This report describes the results of a brief computational study using the ABRES Shape Change Code, ASCC-79, to predict the effects of aerodynamic heating on an ablating nose cap configuration for the XM797 high velocity training round. Ablation rates and in-depth thermal response are analyzed for three flight trajectories. Recommendations are made for experimental verification of the computational modeling.
Topics: DTIC Archive, Abbett, M J, BATTELLE COLUMBUS DIV OH, *AERODYNAMIC HEATING, *NOSE CAPS, *TRAINING...
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244
Jul 23, 2010
07/10
by
Hsu, I. S.; Truong, T. K.; Deutsch, L. J.; Satorius, E. H.; Reed, I. S
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It is well known that the Euclidean algorithm or its equivalent, continued fractions, can be used to find the error locator polynomial needed to decode a Reed-Solomon (RS) code. It is shown that this algorithm can be used for both time and transform domain decoding by replacing its initial conditions with the Forney syndromes and the erasure locator polynomial. By this means both the errata locator polynomial and the errate evaluator polynomial can be obtained with the Euclidean algorithm. With...
Topics: AERODYNAMIC HEATING, REENTRY VEHICLES, REFRACTORY MATERIALS, SILICATES, THERMAL CONDUCTIVITY,...
Three sensors to measure the ablation parameters of advanced heat-shield materials during reentry have been developed by the Instrument Research Division of the NASA Langley Research Center. The make wire sensor is designed to measure rate of recession of the char layer interface in a charring ablator, while the light pipe and spring wire sensors are designed to measure material surface recession rates. These sensors have been extensively tested in arc-jet facilities to evaluate their...
Topics: DTIC Archive, LeBel, Peter J., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY...
The objective of this investigation was to isolate those parameters defined as jet mixing effects on afterbody drag in an effort to develop a method of correcting or simulating the effects of jet temperature in wind tunnel experiments. Data used in the investigation were obtained from experiments conducted in the AEDC Aerodynamic Wind Tunnel (1T) with a strut-mounted model at free-stream Mach numbers from 0.6 to 1.2. Integrated afterbody pressure drag coefficient data were acquired for three...
Topics: DTIC Archive, Peters, W L, ARO INC ARNOLD AFS TN, *AERODYNAMIC DRAG, *BOATTAIL AFTERBODIES, *JET...
A series of flight tests was initiated by the Langley Research Center for the purpose of testing ablative cork as a lightweight thermal protection material. These flight tests were conducted aboard NASA flight vehicles in the low-heating-rate environment of the afterbody regions. The test conditions covered a range of altitudes to 482,000 feet and velocities to 17,900 feet per second. The test results show that cork can provide adequate thermal protection for a long-time, low-heating-rate...
Topics: DTIC Archive, Graves, Randolph A., Jr., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA...
The 105mm M774 is a high velocity, long 1/d, fin stabilized projectile. Recent test firings by LCWSL at Yuma Proving Ground, Arizona, revealed that the stabilizing fins were being severely reduced in span due to aerodynamic heating. This brief computational study examines the in-depth temperature response of a thin, swept fin to aerodynamic heating for a series of fin geometries in an effort to determine if a minor design modification can be found which will result in improved performance of...
Topics: DTIC Archive, Sturek, W B, ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD, *AERODYNAMIC...
In 2008 a wind tunnel test program was implemented to update the experimental data available for predicting protuberance heating at supersonic Mach numbers. For this test the Langley Unitary Wind Tunnel was also used. The significant differences for this current test were the advances in the state-of-the-art in model design, fabrication techniques, instrumentation and data acquisition capabilities. This current paper provides a focused discussion of the results of an in depth analysis of unique...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, WIND TUNNEL TESTS, TEMPERATURE...
An analytical investigation of the effects of varying certain material properties on the performance of a charring ablator material has been made. The quantities which are varied are char conductivity, conductivity and specific heat of the uncharred material, heat of pyrolysis, temperature of pyrolysis, and the specific heat of the gases of pyrolysis. The effects of these variations on surface recession, charred-uncharred interface recession, and internal temperature histories are shown. The...
