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  • 1
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    User's manual for the model interface and plugboard cabinets in the 14- by 22-foot subsonic tunnel (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The primary method of connection between the wind tunnel model instrumentation and the data acquisition system in the 14- by 22-Foot Subsonic Tunnel is through the Model Interface (MIF) and Plugboard cabinets. The MIF and Plugboard cabinets allow versatility in the connection of the instrumentation to the different data systems in the facility. The User's Manual describes the components inside the MIF cabinet, the input and output of the MIF, and the MIF patchboard, and the Plugboard cabinets. There are examples of standard connections for most of the instrumentation used in the facility.
    Keywords: AERODYNAMICS
    Type: NASA-TM-109062 , NAS 1.15:109062
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Langley 14- by 22-Foot Subsonic Tunnel: Description, Flow Characteristics, and Guide for Users (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Langley 14- by 22-foot Subsonic Tunnel is a closed circuit, single-return atmospheric wind tunnel with a test section that can be operated in a variety of configurations (closed, slotted, partially open, and open). The closed test section configuration is 14.5 ft high by 21.75 ft wide and 50 ft long with a maximum speed of about 338 ft/sec. The open test section configuration has a maximum speed of about 270 ft/sec, and is formed by raising the ceiling and walls, to form a floor-only configuration. The tunnel may be configured with a moving-belt ground plane and a floor boundary-layer removal system at the entrance to the test section for ground effect testing. In addition, the tunnel had a two-component laser velocimeter, a frequency modulated (FM) tape system for dynamic data acquisition, flow visualization equipment, and acoustic testing capabilities. Users of the 14- by 22-foot Subsonic Tunnel are provided with information required for planning of experimental investigations including test hardware and model support systems.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3008 , L-16731 , NAS 1.60:3008
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Subsonic aerodynamic characteristic of semispan commercial transport model with wing-mounted advanced ducted propeller operating in reverse thrust (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A test was conducted in the Langley 14 by 22 Foot Subsonic Tunnel to determine the effect of the reverse-thrust flow field of a wing-mounted advanced ducted propeller on the aerodynamic characteristics of a semispan subsonic high-lift transport model. The advanced ducted propeller (ADP) model was mounted separately in position alongside the wing so that only the aerodynamic interference of the propeller and nacelle affected the aerodynamic performance of the transport model. Mach numbers ranged from 0.14 to 0.26; corresponding Reynolds numbers ranged from 2.2 to 3.9 x 10(exp 6). The reverse-thrust flow field of the ADP shielded a portion of the wing from the free-stream airflow and reduced both lift and drag. The reduction in lift and drag was a function of ADP rotational speed and free-stream velocity. Test results included ground effects data for the transport model and ADP configuration. The ground plane caused a beneficial increase in drag and an undesirable slight increase in lift. The ADP and transport model performance in ground effect was similar to performance trends observed for out of ground effect. The test results form a comprehensive data set that supports the application of the ADP engine and airplane concept on the next generation of advanced subsonic transports. Before this investigation, the engine application was predicted to have detrimental ground effect characteristics. Ground effect test measurements indicated no critical problems and were the first step in proving the viability of this engine and airplane configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3427 , L-1782 , NAS 1.60:3427
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Evaluation of Four Advanced Nozzle Concepts for Short Takeoff and Landing Performance (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Four advanced nozzle concepts were tested on a canard-wing fighter in the Langley 14- by 22-Foot Subsonic Tunnel. The four vectoring-nozzle concepts were as follows: (1) an axisymmetric nozzle (AXI); (2) an asymmetric, load balanced exhaust nozzle (ALBEN); (3) a low aspect ratio, single expansion ramp nozzle (LASERN); and (4) a high aspect ratio, single expansion ramp nozzle (HASERN). The investigation was conducted to determine the most suitable nozzle concept for short takeoff and landing (STOL) performance. The criterion for the best STOL performance was a takeoff ground roll of less than 1000 ft. At approach, the criteria were high lift and sufficient drag to maintain a glide slope of -3 to -6 deg with enough pitching-moment control from the canards. The test was performed at a dynamic pressure of 45 lb/sq ft and an angle-of-attack range of 0 to 20 deg. The nozzle pressure ratio was varied from 1.0 to 4.3 at both dry power and after burning nozzle configurations with nozzle vectoring to 60 deg. In addition, the model was tested in and out of ground effects. The ALBEN concept was the best of the four nozzle concepts tested for STOL performance.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3314 , L-16998 , NAS 1.60:3314
    Format: application/pdf
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  • 5
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    User's manual for the Langley Research Center 14- by 22- foot subsonic tunnel static data acquisition system (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Static Data Acquisition System (SDAS) components primarily responsible for acquiring data at the 14- by 22-Foot Subsonic Tunnel are the NEFF 620/600 Data Acquisition Unit (DAU) and the PSI 780B electronically scanned pressure (ESP) measurement system. A 9250 Modcomp computer is used to process the signal, to do all aerodynamic calculation, and to control the output of data. All of the tasks required to support a wind tunnel investigation are menu driven. The purpose of this report is to acquaint users of this system with the wide range of capabilities that exist with the available hardware and software and provide them with the proper procedures to follow when setting up or running individual tests.
