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  • 1
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    Change Detection Experiments Using Low Cost UAVs (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: This paper presents the progress in the development of a low-cost change-detection system. This system is being developed to provide users with the ability to use a low-cost unmanned aerial vehicle (UAV) and image processing system that can detect changes in specific fixed ground locations using video provided by an autonomous UAV. The results of field experiments conducted with the US Army at Ft. A.P.Hill are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: Infotech@Aerospace; 26-29 Sept. 2005; Arlington, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Design, Development, and Testing of a Compound Wing V/TOL small UAS (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: This paper discusses the development and testing of an innovative small UAS (Unmanned Aircraft System). The design of the vehicle was driven by the need to both have long endurance yet still have the convenience of V/TOL (Vertical Take-Off and Landing) operation. The paper discusses some of the design considerations and configurations evaluated in searching for a configuration that met the demanding mission requirements. The paper also discusses some aspects of the compound wing and experimental testing conducted to discern the optimum parameters for the wing's design. The paper discusses the results of the preliminary flight testing and outlines further research to be conducted.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-19089 , SciTech 2015; Jan 05, 2015 - Jan 09, 2015; Kissimmee, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Transonic-Wind-Tunnel Tests of the Aerodynamic Characteristics of a 0.15-Scale Model of the North American Aviation 255-Inch Fin-Stabilized External Store, Coord No. AF-AM-4 (1958)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley 8-foot transonic tunnels on the aerodynamic characteristics of a 0.15-scale model of the North American Aviation 255-inch fin-stabilized external store over a maximum Mach number range of 0.60 to 1.2 and on the effects of mounting lugs, of fin orientation, of fin aspect ratio, and of fixed-transition. The Reynolds number (based on a body length of 37.50 inches) varied from 9.8 x 10(exp 6) to 13.1 x 10(exp 6). The results indicate that the static margin of the finned store at low lift coefficients was only 9 percent of body length at subsonic Mach numbers and was reduced to zero at a Mach number of 1.0, Increasing the fin aspect ratio from 1.82 to 2.41 increased the subsonic static margin to 18 percent and provided a minimum margin of 9 percent near a Mach number of l.O. Store mounting lugs or fin orientation had only small effects on the aerodynamic characteristics of the basic store.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL56A30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects cf control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended. The results indicated that the airplane might not spin at normal spinning-control configuration, but if a spin were obtained, recovery therefrom by full rudder reversal would be satisfactory. It was also indicated that aileron-against settings would lead to violent oscillatory motions and should be avoided.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7L03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Flight Investigation to Determine the Effect of Jet Exhaust on Drag, Trim Characteristics, and Afterbody Pressures of a 0.125-Scale Rocket Model of the Mcdonnell F-101A Airplane (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A flight investigation was conducted to determine the effect of jet exhaust on the drag, trim characteristics, and afterbody pressures on a 0.125-scale rocket model of the McDonnell F-101A airplance. Power-off data were obtained over a Mach number range of 1.04 to 1.9 and power-on data were obtained at a Mach number of about 1.5. The data indicated that with power-on the change in external drag coefficient was within the data accuracy and there was a decrease in trim angle of attack of 1.27 degrees with a corresponding decrease of 0.07 in lift coefficient. Correspondingly, pressure coefficients on the side and bottom of the fuselage indicated a positive increment near the jet exit. As the distance downstream of the jet exit increased, the increment on the bottom of the fuselage increased, whereas the increments on the side decreased to a negative peak.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL56B03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Airspeed Operating Practices of Turbine-Powered Commercial Transport Airplanes (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Data obtained with NASA VGH and V-G recorders installed on three types of turboprop and one type of turbojet commercial transport air- plane have been analyzed to determine the relation of the maximum operational speeds to the placard normal-operating and never-exceed speeds. The frequency of exceeding the placard speeds is compared with corresponding results for past operations with piston-powered transports. In addition, data pertaining to the operational altitudes and the average airspeeds in rough and smooth air for the turbine-powered transports are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-744
