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  • Other Sources  (540)
  • AERODYNAMICS  (365)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (175)
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  • 2015-2019
  • 1980-1984  (509)
  • 1945-1949  (31)
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  • 1980  (509)
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  • 2015-2019
  • 1980-1984  (509)
  • 1945-1949  (31)
  • 1925-1929
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  • 1
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    Use of multiblade sensors for on-line rotor tip-path plane estimation (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Techniques are investigated for on-line estimation of rotor states in the nonrotating frame from multiple, simultaneous measurements in the rotating frame. The multiblade coordinate transformation is first applied to transform both flapping and flapping rate measurements into the nonrotating frame. The 'observer' approach is then used to generate algorithms for estimating tip-path plane rate and attitude from transformed flapping and flapping rate measurements. A numerical evaluation using simulated measurements is conducted to evaluate the performance of the algorithms and recommendations are made.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: American Helicopter Society; vol. 25
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  • 2
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    Three-layer interactive method for computing supersonic laminar separated flows (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An interactive model for numerical computation of complicated two-dimensional flowfields including regions of reversed flow is proposed. The present approach is one of dividing the flowfield into three regions, in each of which a simplified mathematical model is applied: (1) outer, supersonic flow for which the full potential equation (hyperbolic) is used; (2) viscous, laminar layer in which the compressible boundary-layer model (parabolic) is used; and (3) recirculating flow modeled by the incompressible Navier-Stokes equations (elliptic). For matching of the numerical solutions in the three layers, two interaction models are developed: one for pressure interaction, the other for interaction between the shear layer and the recirculating flow. The uniform solution for the whole flowfield is then obtained by iteration of the local solutions under the constraints imposed by matching. The three-layer interactive model is used for solution of the flowfield past an asymmetric cavity. The method is shown to be capable of dealing with backflow without encountering problems at separation, characteristic to the boundary-layer approach.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; Nov. 198
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  • 3
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    The promise of multicyclic control (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The rough ride a helicopter endures is known to be self-generated. This roughness results in fatiguing blade loads and vibration which can be eliminated or greatly reduced by multicyclic control. Rotor performance may also be improved. Several types of rotors which have employed multicyclic control are reviewed and compared. Their differences are highlighted and their potential advantages and disadvantages are discussed. The flow field these rotors must operate in is discussed, and it is shown that simultaneous elimination of vibration and oscillatory blade loads is not an inherent solution to the roughness problem. The use of rotor blades and energy absorbers is proposed. Input-output relations are considered and a gain control for ROMULAN, a multicyclic controlling computer program, is introduced. Implications of the introduction of multicyclic systems into helicopters are also discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Vertica; 4; 1, 19; 1980
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  • 4
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    Noise radiation from the side edges of flaps (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The recently observed phenomenon of high noise radiation from the side edges of flaps in flow is investigated by way of a simple two-dimensional model problem. The model is based upon a physical picture of boundary layer vorticity being swept around the edge by spanwise flow on the flap. The model problem is developed and solved and the resulting noise radiation calculated. Further, a mathematical condition for the vortex to be captured by the potential flow and swept around the edge is derived. The results show that the sound generation depends strongly upon the strength of the vorticity and distance from the edge and that it can be more intense than the more common trailing edge noise source in agreement with the experimental observations.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; May 1980
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  • 5
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    Stability aspects of diverging subsonic flow (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes the computation of two-dimensional, subsonic, diverging internal flows and how they differ from the corresponding converging flows. Such diverging or decelerating flows occur in such obvious places as subsonic diffusers and inlets; however, such flows also occur in supersonic nozzles in the presence of a normal shock. The flow instability and its relation to the numerical method used, boundary conditions, and viscous effects are assessed both analytically and numerically. The inviscid flow is shown to be physically unstable and a poor representation of the true viscous flow.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; May 1980
