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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 541 records · Page 30
All sourcesNASA NTRSDOE OSTI
NASA NTRS1990

Heavy rain effects on airplane performance

The objective is to determine if the aerodynamic characteristics of an airplane are altered while flying in the rain. Wind-tunnel tests conducted at the NASA Langley Research Center (LaRC) have shown losses in maximum lift, reduction in stall angle, and increases in drag when a wing is placed in a simulated rain spray. For these tests the water spray concentration used represented a very heavy rainfall. A lack of definition of the scaling laws for aerodynamic testing in a two-phase, two-component flow makes interpolation of the wind-tunnel test uncertain. Tests of a large-scale wing are to be conducted at the LaRC. The large-scale wing is mounted on top of the Aircraft Landing Dynamics Facility (ALDF) carriage. This carriage (which is 70-foot long, 30-foot wide, and 30-foot high) is propelled with the wing model attached down a 3000-foot long test track by a water jet at speeds of up to 170 knots. A simulated rain spray system has been installed along 500 feet of the test track and can simulate rain falls from 2 to 40 inches/hour. Operational checks are underway and the initial tests should be completed by the Fall of 1989.

Dunham, R. E., Jr.↗
NASA NTRS1990

Aerodynamic Effect of Strakes on Two-Dimensional Tail Boom Models of the OH-58A and the OH-58D Helicopters

During hover and low speed flight, helicopters experience significant aerodynamic forces on the tail boom caused by the wake from the main and tail rotors and by crosswinds. These effects were simulated during a study conducted in the Langley 14 by 22 Foot Subsonic Tunnel on a 136 percent scaled 2-D tail boom model with cross sections representative of those on the U.S. Army OH-58A and the OH-58D helicopters. The effects of longitudinal strakes attached to the cross sections were studied. To obtain the aerodynamic forces acting on the cross sections, the flow incidence range on the scaled models was varied from -45 to 90 degrees and the models were tested through a dynamic pressure range of 5 to 15 psf. The results of the OH-58A and the OH-58D configurations show a significant improvement at conditions which represent right sideward flight by reducing the adverse aerodynamic side force when the strakes are installed. These data were used to calculate a change in tail rotor power for the full scale flight vehicle and indicated approx. a 5 to 6 percent average savings in right sideward flight for the critical velocity range of 0 to 30 knots. Increases in the tail boom normal force were noted due to the strakes. The results indicate a potential for reducing the directional control and tail rotor thrust required in the critical hover and right sideward flight speed range with a calculated minimum increase to main rotor power required and an overall net improvement in power of 0.5 percent for both the OH-58A and OH-58D.

Crowell, Cynthia A.↗
NASA NTRS1990

CO aperture synthesis of NGC 4038/9 (ARP 244)

Researchers present high-resolution (approx. 6 seconds) CO observations of the merging galaxies NGC 4038/9 made with the Owens Valley Radio Observatory (OVRO) Millimeter Wave Interferometer. The CO observations of Arp 244 were obtained between April and June 1988 using the OVRO Millimeter Wave Interferometer. Two fields with phase centers near the NGC 4039 nucleus and near the NGC 4038 nucleus were observed. The size of the synthesized beam is approximately 6.5 x 7 seconds at PA=72 degrees. The rms in a single cleaned channel map is 0.06 Jy beam(exp -1), corresponding to a brightness temperature of 0.12 K over the synthesized beam. Contour maps of the integrated CO intensity for both interferometer fields are shown. Three CO concentrations are evident. Two are centered near the nuclei of NGC 4038 and NGC 4039, closely correlated with H alpha and radio continuum maxima. A third CO emission region lies about 25 seconds northeast of the NGC 4039 nucleus. A number of radio continuum, H alpha, and 10 micron emission knots appear in this region. The total integrated intensity at the northern nuclear source, 302 K km/s, leads to a molecular mass of 8.3 by 10 to the 8th power solar mass assuming a Galactic CO to H2 conversion factor of 3.0 x 10 to the 20th power H2 cm(-2) (K km/s)(-1). The integrated CO intensity of the southern nuclear source leads to a molecular mass of 2.4 x 10 to the 8th solar mass. The extranuclear CO concentration contains 1.2 x 10 to the 9th power solar mass of molecular gas, extending over 170 km/s, and is resolved in a number of channels. Its large size, mass, and morphology strongly suggest that it is an agglomeration of several clumps.

