United States National Aeronautics and Space Administration
Overview
| Works: | 133 works in 156 publications in 1 language and 204 library holdings |
|---|---|
| Genres: | Conference papers and proceedings Handbooks and manuals Specifications |
Publication Timeline
.
Most widely held works by
United States
Experimental investigation of Mach 3 cruise heating simulations on a representative wing structure for flight-loads measurement by
Roger A Fields(
Book
)
1 edition published in 1972 in English and held by 6 WorldCat member libraries worldwide
Radiant heating experiments were performed in the laboratory on an instrumented multispar wing structure to investigate (1) how accurately the structural temperatures of a Mach 3 cruise-flight profile could be simulated, (2) what the effects of the heating and heating inaccuracies would be on the responses of strain-gage bridges installed on the structure, and (3) how these responses would affect flight loads measurements. Test temperatures throughout the structure agreed well with temperatures calculated for a Mach 3 profile. In addition, temperatures produced by two identical tests were repeatable to less than ±6 K⁰ (±10 F⁰). Thermally induced strain-gage-bridge responses were large enough to be detrimental to a high-speed flight loads program with a goal of establishing aerodynamic loads (exclusive of thermal loads). It was shown that heating simulation can be used effectively for thermal calibration (that is, to provide corrections for a high-temperature environment), and that thermal calibration may not be needed if the simulation data are used to carefully select bridges and load equations.--P. [i]
1 edition published in 1972 in English and held by 6 WorldCat member libraries worldwide
Radiant heating experiments were performed in the laboratory on an instrumented multispar wing structure to investigate (1) how accurately the structural temperatures of a Mach 3 cruise-flight profile could be simulated, (2) what the effects of the heating and heating inaccuracies would be on the responses of strain-gage bridges installed on the structure, and (3) how these responses would affect flight loads measurements. Test temperatures throughout the structure agreed well with temperatures calculated for a Mach 3 profile. In addition, temperatures produced by two identical tests were repeatable to less than ±6 K⁰ (±10 F⁰). Thermally induced strain-gage-bridge responses were large enough to be detrimental to a high-speed flight loads program with a goal of establishing aerodynamic loads (exclusive of thermal loads). It was shown that heating simulation can be used effectively for thermal calibration (that is, to provide corrections for a high-temperature environment), and that thermal calibration may not be needed if the simulation data are used to carefully select bridges and load equations.--P. [i]
Longitudinal stability and control derivatives of a jet fighter airplane extracted from flight test data by utilizing maximum
likelihood estimation by
George G Steinmetz(
Book
)
1 edition published in 1971 in English and held by 5 WorldCat member libraries worldwide
"A method of parameter extraction for stability and control derivatives of aircraft from flight test data, implementing maximum likelihood estimation, has been developed and successfully applied to actual longitudinal flight test data from a modern sophisticated jet fighter. The results of this application establish the merits of the estimation technique and its computer implementation (allowing full analyst interaction with the program) as well as provide data for the validation of a portion of the Langley differential maneuvering simulator (DMS). The results are presented for all flight test runs in tabular form and as time history comparisons between the estimated states and the actual flight test data."--Page [i]
1 edition published in 1971 in English and held by 5 WorldCat member libraries worldwide
"A method of parameter extraction for stability and control derivatives of aircraft from flight test data, implementing maximum likelihood estimation, has been developed and successfully applied to actual longitudinal flight test data from a modern sophisticated jet fighter. The results of this application establish the merits of the estimation technique and its computer implementation (allowing full analyst interaction with the program) as well as provide data for the validation of a portion of the Langley differential maneuvering simulator (DMS). The results are presented for all flight test runs in tabular form and as time history comparisons between the estimated states and the actual flight test data."--Page [i]
Low-lift-to-drag-ratio approach and landing studies using a CV-990 airplane by Berwin M Kock(
Book
)