    Keywords: AERODYNAMICS
    Type: NASA-TM-109027 , NAS 1.15:109027
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Dynamic Pressure Equations Used at the 14- by 22-Foot Subsonic Tunnel (2019)
    In:  CASI
    Details
    Publication Date: 2019-05-13
    Description: This document provides a description of equations used to calculate test section dynamic pressure in the 14- by 22-Foot Subsonic Tunnel. The equation used to calculate dynamic pressure is dependent on the test section configuration.
    Keywords: Research and Support Facilities (Air)
    Type: NF1676L-32662
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Langley 14- by 22-foot subsonic tunnel test engineer's data acquisition and reduction manual (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Langley 14- by 22-Foot Subsonic Tunnel is used to test a large variety of aircraft and nonaircraft models. To support these investigations, a data acquisition system has been developed that has both static and dynamic capabilities. The static data acquisition and reduction system is described; the hardware and software of this system are explained. The theory and equations used to reduce the data obtained in the wind tunnel are presented; the computer code is not included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4563 , L-17263 , NAS 1.15:4563
    Format: application/pdf
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  • 8
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    Thrust-reverser flow investigation on a twin-engine transport (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the NASA Langley 14 x 22 foot Subsonic Tunnel to study the effects of engine thrust reversing on an aft-mounted twin-engine transport and to develop effective testing techniques. Testing was done over a fixed and a moving-belt ground plane and over a pressure instrumented ground board. Free-stream dynamic pressure was set at values up to 12.2 psf, which corresponded to a maximum Reynolds number based on the mean aerodynamic chord of 765,000. The thrust reversers examined included cascade, target and four-door configurations. The investigation focused on the range of free-stream velocities and engine thrust-reverser flow rates that would be typical for landing ground-roll conditions. Flow visualization techniques were investigated, and the use of water or smoke injected into the reverser flow proved effective to determine the forward progression of the reversed flow and reingestion limits. When testing over a moving-belt ground plane, as opposed to a fixed ground plane, forward penetration of the reversed flow was reduced. The use of a pressure-instrumented ground board enabled reversed flow ground velocities to be obtained, and it provided a means by which to identify the reversed flow impingement point on the ground.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2856 , L-16426 , NAS 1.60:2856
    Format: application/pdf
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  • 9
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    Low-speed aerodynamic characteristics of a twin-engine general aviation configuration with aft-fuselage-mounted pusher propellers (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to determine the aerodynamic characteristics of an advanced turboprop aircraft model with aft-pylon-mounted pusher propellers. Tests were conducted through an angle-of-attack range of -8 to 28 degrees, and an angle-of-sideslip range of -20 to 20 degrees at free-stream conditions corresponding to Reynolds numbers of 0.55 to 2.14 x 10 to the 6th power based on mean aerodynamic chord. Test results show that for the unpowered configurations the maximum lift coefficients for the cruise, takeoff, and landing configurations are 1.45, 1.90, and 2.10, respectively. Nacelle installation results in a drag coefficient increase of 0.01. Increasing propeller thrust results in a significant increase in lift for angles of attack above stall and improves the longitudinal stability. The cruise configuration remains longitudinally stable to an angle of attack 5 degrees beyond the stall angle, the takeoff configuration is stable 4 degrees beyond stall angle, and the landing configuration is stable 3 degrees beyond stall angle. The predominant effect of symmetric thrust on the lateral-directional aerodynamic characteristics is in the post-stall region, where additional rudder control is available with power on.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2763 , L-16331 , NAS 1.60:2763
    Format: application/pdf
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  • 10
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    A review of technologies applicable to low-speed flight of high-performance aircraft investigated in the Langley 14- x 22-foot subsonic tunnel (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An extensive research program has been underway at the NASA Langley Research Center to define and develop the technologies required for low-speed flight of high-performance aircraft. This 10-year program has placed emphasis on both short takeoff and landing (STOL) and short takeoff and vertical landing (STOVL) operations rather than on regular up and away flight. A series of NASA in-house as well as joint projects have studied various technologies including high lift, vectored thrust, thrust-induced lift, reversed thrust, an alternate method of providing trim and control, and ground effects. These technologies have been investigated on a number of configurations ranging from industry designs for advanced fighter aircraft to generic wing-canard research models. Test conditions have ranged from hover (or static) through transition to wing-borne flight at angles of attack from -5 to 40 deg at representative thrust coefficients.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2796 , L-16364 , NAS 1.60:2796
    Format: application/pdf
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