Configuration concepts are presented which have high lift-to-drag ratios and maneuverability achievable by relieving constraints due to carriage, propulsion and subsystem integration. Noncircular body, lifting body, blended wing-body, wing-body and favorable interference concepts are developed using aerodynamic design criteria derived for climb-cruise-intercept missions. The Hypersonic Arbitrary Body Program (HABP) is evaluated for predicting aerodynamic characteristics. Comparisons of wind...

Topics: DTIC Archive, Krieger,Robert, MCDONNELL DOUGLAS ASTRONAUTICS CO-ST LOUIS MO, *AIR TO SURFACE...

Configuration concepts are presented which have high lift-to-drag ratios and maneuverability achievable by relieving constraints due to carriage, propulsion and subsystem integration. Noncircular body, lifting body, blended wing-body, wing-body and favorable interference concepts are developed using aerodynamic design criteria derived for climb-cruise-intercept missions. The Hypersonic Arbitrary Body Program (HABP) is evaluated for predicting aerodynamic characteristics. Comparisons of wind...

Topics: DTIC Archive, Krieger,Robert, MCDONNELL DOUGLAS ASTRONAUTICS CO-ST LOUIS MO, *AIR TO SURFACE...

Configuration concepts are presented which have high lift-to-drag ratios and maneuverability achievable by relieving constraints due to carriage, propulsion and subsystem integration. Noncircular body, lifting body, blended wing-body, wing-body and favorable interference concepts are developed using aerodynamic design criteria derived for climb-cruise-intercept missions. The Hypersonic Arbitrary Body Program (HABP) is evaluated for predicting aerodynamic characteristics. Comparisons of wind...

Topics: DTIC Archive, Krieger,Robert, MCDONNELL DOUGLAS ASTRONAUTICS CO-ST LOUIS MO, *AIR TO SURFACE...

This report presents an extensive bibliography of experimental ground and flight test data primarily for strategic maneuvering reentry vehicles (MarV) . The overall objective of the MAT program is to assess and extend the current state-of-the-art of technology for predicting MaRV aerothermal performance for current and next generation vehicles in flight regimes characteristic of future mission requirements. The specific objective of this data search and review task was to: (1) assemble a...

Topics: DTIC Archive, Martellucci, A., SCIENCE APPLICATIONS INC WAYNE PA, *FLIGHT TESTING, *EXPERIMENTAL...

Contents: Nonlinear waves and wave Resistance; Some Free-Surface Phenomena Around Ships to be Challenged by Numerical Analysis; Free Surface Potential Flow Computation Using a Finite Element Method: Numerical Explanation of Nonlinear Nondispersive Waves around Bow; Numerical Studies of the Neumann- Kelvin Problem for a Two-Dimensional Semi-Submerged Body; Nonlinear Waves Behind an Accelerated Transom Stern; Transient and Nonlinear Solutions to Body-Wave and Water-Wave Problem; Applications of a...

Topics: DTIC Archive, Dern, Jean-Claude, DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA...

This work continues previous inflow work in that it extends it to the flow below the disk both in and out of the shed wake. In addition, the work utilizes that new inflow model to offer optimum power states for rotors in hover and in forward flight.

Topics: DTIC Archive, WASHINGTON UNIV ST LOUIS MO SCHOOL OF ENGINEERING AND APPLIED SCIENCE, *FLIGHT,...

455
455

Dec 8, 2009
12/09

by
NASA

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The M2-F2 lifting body returns from a research flight at the NASA Dryden Flight Research Center, Edwards, California, with an F-104 flying chase.

Topics: Lifting Bodies, Top 20 Dryden Aircraft, Where -- Dryden Flight Research Center (DFRC), Where --...

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000150.html

625
625

Dec 8, 2009
12/09

by
NASA

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The M2-F2 lifting body aircraft crash landed on Rogers Dry Lakebed at the Dryden Flight Research Center at Edwards, California on May 10, 1967.

Topics: Lifting Bodies, Top 20 Dryden Aircraft, Where -- Dryden Flight Research Center (DFRC), Where --...