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  • 6
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    Measurements of cabin and ambient ozone on B747 airplanes (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: In response to recent concerns over possibly high ozone levels in the cabins of aircraft flying in the stratosphere, simultaneous measurements of the cabin and ambient ozone levels have been made as part of the NASA Global Atmospheric Sampling Program. Examples of the data taken on commercially operated Boeing 747-100 and 747SP airplanes are given for selected flights, together with summary statistics of over 5600 observations. Cabin ozone levels vary with the ambient level and, for unmodified aircraft, are higher on the 747SP than on the 747-100. Modifications to the ventilation system of the 747SP reduced cabin ozone levels by varying amounts up to a factor of 14.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 17; Apr. 198
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  • 7
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    Illustration of airfoil shape effect on forward-swept wing divergence (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A static aeroelastic analysis is presented of the divergence of untapered wings with conventional and supercritical airfoil sections at sweep angles of zero and -15 deg. One bending and one torsion mode were employed for a uniform rectangular cantilevered beam with the elastic axis at midchord, and calculations were based on a two-dimensional differential equations formulation in the structural coordinate system and in simple strip theory. A minimum divergence speed in the transonic range is obtained which is associated with the rearward shift of the aerodynamic center, and a 17% difference in minimum divergence dynamic pressure is found between a supercritical and a conventional wing. It is noted that although the strip method employed allows the assessment of the sensitivity of airfoil shapes to divergence, three-dimensional transonic aerodynamic methods should be used to predict wing divergence characteristics.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 17; Oct. 198
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  • 8
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    Computational aerodynamics on large computers (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Three examples of advances in computational aerodynamics; (1) three-dimensional inviscid transonic analysis, (2) design calculations for wings, and (3) the computation of viscous-induced aileron buzz, are reviewed. Attention is given to wing surface pressures, design optimization, computer memory, speed and advanced solution methods on parallel computer architecture. It is determined that many implicit approximate-factorization schemes, that have been developed for Navier-Stokes equations, can be coded to run efficiently on microprocessors.
    Keywords: AERODYNAMICS
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  • 9
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    Wing flapping with minimum energy (1980)
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    Publication Date: 2011-08-18
    Description: A technique employed by Prandtl and Munk is adapted for the case of a wing in flapping motion to determine its lift distribution. The problem may be reduced to one of minimizing induced drag for a specified and periodically varying bending moment at the wing root. It is concluded that two wings in close tandem arrangement, moving in opposite phase, would eliminate the induced aerodynamic losses calculated
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal; 84; July 198
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  • 10
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    The effect of finite turbulence spatial scale on the amplification of turbulence by a contracting stream (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The turbulence downstream of a rapid contraction is calculated for the case when the turbulence scale can have the same magnitude as the mean-flow spatial scale. The approach used is based on the formulation of Goldstein (1978) for turbulence downstream of a contraction, with the added assumptions of a parallel mean flow at downstream infinity and turbulence calculated far enough downstream so that the nonuniformity of the mean flow field has decayed, and by treating the inverse contraction ratio as a small parameter. Consideration is given to the large-contraction-ratio and classical rapid-distortion theory limits, and to results at an arbitrary contraction ratio. It is shown that the amplification effect of the contraction is reduced when the spatial scale of the turbulence increases, with the upstream turbulence actually suppressed for a contraction ratio less than five and a turbulence spatial scale greater than three times the transverse dimensions of the downstream channel.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 98; June 12
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  • 11
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    Types of leeside flow over delta wings (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: It is noted that so far most systematic investigations on the lee side flow over delta wings at supersonic speeds are concerned with flat upper surfaces. On the basis of these results, the paper makes an attempt to characterize the different types of flow over a wing with a delta-shaped upper surface by varying a number of parameters. It is concluded that the work should be considered a first step toward systematizing the flow over delta-shaped lee sides as well.