1 edition published in 1972 in English and held by 5 WorldCat member libraries worldwide
Results are presented of a flight-test program utilizing a CV-990 airplane, flow in low-lift-to-drag-ratio (L/D) configurations, to simulate terminal area operation, approach, and landing of large unpowered vehicles. The results indicate that unpowered approaches and landings are practical with vehicles of the size and performance characteristics of the proposed shuttle vehicle. Low L/D landings provided touchdown dispersion patterns acceptable for operation on runways of reasonable length. The dispersion pattern was reduced when guidance was used during the final approach. High levels of pilot proficiency were not required for acceptable performance.--P. [i]
1 edition published in 1972 in English and held by 5 WorldCat member libraries worldwide
Results are presented of a flight-test program utilizing a CV-990 airplane, flow in low-lift-to-drag-ratio (L/D) configurations, to simulate terminal area operation, approach, and landing of large unpowered vehicles. The results indicate that unpowered approaches and landings are practical with vehicles of the size and performance characteristics of the proposed shuttle vehicle. Low L/D landings provided touchdown dispersion patterns acceptable for operation on runways of reasonable length. The dispersion pattern was reduced when guidance was used during the final approach. High levels of pilot proficiency were not required for acceptable performance.--P. [i]
Lateral vibration characteristics of the 1/10-scale Apollo/Saturn v replica model by
Ellwood L Peele(
Book
)
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
A l/l0-scale replica model of the Apollo/Saturn V vehicle has been tested to determine its free-free lateral vibration characteristics. Several simulated propellant loadings were investigated for each of three model configurations simulating the firststage, second-stage, and third-stage burns. Tests were conducted in both the pitch and yaw directions. A one-dimensional lumped-parameter analysis employing the transfermatrix method was used to calculate the uncoupled natural modes and frequencies of the system. Analytical parameter studies were conducted to investigate the effects of engine flexibility, liquid slosh, and decreased stiffness due to ineffective skin on the modal behavior of the system.--P. [i]
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
A l/l0-scale replica model of the Apollo/Saturn V vehicle has been tested to determine its free-free lateral vibration characteristics. Several simulated propellant loadings were investigated for each of three model configurations simulating the firststage, second-stage, and third-stage burns. Tests were conducted in both the pitch and yaw directions. A one-dimensional lumped-parameter analysis employing the transfermatrix method was used to calculate the uncoupled natural modes and frequencies of the system. Analytical parameter studies were conducted to investigate the effects of engine flexibility, liquid slosh, and decreased stiffness due to ineffective skin on the modal behavior of the system.--P. [i]
Aerodynamic characteristics of a large-scale model a lift fan mounted in a 5-percent-thick triangular wing, including the
effects of BLC on the lift-fan inlet by Brent K Hodder(
Book
)
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
The low-speed aerodynamics of a large-scale triangular wing model, with a reduced thickness, tip-turbine driven lift fan in each wing were investigated in the Ames 40-by 80-Foot Wind Tunnel. The model had a 5-percent-thick wing typical of wings designed for supersonic performance. Conventional lift-fan depth has, in the past, limited wing thickness to about 10 percent. A thinner lift fan for the present investigation was obtained by modification of a conventional fan. The modification included removing the discharge stator and reducing the fan inlet length and radius. To control airflow separation resulting from small inlet radii, blowing boundary-layer control was applied through a nozzle in the inlet. Performance of the modified fan along with aerodynamic characteristics of the total configuration is presented. The static thrust performance of the conventional fan (requiring a lo-percent wing) was equalled by the reduced thickness fans of this investigation.--P. [i]
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
