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  • 11
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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
  • 12
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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
  • 13
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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
  • 14
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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
  • 15
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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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    NASA TECHNICAL REPORTS
  • 16
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    Moderate-Resolution Spitzer Infrared Spectrograph Observations of M, L, and T Dwarfs (2007)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: We present 10-19 micrometers moderate-resolution spectra of 10 M dwarfs, one L dwarf, and two T dwarf systems obtained with the Infrared Spectrograph (IRS) on board the Spitzer Space Telescope. The IRS allows us to examine molecular spectroscopic features/lines at moderate spectral resolution in a heretofore untapped wavelength regime. These R = (lamda)/(Delta)(lamda) approximately equal to 600 spectra allow for a more detailed examination of clouds and nonequilibrium chemistry, as well as the molecular features of H2O, NH3, and other trace molecular species that are the hallmarks of these objects. A cloud-free model best fits our mid-infrared spectrum of the T1 dwarf (Sigma) Indi Ba, and we find that the NH3 feature in (Sigma) Indi Bb is best explained by a nonequilibrium abundance due to vertical transport in its atmosphere.We examined a set of objects (mostly M dwarfs) in multiple systems to look for evidence of emission features, which might indicate an atmospheric temperature inversion, as well as trace molecular species; however, we found no evidence of either.
    Keywords: Astronomy
    Type: The Astrophysical Journal; 662; 1245-1253
    Format: text
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    NASA TECHNICAL REPORTS
  • 17
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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
  • 18
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    Application of a Self-Similar Pressure Profile to Sunyaev-Zeldovich Effect Data from Galaxy Clusters (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: We investigate the utility of a new, self-similar pressure profile for fitting Sunyaev-Zel'dovich (SZ) effect observations of galaxy clusters. Current SZ imaging instruments-such as the Sunyaev-Zel'dovich Array (SZA)- are capable of probing clusters over a large range in a physical scale. A model is therefore required that can accurately describe a cluster's pressure profile over a broad range of radii from the core of the cluster out to a significant fraction of the virial radius. In the analysis presented here, we fit a radial pressure profile derived from simulations and detailed X-ray analysis of relaxed clusters to SZA observations of three clusters with exceptionally high-quality X-ray data: A1835, A1914, and CL J1226.9+3332. From the joint analysis of the SZ and X-ray data, we derive physical properties such as gas mass, total mass, gas fraction and the intrinsic, integrated Compton y-parameter. We find that parameters derived from the joint fit to the SZ and X-ray data agree well with a detailed, independent X-ray-only analysis of the same clusters. In particular, we find that, when combined with X-ray imaging data, this new pressure profile yields an independent electron radial temperature profile that is in good agreement with spectroscopic X-ray measurements.
    Keywords: Astronomy
    Type: M09-0071 , The Astrophysical Journal; 694; 1034-1044
    Format: text
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    NASA TECHNICAL REPORTS
  • 19
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    Technology Challenges in Small UAV Development (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Development of highly capable small UAVs present unique challenges for technology protagonists. Size constraints, the desire for ultra low cost and/or disposable platforms, lack of capable design and analysis tools, and unique mission requirements all add to the level of difficulty in creating state-of-the-art small UAVs. This paper presents the results of several small UAV developments, the difficulties encountered, and proposes a list of technology shortfalls that need to be addressed.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2005-7089 , Infotech@Aerospace; Sep 26, 2005 - Sep 29, 2005; Arlington, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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