11 Matching Results

Search Results

Advanced search parameters have been applied.

Wind-Tunnel Investigation of the Effect of Power and Flaps on the Static Longitudinal Stability and Control Characteristics of a Single-Engine High-Wing Airplane Model.

Description: Note presenting an investigation conducted to determine the effect of power and full-span slotted flaps on the longitudinal stability and control characteristics of a single-engine high-wing airplane. The model was tested at three power conditions: propeller off, propeller windmilling, and power on, and with the flap neutral, single slotted flap, and double slotted flap. The results indicated that deflection of the double slotted flap produced almost twice as much lift increment as did the deflection of the single slotted flap.
Date: July 1947
Creator: Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Effect of Power and Flaps on the Static Lateral Stability and Control Characteristics of a Single-Engine High-Wing Airplane Model

Description: Note presenting an investigation conducted to determine the effect of power and of full-span slotted flaps on the static lateral stability and control characteristics of a single-engine high-wing airplane with tail on and tail off. The model combinations investigated included three power conditions, including with the propeller off, propeller windmilling, and power on, and tested with the flap neutral, single slotted flap, and double slotted flap.
Date: July 1947
Creator: Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Downwash and Wake Behind Untapered Wings of Various Aspect Ratios and Angles of Sweep

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the downwash angles and the dynamic-pressure ratios behind wings of various sweep angles and aspect ratios, and the aerodynamic force characteristics of the wings. The wake center line behind the sweptforward wings was found to be located higher than the wake center line behind sweptback wings. Results regarding force data, surveys, and pictorial representation are provided.
Date: October 1948
Creator: Hoggard, H. Page, Jr. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Investigation of Extensible Wing-Tip Ailerons on an Untapered Semispan Wing at 0 Degree and 45 Degrees Sweepback

Description: Report presenting a low-speed wind-tunnel investigation to determine the lateral control characteristics of extensible wing-tip ailerons on an untapered semispan wing with two configurations; one was unswept and had an aspect ratio of 3.13 and the other was swept back 45 degrees and had an aspect ratio of 1.59. Results regarding the plain-wing aerodynamic characteristics and lateral control characteristics are provided.
Date: September 20, 1949
Creator: Hagerman, John R. & O'Hare, William M.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of an Unswept Untapered Semispan Wing of Aspect Ratio 3.13 Equipped With Various 25-Percent-Chord Plain Flaps

Description: Report presenting force and moment data obtained at low speeds to determine the aerodynamic characteristics of an unswept untapered semispan wing of NACA 64A010 section and aspect ratio 3.13 equipped with 25-percent-chord unsealed plain flaps with various spans and spanwise locations. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the flaps deflected up to 60 degrees.
Date: April 1950
Creator: Johnson, Harold S. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Lateral Control Characteristics of an Unswept Untapered Semi-Span Wing of Aspect Ratio 3.13 Equipped With Various 25-Percent-Chord Plain Ailerons

Description: Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with 25-percent-chord plain unsealed ailerons with various spans and spanwise locations. Results regarding wing aerodynamic characteristics and aileron control characteristics are provided.
Date: October 1950
Creator: Johnson, Harold S. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method

Description: From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Test of 0.14-Scale Models of the Control Surfaces of Army Project MX-511 in Attitudes Simulating Spins

Description: Report discussing the aerodynamic characteristics of the wing and isolated tail of the Bell XP-83 airplane in attitudes simulating spin conditions. Information about the the aileron hinge moment, angle of attack, and elevator hinge-moment is provided.
Date: April 1945
Creator: Hoggard, H. Page, Jr. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of a 45 Degree Sweptback Untapered Semispan Wing of Aspect Ratio 1.59 Equipped With Various 25-Percent Chord Plain Flaps

Description: Report presenting a wind-tunnel investigation at low speed to determine the aerodynamic characteristics of a 45 degree sweptback untapered semispan wing of NACA 64A010 airfoil section normal to the leading edge and aspect ratio of 1.59 equipped with 25-percent-chord plain unsealed flaps with various spans and spanwise conditions. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the various flaps deflected up to 60 degrees.
Date: August 1950
Creator: Johnson, Harold S. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees

Description: Report presenting a wind-tunnel investigation through a speed range from Mach number 0.30 to 0.90 to determine the lateral-control characteristics of a 20-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoilers on a semispan-wing model with aspect ratio of 3.06 with 51.3 degrees sweepback of the wing leading edge. The aileron rolling effectiveness decreased as the Mach number increased, while the spoiler rolling-moment effectiveness decreased with Mach number.
Date: June 7, 1949
Creator: Schneiter, Leslie E. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department

Effect of Aspect Ratio on the Low-Speed Lateral Control Characteristics of Untapered Low-Aspect-Ratio Wings Equipped With Flap and With Retractable Ailerons

Description: A low-speed wind-tunnel investigation was made to determine the lateral control characteristics of a series of untapered low-aspect-ratio wings. Sealed flap ailerons of various spans and spanwise locations were investigated on unswept wings of aspect ratios 1.13, 1.13, 4.13, and 6.13; and various projections of 0.60-semispan retractable ailerons were investigated on the unsweptback wings of aspect ratios 1.13, 2.13, and 4.13 and on a 45 degree sweptback wing. The retractable ailerons investigated on the unswept wings spanned the outboard stations of each wing; whereas the plain and stepped retractable ailerons investigated on the sweptback wing were located at various spanwise stations. Design charts based on experimental results are presented for estimating the flap aileron effectiveness for low-aspect-ratio, untapered, unswept.
Date: February 8, 1952
Creator: Fischel, Jack; Naeseth, Rodger L.; Hagerman, John R. & O'Hare, William M.
Partner: UNT Libraries Government Documents Department