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000089.html

A new incompressible lifting-surface theory is developed for thin rectangular wings. The solution requires the downwash equation to be in the form of Cauchy-type integrals. Lan's method is employed for the chordwise integrals since it properly accounts for the leading-edge singularity, Cauchy singularity and Kutta condition. The Cauchy singularity in the spanwise integral is also accounted for by using the midpoint trapezoidal rule and theory of Chebychev polynomials. The resulting matrix...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, CAUCHY INTEGRAL FORMULA, LIFTING...

The unsteady aerodynamic lifting surface theory, the Doublet Lattice method, with experimental steady and unsteady pressure measurements of a high aspect ratio supercritical wing model at a Mach number of 0.78 were compared. The steady pressure data comparisons were made for incremental changes in angle of attack and control surface deflection. The unsteady pressure data comparisons were made at set angle of attack positions with oscillating control surface deflections. Significant viscous and...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, HIGH ASPECT RATIO, LATTICES (MATHEMATICS),...

NASA is currently studying a personnel launch system (PLS) approach to help satisfy the crew rotation requirements for the Space Station Freedom. Several concepts from low L/D capsules to lifting body vehicles are being examined in a series of studies as a potential augmentation to the Space Shuttle launch system. Rockwell International Corporation, under contract to NASA, analyzed a lifting body concept to determine whether the lifting body class of vehicles is appropriate for the PLS...

Topics: NASA Technical Reports Server (NTRS), LAUNCHING, LIFTING BODIES, SPACE SHUTTLES, SPACE STATION...

92
92

Dec 7, 2009
12/09

by
NASA

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The M2-F1 lifting body aircraft rests on the sun-baked floor of a dry lake bed located out in the Mojave Desert at the Dryden Flight Research Center, California. Pilot Chuck Yeager, seated in the cockpit of the M2- F1, talks with fellow pilots from left to right Milt Thompson, Don Malick and Bruce Peterson. All three flew the lifting body in several flights. The vehicle later suffered a mishap when Peterson was landing it--the oil in the landing gear hydraulics was not suitable for cold...

Topics: Lifting Bodies, What -- Sun, Where -- Dryden Flight Research Center (DFRC), Where -- California

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000082.html

619
619

Jul 12, 2010
07/10

by
Blackwell, J. A., Jr.; Hinson, B. L

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An advanced rotor airfoil, designed utilizing supercritical airfoil technology and advanced design and analysis methodology is described. The airfoil was designed subject to stringent aerodynamic design criteria for improving the performance over the entire rotor operating regime. The design criteria are discussed. The design was accomplished using a physical plane, viscous, transonic inverse design procedure, and a constrained function minimization technique for optimizing the airfoil leading...

Topics: KUTTA-JOUKOWSKI CONDITION, MOMENTS OF INERTIA, PRESSURE DISTRIBUTION, VELOCITY DISTRIBUTION, LIFT...

258
258

Jun 13, 2011
06/11

by
Buchner, Stephen; McMorrow, Dal

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This viewgraph presentation reviews the challenges for the pulsed laser in the following categories: 1. Metal 2. Package 3. Scaling 4. Exotic materials 5. Novel devices 6. Equipment

Topics: FREE FLIGHT, PRESSURE, FLIGHT CONDITIONS, INTERNATIONAL SPACE STATION, NOSE FINS, SIDESLIP, YAW,...

215
215

May 31, 2011
05/11

by
Harris, Jerry D.; Anglin, Emily J.; Hepp, Aloysius F.; Bailey, Sheila G.; Scheiman, David A.; Castro, Stephenie L

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Recent advances in nanocrystalline dye-sensitized solar cells has lead NASA to investigate the potential of these devices for space power generation, Reported here is the first space environment characterization of these type of photovoltaic devices. Cells containing liquid electrolytes were exposed to simulated low-earth orbit conditions and their performance evaluated. All cells were characterized under simulated air mass zero (AMO) illumination. Complete cells were exposed to pressures less...