The low-speed aerodynamics of a large-scale triangular wing model, with a reduced thickness, tip-turbine driven lift fan in each wing were investigated in the Ames 40-by 80-Foot Wind Tunnel. The model had a 5-percent-thick wing typical of wings designed for supersonic performance. Conventional lift-fan depth has, in the past, limited wing thickness to about 10 percent. A thinner lift fan for the present investigation was obtained by modification of a conventional fan. The modification included removing the discharge stator and reducing the fan inlet length and radius. To control airflow separation resulting from small inlet radii, blowing boundary-layer control was applied through a nozzle in the inlet. Performance of the modified fan along with aerodynamic characteristics of the total configuration is presented. The static thrust performance of the conventional fan (requiring a lo-percent wing) was equalled by the reduced thickness fans of this investigation.--P. [i]
A simulator study of the control of lunar flying platforms by pilot body motions by
Paul R Hill(
Book
)
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
"This paper presents the results of an investigation of body-motion control of lunar-flying-platform configurations utilizing shirt-sleeved operators and a simulator with five degrees of freedom. The results show that lunar vehicles with moments of inertia up to 100 slug-ft² (136 kg-m²) in pitch and 300 or 400 slug-ft² (407 of 542 kg-m²) in roll should have satisfactory control qualities. The separation of the vehicle operator and thrusts jets from the high-inertia vehicle elements by means of a low inertia auxiliary platform resulted in satisfactory control in both pitch and roll over the range of equivalent lunar moments of inertia of 33 to 400 slug-ft² (45 to 542 kg-m²). A description of a number of useful variations of body-motion control is presented."--Page [i]
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
"This paper presents the results of an investigation of body-motion control of lunar-flying-platform configurations utilizing shirt-sleeved operators and a simulator with five degrees of freedom. The results show that lunar vehicles with moments of inertia up to 100 slug-ft² (136 kg-m²) in pitch and 300 or 400 slug-ft² (407 of 542 kg-m²) in roll should have satisfactory control qualities. The separation of the vehicle operator and thrusts jets from the high-inertia vehicle elements by means of a low inertia auxiliary platform resulted in satisfactory control in both pitch and roll over the range of equivalent lunar moments of inertia of 33 to 400 slug-ft² (45 to 542 kg-m²). A description of a number of useful variations of body-motion control is presented."--Page [i]
Simulation and analysis of panel separation from the Apollo 13 service module by H. Wayne Leonard(
Book
)
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
"An experimental and analytical program was conducted to simulate the separation of the service module bay 4 cover panel from the Apollo 13 spacecraft which occurred during its flight accident. The study was also intended to establish failure mechanisms, pressure distributions, and pressure time histories that would explain the essentially complete separation that was observed in the photographs taken by the Apollo 13 crew. Complete separations of both isotropic and sandwich one-half-scale panel models from a boilerplate test fixture were achieved by rapidly pressurizing the oxygen shelf space with air in a vacuum environment. The sandwich panels tested were most representative of flight hardware. One particular sandwich panel separated as a result of a non-uniform pressure distribution of over 40 psi in the oxygen shelf space 20 milliseconds after start of pressurization; this result was the one most nearly consistent with known flight events. A similar test at slightly lower pressure did not separate the panel; thus, the separation pressure distribution and time history boundary was established.--P. [i]
1 edition published in 1970 in English and held by 5 WorldCat member libraries worldwide
"An experimental and analytical program was conducted to simulate the separation of the service module bay 4 cover panel from the Apollo 13 spacecraft which occurred during its flight accident. The study was also intended to establish failure mechanisms, pressure distributions, and pressure time histories that would explain the essentially complete separation that was observed in the photographs taken by the Apollo 13 crew. Complete separations of both isotropic and sandwich one-half-scale panel models from a boilerplate test fixture were achieved by rapidly pressurizing the oxygen shelf space with air in a vacuum environment. The sandwich panels tested were most representative of flight hardware. One particular sandwich panel separated as a result of a non-uniform pressure distribution of over 40 psi in the oxygen shelf space 20 milliseconds after start of pressurization; this result was the one most nearly consistent with known flight events. A similar test at slightly lower pressure did not separate the panel; thus, the separation pressure distribution and time history boundary was established.--P. [i]