Topics: DTIC Archive, Pittman, Claud M., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY...
Spherically blunted 0.44-radian (25 deg) half-angle conical models coated with elastomeric ablative materials were tested in supersonic arc-heated wind tunnels to evaluate performance of the ablators over a range of conditions typical of lifting entry. Four test conditions were combinations of stagnation-point heat-transfer rates of 2.3 and 4.5 MW/m2 (200 and 400 Btu/ft2-sec) and stagnation pressures of 20 and 2 kN/m2 (0.2 and 0.02 atm). Afterbody values of heat-transfer rate and pressure were...
Topics: DTIC Archive, Chapman, Andrew J., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY...
A technique to provide model pressure and heating rate measurements free from support interference has been developed for the continuous flow, hypersonic wind tunnels (Mach numbers 6, 8, and 10) in the von Karman Gas Dynamics Facility. Data may be obtained from models up to 12 in. in length and 4.5 in. in diameter using onboard telemetry. A description of the test equipment and instrumentation is presented, in addition to base pressure measurements obtained on a 10-deg half-angle cone and base...
Topics: DTIC Archive, Ward, L K, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *FREE FLIGHT MODELS,...
The design of aircraft for sustained operation at hypersonic speeds requires the understanding of aerodynamic heating generated through interfering flow fields. Such interactions not only determine the required level of vehicle thermal protection but also create severe gradients of temperature along skin panels. An extensive experimental program supporting the conceptual design of these vehicles was completed. Experimental results were generated on models illuminating the basic features of both...
Topics: DTIC Archive, Neumann, Richard D, AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH,...
A heated titanium structure flying through a nuclear burst dust cloud may experience aerodynamic heating, kinetic energy heating and oxidation. The rate of heat transfer due to oxidation is examined to determine its contribution relative to other mechanisms of heat transfer, and whether an increase in oxidation heat transfer occurs in the presence of water vapor. The results of the investigation show that heat transfer is dominated by particle kinetic energy conversion and aerodynamic heating...
Topics: DTIC Archive, Sullivan, R J, GENERAL ELECTRIC CO PHILADELPHIA PA RE-ENTRY SYSTEMS DEPT,...
In a performance comparison of reentry vehicles there are a number of important interrelated criteria determining the acceptability of the vehicle. These include the peak deceleration, the limits imposed by atmospheric heating, guidance control and accuracy, and time of descent. A general study has been undertaken which places emphasis on the first two considerations and is based on three vehicle configurations appropriate to both manned and unmanned entry into the earth's atmosphere from high...
Topics: DTIC Archive, Crisp, John D, POLYTECHNIC INST OF BROOKLYN NY DEPT OF AEROSPACE ENGINEERING AND...
Specific tasks included airfoil design; study of airfoil constraints on pullout maneuver; selection of tail airfoils; examination of wing twist; test section instrumentation and layout; and integrated airfoil/heat-exchanger tests. In the course of designing the airfoil, specifically for the APEX test vehicle, extensive studies were made over the Mach and Reynolds number ranges of interest. It is intended to be representative of airfoils required for lightweight aircraft operating at extreme...
Topics: NASA Technical Reports Server (NTRS), AIRFOILS, AERODYNAMIC CONFIGURATIONS, AIRFOIL PROFILES, TAIL...
The report discusses the data needed to perform radiative transfer calculations in nonhydrogenic gases in local thermodynamic equilibrium and presents some approximate methods for computing the radiative energy transferred by spectral lines where the properties of the gas are uniform. The methods currently available for calculating the cross sections of radiative processes are described and compared. An accurate method for calculating the species composition of nitrogen is described and the...
Topics: DTIC Archive, Hunt, Brian L, BROWN UNIV PROVIDENCE RI DIV OF ENGINEERING, *GASES, *THERMAL...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
The development of the phase-change paint technique has provided access to a wealth of information in the form of photographs of heating rate patterns on wind tunnel test models. However, difficulty is experienced in the transformation of the data from the photographs to model coordinates because of the distortion of the model image caused by oblique camera views. This report documents the unique capabilities recently developed at the AEDC-VKF for transformation of the photographic information...