Topics: BASE FLOW, VORTICES, WAKES, LAUNCH VEHICLES, DRAG REDUCTION, REENTRY VEHICLES, VISCOUS DRAG,...

542
542

Jun 9, 2011
06/11

by
Singleton, Jeffrey D.; Yeager, William T., Jr

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An investigation into the effects of aerodynamic and aeroelastic scaling parameters on model scale helicopter rotors has been conducted in the NASA Langley Transonic Dynamics Tunnel. The effect of varying Reynolds number, blade Lock number, and structural elasticity on rotor performance has been studied and the performance results are discussed herein for two different rotor blade sets at two rotor advance ratios. One set of rotor blades were rigid and the other set of blades were dynamically...

Topics: HYPERSONIC FLOW, SURFACE TEMPERATURE, CATALYTIC ACTIVITY, SUPERSONIC FLOW, COMPUTATIONAL FLUID...

328
328

May 28, 2011
05/11

by
Wu, K. Chauncey; Lepsch, Roger A., Jr

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Dry weights for single-stage launch vehicles that incorporate nontangent, developed contour bulkheads are estimated and compared to a baseline vehicle with 1.414 aspect ratio ellipsoidal bulkheads. Weights, volumes, and heights of optimized bulkhead designs are computed using a preliminary design bulkhead analysis code. The dry weights of vehicles that incorporate the optimized bulkheads are predicted using a vehicle weights and sizing code. Two optimization approaches are employed. A...

Topics: AERODYNAMIC COEFFICIENTS, ANGLE OF ATTACK, PLANFORMS, VORTEX SHEDDING, LIFTING BODIES, RETRACTABLE...

Topics: DTIC Archive, Breyer,Siegfried, NAVAL INTELLIGENCE SUPPORT CENTER WASHINGTON DC TRANSLATION DIV,...

Image L63-7161is available as an electronic file from the photo lab. See URL. -- Photographed on 09/25/1963. -- PARD lifting body.

Topic: LIFTING BODIES. -- HL-10 REENTRY VEHICLE

The viscous shock-layer equations for three-dimensional hypersonic flows of a perfect gas or equilibrium air over lifting bodies at high angles of attack have been developed. For the complex three-dimensional reentry vehicle geometries of interest, the resulting equations are written in a nonorthogonal, body-oriented coordinate system, and the three velocity components are defined in the nonorthogonal coordinate directions. Since the viscous shock-layer governing equations are parabolic in both...

Topics: DTIC Archive, Szema,K Y, VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND...

Photographed on: 04/28/92. -- L-92-5124: Top view of Langley HL-20 Lifting Body. -- Photograph published in Winds of Change, 75th Anniversary NASA publication (page viii), by James Schultz.

Topic: REENTRY VEHICLES. -- LIFTING BODIES. --

614
614

Jun 21, 2010
06/10

by
Teyfel, V. G

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Optical and radiometric observations of planet Jupiter atmosphere

Topics: AERODYNAMIC CHARACTERISTICS, WIND TUNNEL STABILITY TESTS, X-24 AIRCRAFT, LIFT DRAG RATIO, LIFTING...

122
122

Dec 7, 2009
12/09

by
NASA

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Full scale model of the HL-10 lifting body mounted in the 30 x 60 Full Scale Tunnel at Langley.

Topics: Wind Tunnels-Interior, Lifting Bodies

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-001894.html

Photographed on: 04/28/92. -- L-92-5124: Top view of Langley HL-20 Lifting Body. -- Photograph published in Winds of Change, 75th Anniversary NASA publication (page viii), by James Schultz.

Topic: REENTRY VEHICLES. -- LIFTING BODIES. --

The Douglas Neumann Cascade Program has been rewritten so that it can analyze circular cascades with inward or outward radial flow directions, in addition to linear cascades for which it was originally developed. A solution for circular cascades is obtained by employing a conformal transformation which maps the circular cascade into a linear cascade. The capability available in the original program of analyzing multiple cascades has been preserved and can also be applied to circular cascades....