Lunar science VI : abstracts of papers submitted to the sixth Lunar Science Conference by Lunar Science Conference(
Book
)
4 editions published in 1975 in English and held by 4 WorldCat member libraries worldwide
4 editions published in 1975 in English and held by 4 WorldCat member libraries worldwide
Effect of error in spectral measurements of solar simulators on surface response by Henry B Curtis(
Book
)
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
Effect of measurement error in spectral distribution of solar simulators
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
Effect of measurement error in spectral distribution of solar simulators
Investigation of an optimum detection scheme for a star-field mapping system by Melvin D Aldridge(
Book
)
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
"An investigation was made to determine the optimum detection scheme for a star-field mapping system that uses coded detection resulting from starlight shining through specially arranged multiple slits of a reticle. With threshold levels established by the Neyman-Pearson criterion, the computer solutions of equations derived from a theoretical model are used to judge performance and then practical problems such as synchronization, code construction, and detector noise are considered. On the basis of the Neyman-Pearson criterion it was determined that the maximum probability of detection occurred with the use of a single transparent slit in them odulating reticle. However, use of multiple slits improved the system's ability to reject the detection of undesirable lower intensity stars, but only by decreasing the detection probability of the lower intensity stars to be mapped. Also, it was found that the coding arrangement affected the root-mean-square star-position error and that detection is possible with error in the system's detected spin rate, though at a reduced probability."--Page [i]
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
"An investigation was made to determine the optimum detection scheme for a star-field mapping system that uses coded detection resulting from starlight shining through specially arranged multiple slits of a reticle. With threshold levels established by the Neyman-Pearson criterion, the computer solutions of equations derived from a theoretical model are used to judge performance and then practical problems such as synchronization, code construction, and detector noise are considered. On the basis of the Neyman-Pearson criterion it was determined that the maximum probability of detection occurred with the use of a single transparent slit in them odulating reticle. However, use of multiple slits improved the system's ability to reject the detection of undesirable lower intensity stars, but only by decreasing the detection probability of the lower intensity stars to be mapped. Also, it was found that the coding arrangement affected the root-mean-square star-position error and that detection is possible with error in the system's detected spin rate, though at a reduced probability."--Page [i]
Flight investigation of a V/STOL transport model with four pod-mounted lift fans by
William A Newsom(
Book
)
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
"The investigation consisted of free-flight model tests in hovering and forward flight through the transition speed range up to the point where conversation would be made to wing-borne flight. Dynamic stability characteristics of the model were also calculated for correction with flight results. Because of a small static margin and speed instability, artificial damping in pitch was needed to obtain satisfactory pitch characteristics. No problem was experienced with roll or yaw through the transition speed range."--Page [i]
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
"The investigation consisted of free-flight model tests in hovering and forward flight through the transition speed range up to the point where conversation would be made to wing-borne flight. Dynamic stability characteristics of the model were also calculated for correction with flight results. Because of a small static margin and speed instability, artificial damping in pitch was needed to obtain satisfactory pitch characteristics. No problem was experienced with roll or yaw through the transition speed range."--Page [i]
Relative susceptiblity of titanium alloys to hot-salt stress-corrosion by Hugh R Gray(
Book
)
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
