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An Experimental Investigation at Subsonic Speeds of a Scoop-Type Air-Induction System for a Supersonic Airplane

Description: Report presenting an investigation at subsonic speeds of a scoop-type air-induction system designed for use at subsonic and supersonic speeds. Measurements of the ram-recovery ratio and static pressures in a scoop-type intake on the upper surface of the fuselage were taken for a large range of mass-flow ratios, angles of attack, and angles of sideslip.
Date: July 19, 1951
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation at Large Scale of an NACA Submerged Intake and Deflector Installation on the Rearward Portion of a Fuselage

Description: Report presenting an experimental investigation at low speed to determine the pressure-recovery and drag characteristics of an NACA submerged intake and deflector installation on the rearward portion of the fuselage of a model.
Date: August 30, 1950
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Use of Leading-Edge and Trailing-Edge Area-Suction Flaps on a 13-Percent-Thick Straight Wing and Fuselage Model

Description: Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.
Date: January 24, 1958
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

The Effect of Entrance Mach Number and Lip Shape on the Subsonic Characteristics of a Scoop-Type-Air-Induction System for a Supersonic Airplane

Description: Report presenting an investigation at subsonic speeds to determine the effects of lip shape and entrance Mach number on the characteristics of a scoop-type air-induction system designed for an airplane flying at supersonic speeds. Results regarding the ram-recovery ratio, static-pressure distribution, and drag are provided.
Date: January 9, 1952
Creator: Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

Analysis of factors influencing the stability characteristics of symmetrical twin-intake Air-induction systems

Description: From Introduction: "Experimental investigations of air-induction systems in which the air flows of two intakes join in a common duct have inducted that many of these systems are subject to air-flow instability at low inlet-velocity ratios. Therefore, an analysis has been made to determine a proper basis for an explanation and to provide a more quantitative explanation of the flow instability and the flow reversal. This report presents the results of this analysis."
Date: March 1950
Creator: Martin, Norman J. & Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

Exploratory Investigation of the Use of Area Suction to Eliminate Air-Flow Separation in Diffusers Having Large Expansion Angles

Description: Tests were made at a mean inlet Mach number of 0.2 with area suction applied to conical diffusers with expansion angles of 30 degrees and 50 degrees and exit to inlet area ratios of 2. Air-flow separation was eliminated with suction mass flows of 3 and 4 percent of the inlet mass flows for the 30 degrees and 50 degrees diffusers, respectively.
Date: October 1956
Creator: Holzhauser, Curt A. & Hall, Leo P.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation at Large Scale of Single and Twin Naca Submerged Side Intakes at Several Angles of Sideslip

Description: Report presenting the results of an experimental investigation to determine the pressure-recovery and mass-flow characteristics of single and twin NACA submerged intakes on the sides of a fuselage at various angles of sideslip. Tests were conducted with single and twin submerged intakes on a model of a fighter-type airplane.
Date: August 1, 1949
Creator: Martin, Norman J. & Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake

Description: "An investigation of an NACA submerged air intake was conducted on a full-scale model of a fighter-type airplane. This study was made to determine the large-scale aerodynamic characteristics of a submerged air intake proposed as the result of small-scale tests and to compare the pressure-recovery characteristics of the large- and small-scale installations. Additional tests were made to determine the effect on pressure recovery of a systematic variation of ramp divergence" (p. 1).
Date: October 19, 1948
Creator: Martin, Norman J. & Holzhauser, Curt A.
Partner: UNT Libraries Government Documents Department

The Use of a Leading-Edge Area-Suction Flap to Delay Separation of Air Flow From the Leading Edge of a 35 Degrees Sweptback Wing

Description: "An investigation was conducted on a 35 degree swept-wing model to determine the aerodynamic characteristics and suction requirements of a model having a leading-edge area-suction flap deflected 40 degrees" (p. 1). The procedures, corrections needed, force characteristics, suction requirements, and pressure distributions are described.
Date: December 10, 1953
Creator: Holzhauser, Curt A. & Martin, Robert K.
Partner: UNT Libraries Government Documents Department

The Use of Area Suction for the Purpose of Improving Trailing-Edge Flap Effectiveness on a 35 Degree Sweptback Wing

Description: "An investigation was conducted to determine the effectiveness of suction applied through a porous area at the leading edge of the flap, on a 35 degree sweptback wing. Several chordwise extents and positions of area suction were tested for the suction flap deflected 55 degrees and 70 degrees. The results indicated that large increases in flap lift increment can be made by applying suction with very small flow quantities to an area near the leading edge of a flap" (p. 1).
Date: July 2, 1953
Creator: Cook, Woodrow L.; Holzhauser, Curt A. & Kelly, Mark W.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel and Flight Investigations of the Use of Leading-Edge Area Suction for the Purpose of Increasing the Maximum Lift Coefficient of a 35 Degree Swept-Wing Airplane

Description: "An investigation was undertaken to determine the increase in maximum lift coefficient that could be obtained by applying area suction near the leading edge of a wing. This investigation was performed first with a 35 degree swept-wing model in the wind tunnel, and then with an operational 35 degree swept-wing airplane which was modified in accord with the wind-tunnel results. The wind-tunnel and flight tests indicated that the maximum lift coefficient was increased more than 50 percent by the use of area suction. Good agreement was obtained in the comparison of the wind-tunnel results with those measured in flight" (p. 1).
Date: 1956
Creator: Holzhauser, Curt A. & Bray, Richard S.
Partner: UNT Libraries Government Documents Department