Topics: DTIC Archive, Yocum,A M, PENNSYLVANIA STATE UNIV UNIVERSITY PARK APPLIED RESEARCH LAB, *COMPUTER...

Configuration concepts are presented which have high lift-to-drag ratios and maneuverability achievable by relieving constraints due to carriage, propulsion and subsystem integration. Noncircular body, lifting body, blended wing-body, wing-body and favorable interference concepts are developed using aerodynamic design criteria derived for climb-cruise-intercept missions. The Hypersonic Arbitrary Body Program (HABP) is evaluated for predicting aerodynamic characteristics. Comparisons of wind...

Topics: DTIC Archive, Krieger,Robert, MCDONNELL DOUGLAS ASTRONAUTICS CO-ST LOUIS MO, *AIR TO SURFACE...

The Army is planning to upgrade the existing Main Battle Tank. Concern was expressed whether the current lifting configuration was strong enough to support the additional load of this upgrade. A non-linear finite element analysis of four different configurations was done to determine whether the front lifting eye was strong enough. The analysis indicates that with a spreader bar incorporated in the lifting harness, the eye is strong enough. Without such a spreader bar, a detailed comparison...

Topics: DTIC Archive, Lambrecht, Stephen, TACOM RESEARCH DEVELOPMENT AND ENGINEERING CENTER WARREN MI,...

Aerodynamic flutter and a re-written computer program for its study are discussed. Data cover: (1) lifting surface theory with boundary layer, (2) incompressible, two dimensional, unsteady flow with control surfaces, (3) improved unsteady theory, (4) combined transonic airfoil thickness and shear layer thickness effects, and (5) bending-torsion flutter calculations.

Topics: NASA Technical Reports Server (NTRS), AIRFOILS, BOUNDARY LAYERS, COMPUTER PROGRAMS, LIFTING BODIES,...

The application of the vortex lattice method to problems not usually dealt with by this technique is considered. It is shown that if the discrete vortex lattice is considered as an approximation to surface-distributed vorticity, then the concept of the generalized principal part of an integral yields a residual term to the vortex-induced velocity that renders the vortex lattice method valid for supersonic flow. Special schemes for simulating non-zero thickness lifting surfaces and fusiform...

Topics: NASA Technical Reports Server (NTRS), APPLICATIONS OF MATHEMATICS, LATTICES (MATHEMATICS),...

A nonlinear, nonplanar three dimensional jet flap analysis, applicable to the ground effect problem, is presented. Lifting surface methodology is developed for a wing with arbitrary planform operating in an inviscid and incompressible fluid. The classical, infintely thin jet flap model is employed to simulate power induced effects. An iterative solution procedure is applied within the analysis to successively approximate the jet shape until a converged solution is obtained which closely...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, GROUND EFFECT (AERODYNAMICS),...

Flight derived longitudinal and lateral-directional stability and control derivatives were compared to wind-tunnel derived values. As a result of these comparisons, boundaries representing the uncertainties that could be expected from wind-tunnel predictions were established. These boundaries provide a useful guide for control system sensitivity studies prior to flight. The primary application for this data was the space shuttle, and as a result the configurations included in the study were...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, DATA CORRELATION, DELTA WINGS,...

The problem of the determination of the subcritical aeroelastic response and flutter instability of nonlinear two-dimensional lifting surfaces in an incompressible flow-field via Volterra series approach is addressed. The related aeroelastic governing equations are based upon the inclusion of structural nonlinearities, of the linear unsteady aerodynamics and consideration of an arbitrary time-dependent external pressure pulse. Unsteady aeroelastic nonlinear kernels are determined, and based on...

Topics: NASA Technical Reports Server (NTRS), TWO DIMENSIONAL MODELS, LIFTING BODIES, AEROELASTICITY,...

A method and associated system for multi-disciplinary optimization of various parameters associated with a space vehicle that experiences aerocapture and atmospheric entry in a specified atmosphere. In one embodiment, simultaneous maximization of a ratio of landed payload to vehicle atmospheric entry mass, maximization of fluid flow distance before flow separation from vehicle, and minimization of heat transfer to the vehicle are performed with respect to vehicle surface geometric parameters,...