Susceptibility of titanium alloys to hot-salt stress-corrosion cracking increased as follows: Ti-2Al-11Sn-5Zr-0.2Si(679), Ti-6Al-2Sn-4Zr-2Mo(6242), Ti-6Al-4V(64), Ti-6Al-4V-3Co(643), Ti-8Al-1Mo-1V(811), and Ti-13V-11Cr-3A1(13-11-3). The Ti-5Al-6Sn-2Zr-1Mo-0.25Si(5621S) alloy was both the least and most susceptible depending on heat treatment. Such rankings can be drastically altered by heat-to-heat and processing variations. Residual compressive stresses and cyclic exposures also reduce susceptibility to stress-corrosion. Simulated turbine-engine compressor environmental variables such as air velocity, pressure, dewpoint, salt concentration, and salt deposition temperature have only minor effects. Detection of substantial concentrations of hydrogen in all corroded alloys confirmed the existence of a hydrogen embrittlement mechanism.--P. [i]
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
Susceptibility of titanium alloys to hot-salt stress-corrosion cracking increased as follows: Ti-2Al-11Sn-5Zr-0.2Si(679), Ti-6Al-2Sn-4Zr-2Mo(6242), Ti-6Al-4V(64), Ti-6Al-4V-3Co(643), Ti-8Al-1Mo-1V(811), and Ti-13V-11Cr-3A1(13-11-3). The Ti-5Al-6Sn-2Zr-1Mo-0.25Si(5621S) alloy was both the least and most susceptible depending on heat treatment. Such rankings can be drastically altered by heat-to-heat and processing variations. Residual compressive stresses and cyclic exposures also reduce susceptibility to stress-corrosion. Simulated turbine-engine compressor environmental variables such as air velocity, pressure, dewpoint, salt concentration, and salt deposition temperature have only minor effects. Detection of substantial concentrations of hydrogen in all corroded alloys confirmed the existence of a hydrogen embrittlement mechanism.--P. [i]
An investigation of the fine-pointing control system of a soft-gimbaled orbiting telescope by
Frederick R Morrell(
Book
)
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
"Computer-simulation results are presented for the rigid-body planar equations of motion of an attitude-stabilized orbiting telescope passively coupled to a manned service module. This coupling is provided through a set of soft springs and a two-axis gimbal alined [sic] with the telescope center of mass. Principal nonlinearities in the suspension system and the telescope control system are included. The simulation indicates feasibility of this operational mode."--Page [i]
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
"Computer-simulation results are presented for the rigid-body planar equations of motion of an attitude-stabilized orbiting telescope passively coupled to a manned service module. This coupling is provided through a set of soft springs and a two-axis gimbal alined [sic] with the telescope center of mass. Principal nonlinearities in the suspension system and the telescope control system are included. The simulation indicates feasibility of this operational mode."--Page [i]
Mariner-Venus, 1962 : final project report by
Jet Propulsion Laboratory (U.S.)(
Book
)
1 edition published in 1965 in English and held by 4 WorldCat member libraries worldwide
1 edition published in 1965 in English and held by 4 WorldCat member libraries worldwide
Thrusting trajectory minimization program for orbital transfer maneuvers by
Lawrence H Hoffman(
Book
)
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
"A computer program has been designed which determines the minimum-burn-time, thrusting, transfer trajectory between two Keplerian orbits. The minimization equations are formulated with constant Lagrange multipliers and solved numerically with the Newton-Raphson method. The solution obtained in this paper is not truly optimum because the control vector has been restricted to constant values (i.e., to be optimum the control vector should be a function of time)."--Page [i]
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
"A computer program has been designed which determines the minimum-burn-time, thrusting, transfer trajectory between two Keplerian orbits. The minimization equations are formulated with constant Lagrange multipliers and solved numerically with the Newton-Raphson method. The solution obtained in this paper is not truly optimum because the control vector has been restricted to constant values (i.e., to be optimum the control vector should be a function of time)."--Page [i]
Reingestion characteristics and inlet flow distortion of V/STOL lift-engine fighter configurations by
Jerry V Kirk(
Book
)
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