Stanford, S. A.↗
NASA NTRS1990

Large-scale aeroacoustic research feasibility and conceptual design of test-section inserts for the Ames 80- by 120-foot wind tunnel

An engineering feasibility study was made of aeroacoustic inserts designed for large-scale acoustic research on aircraft models in the 80 by 120 foot Wind Tunnel at NASA Ames Research Center. The advantages and disadvantages of likely designs were analyzed. Results indicate that the required maximum airspeed leads to the design of a particular insert. Using goals of 200, 150, and 100 knots airspeed, the analysis indicated a 30 x 60 ft open-jet test section, a 40 x 80 ft open jet test section, and a 70 x 100 ft closed test section with enhanced wall lining, respectively. The open-jet inserts would be composed of a nozzle, collector, diffuser, and acoutic wedges incorporated in the existing 80 x 120 test section. The closed test section would be composed of approximately 5 ft acoustic wedges covered by a porous plate attached to the test section walls of the existing 80 x 120. All designs would require a double row of acoustic vanes between the test section and fan drive to attenuate fan noise and, in the case of the open-jet designs, to control flow separation at the diffuser downstream end. The inserts would allow virtually anechoic acoustic studies of large helicopter models, jets, and V/STOL aircraft models in simulated flight. Model scale studies would be necessary to optimize the aerodynamic and acoustic performance of any of the designs. In all designs studied, the existing structure would have to be reinforced. Successful development of acoustically transparent walls, though not strictly necessary to the project, would lead to a porous-wall test section that could be substituted for any of the open-jet designs, and thereby eliminate many aerodynamic and acoustic problems characteristic of open-jet shear layers. The larger size of the facility would make installation and removal of the insert components difficult. Consequently, scheduling of the existing 80 x 120 aerodynamic test section and scheduling of the open-jet test section would likely be made on an annual or longer basis. The enhanced wall-lining insert would likely be permanent. Although the modifications are technically feasible, the economic practicality of the project was not evaluated.

Soderman, Paul T.↗
NASA NTRS1991

Technology needs for high-speed rotorcraft

A study to determine the technology development required for high-speed rotorcraft development was conducted. The study begins with an initial assessment of six concepts capable of flight at, or greater than 450 knots with helicopter-like hover efficiency (disk loading less than 50 pfs). These concepts were sized and evaluated based on measures of effectiveness and operational considerations. Additionally, an initial assessment of the impact of technology advances on the vehicles attributes was made. From these initial concepts a tilt wing and rotor/wing concepts were selected for further evaluation. A more detailed examination of conversion and technology trade studies were conducted on these two vehicles, each sized for a different mission.

Rutherford, John↗
NASA NTRS1991

Simulation evaluation of a speed-guidance law for Harrier approach transitions

An exponential-deceleration speed guidance law is formulated which mimics the technique currently used by Harrier pilots to perform decelerating approaches to a hover. This guidance law was tested along with an existing two-step constant deceleration speed guidance law, using a fixed-base piloted simulator programmed to represent a YAV-8B Harrier. Decelerating approaches to a hover at a predetermined station-keeping point were performed along a straight (-3 deg glideslope) path in headwinds up to 40 knots and turbulence up to 6 ft./sec. Visibility was fixed at one-quarter nautical mile and 100 ft. cloud ceiling. Three Harrier pilots participated in the experiment. Handling qualities with the aircraft equipped with the standard YAV-8B rate damped attitude stability augmentation system were adequate (level 2) using either speed guidance law. However, the exponential deceleration speed guidance law was rated superior to the constant-deceleration speed guidance law by a Cooper-Harper handling qualities rating of about one unit independent of the level of wind and turbulence. Replacing the attitude control system of the YAV-8B with a high fidelity model following attitude flight controller increased the approach accuracy and reduced the pilot workload. With one minor exception, the handling qualities for the approach were rated satisfactory (level 1). It is concluded that the exponential deceleration speed guidance law is the most cost effective.

