-foot tunnel of an airplane model with a 42.8 degree sweptback wing with an aspect ratio 4.00, taper ratio 0.50, a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine the low-speed lateral stability and control characteristics. Some changes made to improve the aerodynamic characteristics included lowering the wing, incorporating a smaller-fineness-ratio fuselage, and increasing the vertical tail size. Res… more
Date: October 17, 1947
Creator: Goodson, Kenneth W. & Comisarow, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section: Transonic-Bump Method

Description: Report discussing a particular wing-body combination that is part of a larger investigation to determine the lift, drag, pitching moment, and root bending moments for various configurations. Information about the aerodynamic characteristics at the tail plane is also provided.
Date: February 24, 1949
Creator: Weil, Joseph & Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of symmetric and asymmetric thrust reversal on the aerodynamic characteristics of a model of a twin-engine airplane

Description: Report presenting an investigation using a twin-engine airplane model in the 300 mph 7- by 10-foot tunnel to determine the magnitude of the changes in aerodynamic forces and moments resulting from propeller pitch reversal. The effects of both positive and negative thrust coefficients were investigated at Reynolds number 550,000. Results regarding the analysis of effects of symmetric and asymmetric thrust on the aerodynamic characteristics and typical performance and control estimates are provid… more
Date: September 1953
Creator: Goodson, Kenneth W. & Draper, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at High Subsonic Speeds of the Stability Characteristics of a Complete Model Having Sweptback-, M-, W-, and Cranked-Wing Plan Forms and Several Horizontal-Tail Locations

Description: Report presenting an investigation at high subsonic speeds of a complete model with one of four types of wings: a basic sweptback wing, an M-shaped wing, a W-shaped wing, and a cranked wing. All of the wings had the same aspect and taper ratio and were tested at the same range of Mach numbers. Results regarding longitudinal characteristics and lateral characteristics of the different wings are provided.
Date: May 14, 1954
Creator: Goodson, Kenneth W. & Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwing XBTK-1 Airplane: Lateral Stability and Control

Description: Report discussing testing on a powered model of the Fleetwings XBTK-1 airplane in order to investigate the lateral stability characteristics. Information about the effective dihedral, directional stability, potential for rudder lock, results of rudder modification, rudder effectiveness, and aileron effectiveness is provided.
Date: July 1945
Creator: Goodson, Kenneth W. & Silvers, H. Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and control characteristics of a complete airplane model having a wing with quarter-chord line swept back 40 degrees, aspect ratio 2.50, and taper ratio 0.42

Description: From Summary: "An investigation has been made of a complete airplane model having a wing with the quarter-chord line swept back 40 degrees, aspect ratio 2.50, and taper ratio 0.42 to determine its low-speed stability and control characteristics. The longitudinal stability investigation included stabilizer and tail-off tests with different wing dihedral angles (Gamma = 0 degrees and Gamma = -10 degrees) over an angle-of-attack range for the cruising and landing configurations and tests. with a h… more
Date: December 1951
Creator: Schulderfrei, Marvin; Comisarow, Paul & Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of an Airplane Model Having a 42.8 Degree Sweptback Circular-Arc Wing With Aspect Ratio 4.00, Taper Ratio 0.50, and Sweptback Tail Surfaces

Description: Report presenting testing of an airplane model with a 42.8 degree sweptback wing with an aspect ratio of 4.00, taper ratio of 0.50, and a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine its low-speed longitudinal stability and control characteristics. Other variables investigated include the vertical-wing location, fuselage size, horizontal-tail location, and stall-control vanes on the wing.
Date: October 17, 1947
Creator: Weil, Joseph; Comisarow, Paul & Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Semispan Wind-Tunnel Model of a Tailless Airplane and a Comparison With Complete-Model Wind-Tunnel Tests and Semispan-Model Wing-Flow Tests

Description: Report presenting an investigation of a model of a tailless airplane in a high speed tunnel at a range of Mach numbers. Results are compared to those obtained from a sting-mounted model tested in the same tunnel and a semispan model tested with the wing-flow method. Information regarding basic aerodynamic characteristics, spoiler controls, lift characteristics, drag characteristics, pitching moment at zero lift, and stability and control is provided.
Date: October 10, 1949
Creator: Goodson, Kenneth W. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Description: Report discussing a wing-alone and wing-fuselage configuration with particular characteristics as part of a series of tests of wings using the transonic-bump test technique. Lift, drag, pitching moment, and root bending moment were obtained for the configurations. The effective downwash angles and dynamic-pressure characteristics in the tail region are also described.
Date: November 1, 1949
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date: October 21, 1949
Creator: Goodson, Kenneth W. & Morrison, William D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of leading-edge chord-extensions on subsonic and transonic aerodynamic characteristics of three models having 45 degrees sweptback wings of aspect ratio 4

Description: Report presenting an investigation to determine the effect of leading-edge chord-extensions on high-lift pitching moment and performance characteristics at subsonic and transonic speeds. Three models with the same wings were used. Results regarding low-speed development and high-speed characteristics are provided.
Date: January 21, 1953
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed static longitudinal and lateral stability characteristics of a model with leading-edge chord-extensions incorporated on a 40 degree sweptback circular-arc wing of aspect ratio 4 and taper ratio 0.50

Description: Report presenting an investigation to determine the aerodynamic effects at low speed of several wing leading-edge chord-extensions incorporated on a complete model with a 40 degree sweptback circular-arc wing of aspect ratio 4 and taper ratio 0.50. Testing indicated that the effectiveness of the chord-extension in increasing the stability is mainly dependent on the spanwise inboard-end location of the device. Results regarding the static longitudinal characteristics and effect of chord-extensio… more
Date: November 3, 1952
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Semispan Wind-Tunnel Model of the XF7U-1 Airplane and a Comparison with Complete-Model Wind-Tunnel Tests and Semispan-Model Wing-Flow Tests

Description: An investigation was conducted on an 0.08-scale semispan model of the Chance Vought XF7U-1 airplane in the Langley high-speed 7- by 10-foot tunnel in the Mach number range from 0.40 to 0.97. The results are compared with those obtained with an 0.08-scale sting-mounted complete model tested in the same tunnel and with an 0.026-scale semispan model tested by the wing-flow method. The lift-curve slopes obtained for the 0.08-scale semispan model and the 0.026-scale wing-flow model were in good agre… more
Date: January 18, 1949
Creator: Goodson, Kenneth W. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees

Description: Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date: October 10, 1950
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part I - Basic Longitudinal Stability Characteristics, TED No. NACA DE308, Part 1, Basic Longitudinal Stability Characteristics, TED No. NACA DE308

Description: The stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane have been investigated over a Mach number range from 0.40 to 0.91. Results of the basic longitudinal tests of the complete model with undeflected control surfaces are given in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Kuhn, Richard E. & Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part 4 - Aileron Characteristics TED No. NACA DE308, Part 4, Aileron Characteristics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The aileron characteristics of the complete model are presented in the present report with a very limited analysis of the results.
Date: August 22, 1947
Creator: Goodson, Kenneth W. & Myers, Boyd C., II
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part II - Basic Lateral Stability Characteristics TED No. NACA DE308, Part 2, Basic Lateral Stability Charactistics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The basic lateral stability characteristics of the complete model with undeflected control surfaces are presented in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Kuhn, Richard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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