Reingestion of exhaust gas into engine inlets during hover, and inlet flow distortion with the associated loss in total-pressure recovery during transition were studied using a largescale generalized lift-engine fighter model powered by 5-85 engines. Exhaust gas reingestion during hover was studied on a static test facility, and inlet flow distortion and total-pressure recovery loss were studied in the 40- by 80-foot wind tunnel. Two lift-engine arrangements were studied, the swiveling, retractable and the internally fixed. Both arrangements were subject to excessive thrust loss and compressor stalls due to reingestion when the engine exhaust was vectored nearly vertical. Vectoring the exhaust approximately 20' from vertical essentially eliminated reingestion problems. Vectoring the lift-engine exhaust forward and the lift-cruise engine exhaust aft tcr balance the aircraft and minimize reingestion appears to be a feasible means of allowing VTOL operation. Inlet flow distortion and total-pressure recovery were within acceptable limits for the swiveling, retractable lift-engine configuration. With the inlet guide vane installed to help turn the flow into the engine, the vertically mounted lift engines of the internally fixed configuration with an inlet radius to diameter ratio of 0.19 produced acceptable inlet flow distortion and totalpressure recovery results. Without the guide vane the nominal acceptable distortion level of 10 percent was exceeded at the higher velocity ratios.--P. i
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
Reingestion of exhaust gas into engine inlets during hover, and inlet flow distortion with the associated loss in total-pressure recovery during transition were studied using a largescale generalized lift-engine fighter model powered by 5-85 engines. Exhaust gas reingestion during hover was studied on a static test facility, and inlet flow distortion and total-pressure recovery loss were studied in the 40- by 80-foot wind tunnel. Two lift-engine arrangements were studied, the swiveling, retractable and the internally fixed. Both arrangements were subject to excessive thrust loss and compressor stalls due to reingestion when the engine exhaust was vectored nearly vertical. Vectoring the exhaust approximately 20' from vertical essentially eliminated reingestion problems. Vectoring the lift-engine exhaust forward and the lift-cruise engine exhaust aft tcr balance the aircraft and minimize reingestion appears to be a feasible means of allowing VTOL operation. Inlet flow distortion and total-pressure recovery were within acceptable limits for the swiveling, retractable lift-engine configuration. With the inlet guide vane installed to help turn the flow into the engine, the vertically mounted lift engines of the internally fixed configuration with an inlet radius to diameter ratio of 0.19 produced acceptable inlet flow distortion and totalpressure recovery results. Without the guide vane the nominal acceptable distortion level of 10 percent was exceeded at the higher velocity ratios.--P. i
Static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations at Mach numbers from 1.60 to 2.86. by
Samuel M Dollyhigh(
Book
)
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
An experimental investigation has been made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60° leading-edge-sweep wing; however, a small amount of data were obtained for a 44° leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard.--P. [i]
1 edition published in 1971 in English and held by 4 WorldCat member libraries worldwide
An experimental investigation has been made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60° leading-edge-sweep wing; however, a small amount of data were obtained for a 44° leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard.--P. [i]
Experimental results of high-current arcs driven supersonically in straight and circular channels by Alexander P Sabol(
Book
)
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
"Quantitative information concerning the static pressure associated with moving arcs and the arc velocity as a function of the Lorentz force for arc currents as high as 8000 amperes is given for magnetic-field strengths of 0.64 and 1.28 webers / meter². With the aid of ultra-high-speed photography and rapid-response pressure gages, results revealed that a single abrupt bow shock ahead of the arc did not occur but that a network of many small primary shocks preceded the luminous zone. In the circular channel tests, different gases and air were used at different densities. These tests, in which the arc ran through its own heated wake, indicated that the arc velocity is faster than that in a straight channel and depends on the gas density to the one-half power for the steady-state condition. During arc start-up periods, the arc velocity is approximately linearly dependent on the applied Lorentz force."--Page [i]
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