Merrick, Vernon K.↗
NASA NTRS1991

Ames Research Center C-130

The C130 Earth Resources Aircraft provides a platform for a variety of sensors that collect data in support of terrestrial and atmospheric projects sponsored by NASA in coordination with Federal, state, university, and industry investigators. This data is applied to research in the areas of forestry, agriculture, land use and land cover analysis, hydrology, geology, photogrammetry, oceanography, meteorology, and other earth science disciplines. The C130 is a platform aircraft flying up to 25,000 feet above sea level at speeds between 150 and 330 knots True Air Speed. The aircraft is capable of precise flight line navigation by means of an optical borescope from which line guidance is provided to the pilots.

Koozer, Mark A.↗
NASA NTRS1991

Technology needs for high-speed rotorcraft, volume 1

High-speed rotorcraft concepts and the technology needed to extend rotorcraft cruise speeds up to 450 knots (while retaining the helicopter attributes of low downwash velocities) were identified. Task I identified 20 concepts with high-speed potential. These concepts were qualitatively evaluated to determine the five most promising ones. These five concepts were designed with optimum wing loading and disk loading to a common NASA-defined military transport mission. The optimum designs were quantitatively compared against 11 key criteria and ranked accordingly. The two highest ranking concepts were selected for the further study.

Wilkerson, J. B.↗
NASA NTRS1991

Enhancement of surface definition and gridding in the Eagle code

A method for locally fairing uniform cubic B-spline curves and surfaces is presented. The algorithm uses an automated technique which detects undesirable geometric characteristics by using a local fairness criterion. The geometric entity is then smoothed using a method based on the repeated removal and insertion of the spline knots in the vicinity of the geometric irregularity.

Source record↗
NASA NTRS1990

The design and flight testing of a long endurance RPV

This paper covers the design process for a long endurance RPV. The 56-pound RPV must operate in the 25-60 knot speed range at low altitudes. An airfoil designed for low-Reynolds-number applications was used with a wing of aspect ratio 22 to reach an estimated L/D(max) of 25. Wing tip feathers were designed to reduce the induced drag. A comparison between the computed aerodynamic predictions and wind-tunnel results is given. The estimated endurance is on the order of 50 hours/gallon of fuel. A three-surface configuration was chosen, and the predicted handling quality and performance results obtained so far are given. The structural challenges in building a lightweight structure for the wing and control surfaces are outlined. The flight test program is currently underway.

Siddiqi, Shahid↗
NASA NTRS1991

First results from the Faint Object Camera - Observations of PKS 0521 - 36

The Faint Object Camera on the Hubble Space Telescope was used to observe the radio galaxy PKS 0521 - 36 which hosts a prominent radio jet. Images of the jet show spatial structure comparable to VLA data and significantly better than optical ground-based observations. The jet structure is resolved at FOC resolution. In addition to the radio knot, well resolved by the FOC, an extension of the jet toward the nucleus is apparent. The rest of the jet does not show much clumpiness, implying that the synchrotron electrons must be accelerated all along the jet to account for the extent in the optical region.

Macchetto, F.↗
NASA NTRS1991

0.4-arc-second images of 3C 273

Images in V and I bands of the QSO 3C 273 (1226 + 023) were obtained using the High-Resolution Camera of the Canada-France-Hawaii telescope. Attention is given to the structure and colors of the jet and details of the host galaxy which have not been observed in previous studies. The systematic change of color along the jet suggests an aging process in a synchrotron spectrum, while the irregularity of the knots and wiggles suggests that the jet structure is primarily governed by passage through a clumpy medium near the host galaxy.

Hutchings, J. B.↗
NASA NTRS1991

HH 5, HH 6, and their exciting stars

Long-slit optical spectroscopy, astrometry, and H-alpha forbidden S II and broad-band 2 micron images of HH 5 and of the HH 6 complex have been obtained. The excitations and radial velocities of the individual HH knots are described. The morphology of the optical and the 2 micron images (the latter dominated by H2 emission and/or the continuum of any embedded exciting stars) is compared; and the new astrometry is discussed. Finally, the likely sources of excitation of these HH nebulae are commented on.