Topics: DTIC Archive, Matthews, R K, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *MANNED...
The effects of strong explosions, particularly nuclear explosions, and their simulation under laboratory and field conditions involve a very broad range of phenomena and parameters such as high temperatures, pressures, electromagnetic energy densities, interaction of energy with materials, shock waves in gases, liquids, and solids, and, in general, events occurring under conditions of a high degree of mechanical, thermal, and radiation stress. The series of Rand Reports of which this is the...
Topics: DTIC Archive, Kassel, Simon, RAND CORP SANTA MONICA CA, *NUCLEAR EXPLOSIONS, ABSTRACTS, AERODYNAMIC...
The Space Shuttle Orbiter has conducted various flight test maneuvers during the Orbital Flight Test Program and beyond in order to establish heating rates at various angles of attack and center of gravity positions. The objective of this project was to investigating the heating effects on the body flap during the entry flight test maneuvers and determine the limits on the flap deflections for an aft center of gravity envelope on the Orbiter. An analysis program available from the Air Force...
Topics: DTIC Archive, Wood,John Robert, AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF...
Data obtained from wind tunnel tests of an .006-scale space shuttle orbiter model in the 18 in. Variable Density Wind Tunnel are presented. The tests, denoted as OH14, were performed to determine transition heating rates using thin skin thermocouples located at various locations on the space shuttle orbiter. The model was tested at M = 8.0 for a range of Reynolds numbers per foot varying from 1.0 to 10.0 million with angles-of-attack from 20 to 35 degrees incremented by 5 degrees.
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, SPACE SHUTTLE ORBITERS, WIND TUNNEL...
A Systems Analysis was completed to determine the feasibility, benefit and risk of an aeroshell aerocapture system for Neptune and to identify technology gaps and technology performance goals. The systems analysis includes the following disciplines: science; mission design; aeroshell configuration; interplanetary navigation analyses; atmosphere modeling; computational fluid dynamics for aerodynamic performance and aeroheating environment; stability analyses; guidance development; atmospheric...
Topics: NASA Technical Reports Server (NTRS), SYSTEMS ANALYSIS, AEROSHELLS, AEROCAPTURE, ATMOSPHERIC...
Heat transfer and distribution tests were conducted on rigid models of the ballute, and drag measurements were obtained on flexible models which were either inflated with ram air or pre-inflated with a bladder. The flexible models were fabricated from a woven stainless steel cloth (Rene' 41 cloth) and impregnated with a silicone polymer to decrease porosity. The Reynolds number range investigated was from 0.36(10exp+6) to 1.80(10exp+6) per foot, and all data were obtained at zero angle of...
Topics: DTIC Archive, Kayser, L D, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN, *RECOVERY,...
The results are given of a series of studies conducted to form the basis for the design of PYE WACKET Feasibility Test Vehicles. Detailed studies (including wind tunnel tests), were conducted in the areas of aerodynamics, control sytem structures and test vehicle performance. All studies were based on sea level flight environment. The complete task is reported in three volumes: Volume I Summary, Volume II -- Aerodynamics, and Volume III -- Configuration and Autopilot/Control. (Author)
Topics: DTIC Archive, GENERAL DYNAMICS CORP POMONA CA POMONADIV, *AUTOMATIC PILOTS, *HYPERSONIC TEST...
Progress in a recently started project aimed at the prediction of transition to turbulence in hypersonic flow is briefly discussed. The prediction of transition to turbulence is a very important issue in the design of space vessels. Two space vehicles currently under investigation, namely the aeroassisted transfer vehicle (AOTV) and the trans-atmospheric vehicle (TAV), suffer from strong aerodynamic heating. This heating is strongly influenced by the boundary layer structure. These aerospace...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, BOUNDARY LAYER FLOW, BOUNDARY LAYER...