"Quantitative information concerning the static pressure associated with moving arcs and the arc velocity as a function of the Lorentz force for arc currents as high as 8000 amperes is given for magnetic-field strengths of 0.64 and 1.28 webers / meter². With the aid of ultra-high-speed photography and rapid-response pressure gages, results revealed that a single abrupt bow shock ahead of the arc did not occur but that a network of many small primary shocks preceded the luminous zone. In the circular channel tests, different gases and air were used at different densities. These tests, in which the arc ran through its own heated wake, indicated that the arc velocity is faster than that in a straight channel and depends on the gas density to the one-half power for the steady-state condition. During arc start-up periods, the arc velocity is approximately linearly dependent on the applied Lorentz force."--Page [i]
Wind-tunnel investigation of a VTOL jet-transport model with powered lift engines in pods at wing midspan or inboard by
Raymond D Vogler(
Book
)
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
Four ejectors mounted in each pod under each wing and powered with compressed air were used to simulate vertical-lift, fan-type jet engines. Data were obtained through an angle-of-attack range to show the effects of engine-pod location, ground-plane movement, flaps, tail size and location, and l0° of sideslip on the aerodynamic characteristics of the model, and the effects of configuration changes on the jet and free-stream interference increments.--P. [i]
1 edition published in 1970 in English and held by 4 WorldCat member libraries worldwide
Four ejectors mounted in each pod under each wing and powered with compressed air were used to simulate vertical-lift, fan-type jet engines. Data were obtained through an angle-of-attack range to show the effects of engine-pod location, ground-plane movement, flaps, tail size and location, and l0° of sideslip on the aerodynamic characteristics of the model, and the effects of configuration changes on the jet and free-stream interference increments.--P. [i]
Metallic materials properties development and standardization (MMPDS) : MMPDS-09 by
United States(
)
7 editions published between 2010 and 2016 in English and held by 0 WorldCat member libraries worldwide
"MMPDS-07 supersedes MMPDS-06 and prior editions of the MMPDS as well as all editions of MIL-HDBK-5, Metallic materials and elemets for aerospace vehicle structures handbook that was maintained by the U.S. Air Force. The last edition, MIL-HDBK-5J, was cancelled by the U.S. Air Force in March 2006. This document contains design information on the mechanical and physical properties of metallic materials and joints commonly used in aircraft and aerospace vehicle structures. All information contained in this Handbook has been reviewed and approved using a standardized process. The development and ongoing maintenance process involves certifying agencies, including the FAA, DoD, and NASA, and major material suppliers and material users worldwide."--Page i
7 editions published between 2010 and 2016 in English and held by 0 WorldCat member libraries worldwide
"MMPDS-07 supersedes MMPDS-06 and prior editions of the MMPDS as well as all editions of MIL-HDBK-5, Metallic materials and elemets for aerospace vehicle structures handbook that was maintained by the U.S. Air Force. The last edition, MIL-HDBK-5J, was cancelled by the U.S. Air Force in March 2006. This document contains design information on the mechanical and physical properties of metallic materials and joints commonly used in aircraft and aerospace vehicle structures. All information contained in this Handbook has been reviewed and approved using a standardized process. The development and ongoing maintenance process involves certifying agencies, including the FAA, DoD, and NASA, and major material suppliers and material users worldwide."--Page i
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Associated Subjects
Absorption Accidents Aerodynamic heating Aerodynamics Aeronautics Aerospace engineering Angle of attack (Aerodynamics) Apollo 13 (Spacecraft) Artificial satellites--Attitude control systems Artificial satellites--Orbits Astronomical photometry Boundary layer control Channels (Structural members) Corrosion and anti-corrosives Electric arc Electric arc--Research Flight Flight testing Interference (Aerodynamics) Jet engines--Air intakes Launch vehicles (Astronautics)--Aerodynamics Launch vehicles (Astronautics)--Stability Lunar excursion module Mach number Military aircraft Moon Newton-Raphson method Orbital transfer (Space flight)--Research Orbiting astronomical observatories Parameter estimation Project Mariner (U.S.) Rockets (Aeronautics)--Models Rockets (Aeronautics)--Vibration Salt Solar radiation simulation Space shuttles--Design and construction Space vehicles--Aerodynamics Spectral sequences (Mathematics) Speed Stability of airplanes, Longitudinal Stress corrosion Structural analysis (Engineering) Telescopes Titanium alloys Titanium alloys--Fatigue Titanium alloys--Heat treatment Titanium alloys--Stress corrosion Transport planes Vacuum arcs Wind tunnels--Testing
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