Cohen, Martin↗
NASA NTRS1991

The radio to X-ray spectrum of the M87 jet and nucleus

Einstein Observatory high-resolution imager data are used in conjunction with recent radio and optical observations to examine the morphology of the M87 jet; IR and UV data from the literature are then employed to construct X-ray spectra for the jet and nucleus, allowing the isolation of new features in the X-ray images which are associable with the radio/optical knots B and D. The synchrotron mechanism is suggested to be the originator of the jet X-ray emission, despite its entailment of very high energy electrons with short lifetimes. Optical data for the nucleus are consistent with the presence of an unresolved blue continuum source, implying a spectrum similar to that of the jet except at high RFs.

Biretta, J. A.↗
NASA NTRS1991

High-speed rotorcraft propulsion

Recently completed high-speed rotorcraft design studies for NASA provide the basis to assess technology needs for the development of these aircraft. Preliminary analysis of several concepts possessing helicopter-like hover characteristics and cruise capabilities in the 450 knot regime, led to the selection of two concepts for further study. The concepts selected included the Rotor/Wing and the Tilt Wing. The two unique concepts use turbofan and turboshaft engines respectively. Designs, based on current technology for each, established a baseline configuration from which technology trade studies could be conducted. Propulsion technology goals from the IHPTET program established the advanced technolgy year. Due to high-speed requirements, each concept possesses its own unique propulsion challenges. Trade studies indicate that achieving th IHPTET Phase III goals significantly improves the effectiveness of both concepts. Increased engine efficiency is particularly important to VTOL aircraft by reducing gross weight.

Rutherford, John W.↗
NASA NTRS1991

Low-speed aerodynamics of the trailed-rotor high-speed rotorcraft concept in cruise configuration

An experimental investigation was performed to determine the low-speed aerodynamic performance characteristics of the trailed-rotor high-speed rotorcraft concept in its cruise configuration. A 15 percent scale semispan model was tested at speeds up to 180 knots in the NASA Ames 7-by 10-Foot Subsonic Wind Tunnel. The objective of this investigation was to determine specific aerodynamic performance characteristics to assist in evaluating the trailed rotor as a high-speed rotorcraft. The aerodynamic influence of the following model configuration changes were determined: ailerons, flaps, wing/pod angle, number of trailed blades, trailed-blade twist and azimuth, and wing/pod filet radius. The low-speed performance objectives for the concept were met and results indicated that the trailed-rotor model had no significant adverse aerodynamic characteristics. The optimum low-speed cruise configuration was determined. Results suggest the trailed-rotor concept has better low-speed cruise performance characteristics than the folding tiltrotor configuration.

Johnson, Jeffrey L.↗
NASA NTRS1991

IUE observations of NGC 1068 - The extended high-ionization emission region

The emissions of the highly ionized species of N V, C IV, and He II have been used to delineate the extent of the high-ionization emission region (HIER) of NGC 1068. The observed fluxes from these features are quite large and are equal to those seen in IUE exposure of the central AGN. The HIER is extremely anisotropic about the nucleus with emission seen only in the NE quadrant within 2.5 kpc of the AGN. The correlation of strong emission in the HIER with the UV starburst knots strongly suggests that much of the observed emission is produced in the galactic plane of NGC 1068. A speculative, qualitative model is presented which supports the so-called dusty torus model and suggests that there has been preferential clearing of attenuating gas and dust both very near the nucleus and in the inner galactic disk.

Truong, K. Q.↗
NASA NTRS1990

A comparison of three regions of Puppis A

High resolution X-ray spectral observations of Puppis A were performed with the FPCS on the Einstein Observatory at three regions of the remnant: the shock front, the bright eastern knot, and the interior. Plasma diagnostics of lines from OVII and OVIII constrain the values of electron temperature, ionization timescale, and hydrogen column density. Results of the diagnostics for these three regions are compared. A nonequilibrium analysis of previously published fluxes of oxygen lines shows that the interior has not yet reached ionization equilibrium.

Fischbach, K. F.↗