Topics: NASA Technical Reports Server (NTRS), OPTIMIZATION, BLUNT BODIES, SHAPES, SPACECRAFT, AEROSHELLS,...

NASA has created the Environmentally Responsible Aviation Project to explore and document the feasibility, benefits, and technical risk of advanced vehicle configurations and enabling technologies that will reduce the impact of aviation on the environment. A critical aspect of this pursuit is the development of a lighter, more robust airframe that will enable the introduction of unconventional aircraft configurations that have higher lift-to-drag ratios, reduced drag, and lower community noise....

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, STRUCTURAL WEIGHT, STRUCTURAL...

248
248

Dec 8, 2009
12/09

by
NASA

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The X-24A lifting-body research aircraft begins its rocket-powered flight after being launched from the wing of NASA's B-52 mothership during a 1970 research flight. NASA B-52, Tail Number 008, is an air launch carrier aircraft, "mothership," as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a "B" model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the...

Topics: X-Series Aircraft, Unique Aircraft, Lifting Bodies, Top 20 Dryden Aircraft, What -- Pegasus, What...

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000205.html

Topics: Radio Program, European Space Agency, Shipping, Personal finance, Science and technology in Europe,...

124
124

Dec 8, 2009
12/09

by
NASA/Tony Landis

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The X-38's blue and white parafoil spreads out in front of the research vehicle as it sits on a lakebed near the Dryden Flight Research Center after a March 2000 test flight. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station.

Topics: X-Series Aircraft, International Space Station, Lifting Bodies, What -- International Space Station...

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000226.html

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140

Dec 7, 2009
12/09

by
NASA

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With pilot Bruce Peterson at the controls, the HL-10 lifting body aircraft makes a successful landing on Rogers Dry Lake at the Dryden Flight Research Center at Edwards, California.

Topics: Lifting Bodies, Top 20 Dryden Aircraft, Where -- Dryden Flight Research Center (DFRC), Where --...

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000086.html

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144

Dec 7, 2009
12/09

by
NASA

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The M2-F1 lifting body is seen here being towed behind a C-47 at the Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric re-entry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle.

Topics: Lifting Bodies, Top 20 Dryden Aircraft, Where -- Dryden Flight Research Center (DFRC), Where --...

Source: http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-000097.html

The program was designed to provide solutions of engineering accuracy for determining the aerodynamic loads on single- or multiple-lifting-surface configurations that represent vehicles in subsonic flight, e.g., wings, wing-tail, wing-canard, lifting bodies, etc. The preparation is described of the input data, associated input arrangement, and the output format for the program data, including specification of the various operational details of the program such as array sizes, tape numbers...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, COMPUTER PROGRAMS, LIFTING BODIES, VORTEX...

A user's manual is presented for a computer program which calculates inviscid flow about lifting configurations in the free-stream Mach-number range from zero to low supersonic. Angles of attack of the order of the configuration thickness-length ratio and less can be calculated. An approximate formulation was used which accounts for shock waves, leading-edge separation and wind-tunnel wall effects.

Topics: NASA Technical Reports Server (NTRS), BODY-WING CONFIGURATIONS, LIFTING BODIES, TRANSONIC FLOW,...

A logarithmic-singularity correction factor is derived for use in kernel function methods associated with Multhopp's subsonic lifting-surface theory. Because of the form of the factor, a relation was formulated between the numbers of chordwise and spanwise control points needed for good accuracy. This formulation is developed and discussed. Numerical results are given to show the improvement of the computation with the new correction factor.

Topics: NASA Technical Reports Server (NTRS), KERNEL FUNCTIONS, LIFTING BODIES, LOGARITHMS, SINGULARITY...

Application of the Kutta-Joukowski theorem to the relationship between airfoil lift and circulation is described. A number of formulas concerning the conduct of vortex systems derived from the theorem are presented. The application of this line of reasoning to several problems of airfoil theory and the observed relations are discussed.