The aerodynamic and aerothermal heating at the leeward surfaces of the Apollo capsule flying high angle of attack were found difficult to simulate using conventional tools. Due to the large subsonic region in the proximity of the shoulder of the base shield, correlation-based tools were found to be inadequate. CFD tools are too time consuming for conceptual design purposes, and cannot account for the transient effects of material response such as wall temperature and blowing. An accurate and...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, INVISCID FLOW, THERMAL PROTECTION,...
186
186
Jul 26, 2010
07/10
by
Baldwin, Barrett S., Jr
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No Abstract Available
Topics: ABLATION, MASS TRANSFER, NONLINEAR EQUATIONS, THERMAL BOUNDARY LAYER, AERODYNAMIC HEAT TRANSFER,...
The development of the thermal protection system for the Solid Rocket Booster is reported. Tests and analytical efforts were conducted and new problems are continually attacked and solved. During the first six Shuttle flights it was necessary to make a final thermal assessment of the TPS and structural systems temperatures. The thermal assessments were made and are compared with post flight data.
Topics: NASA Technical Reports Server (NTRS), AEROTHERMODYNAMICS, BOOSTER ROCKET ENGINES, HEAT SHIELDING,...
Topics: DTIC Archive, Zamula,G N, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO, *FOREIGN TECHNOLOGY,...
One of the problem areas associated with the supersonic carriage of external stores is concerned with temperature restrictions on critical components. Theoretical calculations were used to guide a two-phase experimental program which included both flight and wind tunnel testing. Flight heat-transfer measurements were obtained on a pylon-mounted BDU-12 at flight conditions of 40,000 ft and Mach numbers up to 2.5. The wind tunnel tests of a 1/15-scale model included both pressure and heat...
Topics: DTIC Archive, Matthews, R K, ARO INC ARNOLD AFS TN, *EXTERNAL STORES, AERODYNAMIC HEATING, HEAT...
A broad base of thermocouple and phase change paint data was assembled and correlated to the nominal design 14414.1 and proposed STS-1 (first flight of the space transportation system) entry trajectories. Averaged data from phase change paint tests compared favorably with thermocouple data for predicting heating rates. Laminar and turbulent radiation equilibrium heating rates were computed on the lower surface of the Shuttle orbiter for both trajectories, and the lower surface center line...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, ATMOSPHERIC ENTRY, LEADING EDGE SWEEP,...
The objective of this MTP is to determine the effect of high temperature and temperature changes, resulting from aerodynamic heating, on the missile skin, structure, and interior components using laboratory methods. Such information is used to determine the adequacy of equipment to meet specified requirements such as the ability to withstand the aerodynamic heating associated with flying a specified trajectory. (Author)
Topics: DTIC Archive, ARMY TEST AND EVALUATION COMMAND ABERDEEN PROVING GROUND MD, *GUIDED MISSILES,...
Wind tunnel tests of windshield material intended for use on supersonic aircraft were conducted in the von Karman Facility Hypersonic Wind Tunnel B at a free-stream Mach number of 6 and tunnel stilling chamber conditions of 146 psia and 495 F. The wedge technique was used to provide a local Mach number of 2.5 over the windshield specimen. Selected results are presented to illustrate the test techniques and typical data obtained.
Topics: DTIC Archive, Stallings, D W, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AIRCRAFT...
A major modification of the refrigeration plant and heat exchanger at the NASA Glenn Icing Research Tunnel (IRT) occurred in autumn of 2011. It is standard practice at NASA Glenn to perform a full aero-thermal calibration of the test section of a wind tunnel facility upon completion of major modifications. This paper will discuss the tools and techniques used to complete an aero-thermal calibration of the IRT and the results that were acquired. The goal of this test entry was to complete a flow...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, ICE FORMATION, WIND TUNNEL CALIBRATION,...