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Free-Spinning-Tunnel Tests of a 1/35-Scale Model of the Douglas XB-43 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/35-scale model of the Douglas XB-43 airplane. The spin and recovery characteristics were determined for several loading conditions of the airplane. The effects of installing a dorsal fin and of installing a ventral fin were investigated. Emergency escape of the crew was simulated and the stick and rudder pedal forces necessary to effect recoveries on the airplane were determined.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7G01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Development of Micro Air Reconnaissance Vehicle as a Test Bed for Advanced Sensors and Electronics (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the development of a Micro/Mini Air Reconnaissance Vehicle for advanced sensors and electronics at NASA Langley Research Center over the last year. This vehicle is expected to have a total weight of less than four pounds, a design velocity of 40 mph, an endurance of 15-20 minutes, and a maximum range of 5km. The vehicle has wings that are simple to detach yet retain the correct alignment. The upper fuselage surface has a quick release hatch used to access the interior and also to mount the varying propulsion systems. The sensor suite developed for this vehicle consists of a Pitot-static measurement system for determining air speed, an absolute pressure measurement for determining altitude, magnetic direction measurement, and three orthogonal gyros to determine body angular rates. Swarming GPS-guidance and in-flight maneuvering is discussed, as well as design and installation of some other advance sensors like MEMS microphones, infrared cameras, GPS, humidity sensors, and an ultrasonic sonar sensor. Also low cost, small size, high performance control and navigation system for the Micro Air Vehicle is discussed. At the end, laboratory characterization of different sensors, motors, propellers, and batteries will be discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2002-3411 , 1st AIAA Unmanned Aerospace Vehicles, Systems, Technologies and Operations Technical Conference and Workshop; May 20, 2002 - May 23, 2002; Portsmouth, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Airborne Subscale Transport Aircraft Research Testbed: Aircraft Model Development (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Airborne Subscale Transport Aircraft Research (AirSTAR) testbed being developed at NASA Langley Research Center is an experimental flight test capability for research experiments pertaining to dynamics modeling and control beyond the normal flight envelope. An integral part of that testbed is a 5.5% dynamically scaled, generic transport aircraft. This remotely piloted vehicle (RPV) is powered by twin turbine engines and includes a collection of sensors, actuators, navigation, and telemetry systems. The downlink for the plane includes over 70 data channels, plus video, at rates up to 250 Hz. Uplink commands for aircraft control include over 30 data channels. The dynamic scaling requirement, which includes dimensional, weight, inertial, actuator, and data rate scaling, presents distinctive challenges in both the mechanical and electrical design of the aircraft. Discussion of these requirements and their implications on the development of the aircraft along with risk mitigation strategies and training exercises are included here. Also described are the first training (non-research) flights of the airframe. Additional papers address the development of a mobile operations station and an emulation and integration laboratory.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2005-6432 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 15, 2005 - Aug 18, 2005; San Francisco, CA; United States
    Format: application/pdf
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  • 10
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    Estimation of the Spin and Recovery Characteristics of the North American XSN2J-1 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The probable spin and recovery characteristics of the XSN2J-1 air-plane have been estimated on the basis of the results of brief test a performed on a model of an airplane of somewhat similar design. The spin-recovery tail-parachute requirements for the airplane were also determined end, in addition, an analysis was made to determine the best method of emergency pilot escape during a spin. The results of the investigation indicate that the recovery characteristics of the airplane will be satisfactory for all probable loading conditions of the airplane. A 6-foot-diameter tall parachute attached to a 30-foot tow-line will be satisfactory as a spin-recovery device for emergency recovery from demonstration spins. If the occupants of the airplane decide to abandon the airplane in a spin, they should leave the airplane from the outboard side of the cockpit and as far rearward as possible.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7F23b
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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