Topics: NASA Technical Reports Server (NTRS), KUTTA-JOUKOWSKI CONDITION, LIFT DEVICES, LIFTING BODIES,...

Equations of motion were derived for the three dimensional flight of a lifting vehicles, taking into consideration all the main effects of different forces acting on a vehicle at orbital speeds. A set of equations was formulated which are valid for both the flight with lift modulation inside a planetary atmosphere and the Keplerian motion in the vacuum. The equations are independent of the physical characteristics of the vehicle. The only parameters involved are the maximum lift to drag ratio...

Topics: NASA Technical Reports Server (NTRS), HYPERSONIC FLIGHT, LIFTING BODIES, ORBITAL VELOCITY,...

A computational technique is developed that is suitable for performing preliminary design aeroelastic and structural dynamic analyses of large aspect ratio lifting surfaces. The method proves to be quite general and can be adapted to solving various two point boundary value problems. The solution method, which is applicable to both fixed and rotating wing configurations, is based upon a formulation of the structural equilibrium equations in terms of a hybrid state vector containing generalized...

Topics: NASA Technical Reports Server (NTRS), AEROELASTICITY, ANISOTROPY, BOUNDARY VALUE PROBLEMS, DYNAMIC...

The HL-20 is proposed as a possible future manned spacecraft. The configuration consists of a low-aspect-ratio body with a flat undersurface. Three fins (a small centerline fin and two outboard (tip) fins set at a dihedral angle of 50 deg) are mounted on the aft body. The control system consists of elevon surfaces on the outboard fins, a set of four body flaps on the upper and lower aft body, and an all-movable center fin. Both the elevons and body flaps were capable of trimming the model to...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AERODYNAMIC STABILITY, ELEVONS,...

Current reentry vehicle designs exhibit large amounts of base drag due to large base areas. These large base areas can arise from the integration of the propulsion system (X-33) or control surface placement (X-38). Large base drag limits the vehicle's cross-range capability and causes a large glide-slope angle. Fortunately, there appears to be a possible means of lowering the base drag on these vehicles. Based on early work on the subsonic aerodynamics of lifting bodies, it appears that the...

Topics: NASA Technical Reports Server (NTRS), BASE FLOW, DRAG REDUCTION, REENTRY VEHICLES, VISCOUS DRAG,...

In his remarkable memoir Runway to Orbit, Dr. Kenneth W. Iliff - the recently retired Chief Scientist of the NASA Dryden Flight Research Center- tells a highly personal, yet a highly persuasive account of the last forty years of American aeronautical research. His interpretation of events commands respect, because over these years he has played pivotal roles in many of the most important American aeronautics and spaceflight endeavors. Moreover, his narrative covers much of the second half of...

Topics: NASA Technical Reports Server (NTRS), SPACE TRANSPORTATION SYSTEM FLIGHTS, SPACE FLIGHT, POLICIES,...

Analytical procedures and experimental techniques were developed to improve the capability to design advanced high speed propellers. Some results from the propeller lifting line and lifting surface aerodynamic analysis codes are compared with propeller force data, probe data and laser velocimeter data. In general, the code comparisons with data indicate good qualitative agreement. A rotating propeller force balance demonstrated good accuracy and reduced test time by 50 percent. Results from...

Topics: NASA Technical Reports Server (NTRS), DESIGN ANALYSIS, LIFTING BODIES, PROPELLERS, BOUNDARY LAYER...

A proposed manned spacecraft design, designated the HL-20, has been under investigation at Langley Research Center. Included in that investigation are flight control design and flying qualities studies utilizing a man-in-the-loop real-time simulator. This report documents the current real-time simulation model of the HL-20 lifting body vehicle, known as version 2.0, presently in use at NASA Langley Research Center. Included are data on vehicle aerodynamics, inertias, geometries, guidance and...

Topics: NASA Technical Reports Server (NTRS), COMPUTERIZED SIMULATION, CONTROL THEORY, FLIGHT...