This paper describes arcjet testing and analysis that has successfully demonstrated the viability of three dimensional woven carbon cloth for dual use in the Adaptive Deployable Entry Placement Technology (ADEPT). ADEPT is an umbrella-like entry system that is folded for stowage in the launch vehicle s shroud and deployed in space prior to reaching the atmospheric interface. A key feature of the ADEPT concept is its lower ballistic coefficient for delivery of a given payload than those for...
Topics: NASA Technical Reports Server (NTRS), ATMOSPHERIC ENTRY, DECELERATION, THERMAL PROTECTION, CARBON...
During the recent entry of the Mars Science Laboratory (MSL), the heat shield was equipped with thermocouple stacks to measure in-depth heating of the thermal protection system (TPS). When only convective heating was considered, the derived heat flux from gauges in the stagnation region was found to be underpredicted by as much as 17 W/sq cm, which is significant compared to the peak heating of 32 W/sq cm. In order to quantify the contribution of radiative heating phenomena to the discrepancy,...
Topics: NASA Technical Reports Server (NTRS), MARS SCIENCE LABORATORY, ATMOSPHERIC ENTRY, AERODYNAMIC...
The trio-layer explicit difference scheme which is added artificial viscosity item is found by using filteration in the computation of ablated nosetip shape. The scheme is of first order accuracy in regions where shape change is wavy and second order accuracy in regions where is Smooth. Numerical experiments show that the scheme developed is effective. (kr)
Topics: DTIC Archive, Maozhao, Yang, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *SHAPE, *ABLATION,...
Current high velocity kinetic energy penetrator shell use fins made of aluminum to provide aerodynamic stability. Due to the high velocity of the shell and the requirement to keep the drag of the shell to a minimum, these aluminum fins are very thin, a maximum thickness of 4 mm is typical. The thin cross section of the fin and the low melting point of aluminum combine to create a critical design problem. If the fins do not have sufficient mass to absorb and conduct away the high heat loads...
Topics: DTIC Archive, Sturek, Walter B, ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD, *FINS,...
The main objective of this project was to determine if heat pipe technology could be used to cool the portion of a missile's control surfaces heated by hot exhaust gas. The goal was to reduce the heat conducted into the body of the missile and its actuation rod. The small portion of the airfoil near the missile body heated by the exhaust plume is to be cooled by rejecting the heat to the large portion of the fin moving through ambient air. It is a ground-to-ground missile with a maximum speed...
Topics: DTIC Archive, Donovan, Brian D., AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH, *COOLING, *GUIDED...
The tumbling motion of aerodynamically stable bodies entering planetary atmospheres is analyzed considering that the tumbling, its arrest, and the subsequent oscillatory motion are governed by the equation for the fifth Painleve' transcendent. Results based on the asymptotic behavior of the transcendent are applied to study (1) the oscillatory behavior of planetary probe vehicles in relation to aerodynamic heating and loads and (2) the dynamic behavior of the Australian tektites on entering the...
Topics: DTIC Archive, Tobak, Murray, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...
The flow field about the nose section of a hypervelocity test sled is computed using computational fluid dynamics. The numerical model of the test sled corresponds to the Nike O/U narrow gage sled used in the upgrade program at the High Speed Test Track facility, Holloman Air Force Base, New Mexico. The high temperatures and pressures resulting from the aerodynamic heating and loading affect the sled structure and the performance of the vehicle. The sled transitions from an air environment to a...
Topics: DTIC Archive, Lofthouse, Andrew J, AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF...
Topics: DTIC Archive, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, *AERODYNAMIC LOADING,...
A two-pronged effort in aerodynamic heating was performed. The first, and more basic requirement, was an experimental analysis of heating incurred by conventional weapons. The second effort, which was related to the first, concerned investigating heat transfer mechanisms found in and around weapons. Some of the isolated areas to be investigated were: thermal contact conductance, convective heat transfer coefficient review and analysis, thermal control methods as applied to weapons, and thermal...
Topics: DTIC Archive, Maples, Dupree, LOUISIANA STATE UNIV BATON ROUGE DEPT OF MECHANICAL ENGINEERING,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
The objective of this investigation was to isolate those parameters defined as jet mixing effects on afterbody drag in an effort to develop a method of correcting or simulating the effects of jet temperature in wind tunnel experiments. Data used in the investigation were obtained from experiments conducted in the AEDC Aerodynamic Wind Tunnel (1T) with a strut-mounted model at free-stream Mach numbers from 0.6 to 1.2. Integrated afterbody pressure drag coefficient data were acquired for three...
Topics: DTIC Archive, Peters, W L, ARO INC ARNOLD AFS TN, *AERODYNAMIC DRAG, *BOATTAIL AFTERBODIES, *JET...
The low temperature performance of antimisting kerosene (AMK) in airframe fuel systems and in certain fuel system components was studied and compared to Jet A fuel. Water vapor ingested into fuel tanks during simulation of repeated descents through clouds and rain had little effect on AMK. AMK retained antimisting properties during exposure to severe environmental flight simulations. Jet pump and boost pump operation had no discernable effect on AMK flammability. Jet pump performance with AMK...
Topics: DTIC Archive, McConnell,P M, BOEING MILITARY AIRPLANE CO SEATTLE WA, *FUEL TANKS, *FUEL PUMPS, *JET...
Calculations were made of the equilibrium radiation emitted from air over a range of temperatures from 2,000 K to 23,000 K and over a density range from 10 to the -6th power to 10 atmospheres. The calculations are presented in graphical form and are in terms of the radiation flux emitted from one side of infinite slabs of finite thickness. The molecular band systems were calculated using a smeared rotational model, and are carried out for a slab thickness of 1 cm. Atomic line and free-bound...
Topics: DTIC Archive, Allen, Richard A, AVCO EVERETT RESEARCH LAB INC EVERETT MA, *DIATOMIC MOLECULES,...
An approximate solution is presented for determining transient temperature distributions and ablation rates for solid spheres of low thermal conductivity and constant thermal properties, subjected to point symmetric aerodynamic heat inputs. A short time solution for the temperature which is valid prior to ablation, is developed by use of Laplace transforms. The ablation solution is derived by approximation of the radial temperature profile by an exponential function and utilization of the heat...
Topics: DTIC Archive, POLYTECHNIC INST OF BROOKLYN NY, *ABLATION, *AERODYNAMIC HEATING, *HEAT SHIELDS,...
This report presents heat transfer and pressure distributions for hypersonic flows ahead of ramps, over expansion corners, and past fin-plate combinations. Two basic models were used for these experiments: 1) a flat plate with a full span ramp (trailing-edge flap) on one surface and an expansion corner on the other, and 2) a flat plate with wedge shaped fins mounted on the upper surface and an expansion corner on the lower surface. Both sharp leading edge models were tested in the Grumman...
Topics: DTIC Archive, GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY, *HEAT TRANSFER, *AEROTHERMODYNAMICS,...
A brief sampling of test results obtained during early operation of the range is presented. Among these are: (1) results of sphere drag measurements over the Reynolds number range 3 Re sub 2 10 to the 6th power; (2) results of the measurements of flow transition locations and wake velocities behind spheres, as obtained through the use of a 35-GHz Doppler radar system; (3) results of measurements of electron densities in the wakes of spheres, as obtained using r-f cavity and microwave...
Topics: DTIC Archive, Clemens, P L, ARO INC ARNOLD AFS TN, *HYPERVELOCITY GUNS, *HYPERVELOCITY PROJECTILES,...
The feasibility of inerting the ullage spaces in aircraft fuel tanks via a catalytic combustion technique is evaluated. The technique utilizes nitrogen from the surrounding atmosphere as the principal component of the ballast gas admitted to the tanks. Free oxygen is reduced to safe levels by means of catalyzed reaction with a small fraction of the aircraft fuel. Before the combustion gases are admitted to the fuel tanks, the water content is reduced by condensation and by contact with a...
Topics: DTIC Archive, Wainright, Ralph B., AMERICAN CYANAMID CO STAMFORD CT CENTRAL RESEARCH DIV, *CHEMICAL...