    Keywords: AERODYNAMICS
    Type: Zeitschrift fuer Flugwissenschaften und Weltraumforschung; 4; Mar
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  • 12
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    NACA Conference on Boundary Layers. A compilation of the papers presented (1947)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Keywords: AERODYNAMICS
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  • 13
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    Helicopter theory (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A comprehensive presentation is made of the engineering analysis methods used in the design, development and evaluation of helicopters. After an introduction covering the fundamentals of helicopter rotors, configuration and operation, rotary wing history, and the analytical notation used in the text, the following topics are discussed: (1) vertical flight, including momentum, blade element and vortex theories, induced power, vertical drag and ground effect; (2) forward flight, including in addition to momentum and vortex theory for this mode such phenomena as rotor flapping and its higher harmonics, tip loss and root cutout, compressibility and pitch-flap coupling; (3) hover and forward flight performance assessment; (4) helicopter rotor design; (5) rotary wing aerodynamics; (6) rotary wing structural dynamics, including flutter, flap-lag dynamics ground resonance and vibration and loads; (7) helicopter aeroelasticity; (8) stability and control (flying qualities); (9) stall; and (10) noise.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 14
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    Small Transport Aircraft Technology (1980)
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    Publication Date: 2011-08-17
    Description: The article surveys the results of the NASA-instituted Small Transport Aircraft Technology (STAT) research effort aimed at generating advanced technologies for application to new small, short haul transports having significantly better performance, efficiency, and environmental compatibility. Discussion covers fuselage designs and bonded aluminum-honeycomb wing construction which reduces the number of parts and fasteners, and gives a smoother outer contour. Topics discussed include: advanced aluminum alloys, composite primary structures, propellers, engine components, icing protection, avionics, flight controls, aerodynamics, and gust load alleviation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 18; Feb. 198
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  • 15
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    Constrained optimum trajectories with specified range (1980)
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    Publication Date: 2011-08-17
    Description: The characteristics of optimum fixed-range trajectories whose structure is constrained to climb, steady cruise, and descent segments are derived by application of optimal control theory. The performance function consists of the sum of fuel and time costs, referred to as direct operating costs (DOC). The state variable is range-to-go and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum cruise energy for sufficiently large range. At short ranges (500 n. mi. and less) a cruise segment may also occur below the optimum cruise energy. The existence of such a cruise segment depends primarily on the fuel flow vs thrust characteristics and on thrust constraints. If thrust is a free control variable along with airspeed, it is shown that such cruise segments will not generally occur. If thrust is constrained to some maximum value in climb and to some minimum in descent, such cruise segments generally will occur. The performance difference between free thrust and constrained thrust trajectories has been determined in computer calculations for an example transport aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance and Control; 3; Jan
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  • 16
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    Shipboard trials of the Quiet Short-Haul Research Aircraft /QSRA/ (1980)
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    Publication Date: 2011-08-18
    Description: The feasibility of the application of advanced state-of-the-art high lift STOL aircraft in the aircraft carrier environment was evaluated using the NASA Quiet Short-Haul Research Aircraft (QSRA). The QSRA made repeated unarrested landings and free deck takeoffs from the USS Kitty Hawk while being flown by three pilots of significant different backgrounds. The exercise demonstrated that the USB propulsive lift technology presents no unusual problems in the aircraft carrier environment. Optimum parameters for landing the QSRA were determined from the shore-based program; these proved satisfactory during operations aboard ship. Correlation of shipboard experience with shore-based data indicates that both free deck takeoffs and unarrested landings could be conducted with zero to 35 knots of wind across the deck of an aircraft carrier the size of the USS Kitty Hawk.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 17
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    The XV-15 tilt rotor research aircraft (1980)
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    Publication Date: 2011-08-18
    Description: The XV-15 tilt rotor has shown good handling qualities in all modes of flight; in the helicopter mode it allows precision hover and agility with low pilot workload. Vibration and noise levels are low; the conversion procedure is easy, with satisfactory acceleration or deceleration. The XV-15 handling demonstrated its potential for many civil and military applications.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 18
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    Thin-layer approximation for three-dimensional supersonic corner flows (1980)
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    Publication Date: 2011-08-18
    Description: The thin-layer approximation is extended to an axial corner that is formed by the intersection of two perpendicular plates, one of which has an inclination angle with respect to the free stream. A computer code developed by Hung and MacCormack (1978) is modified for the thin-layer approximation, and a case with Mach 5.9 and a wedge angle of 6 deg is computed. In addition, it is shown that it is not necessary to solve the complete Navier-Stokes equations for a three-dimensional high-Reynolds-number corner flow.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; Dec. 198
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  • 19
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    Application of an advanced trajectory optimization method to ramjet propelled missiles (1980)
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    Publication Date: 2011-08-18
    Description: The mission performance characteristics of ramjet-propelled missiles are highly dependent upon the trajectory flown. Integration of the trajectory profile with the ramjet propulsion system performance characteristics to achieve optimal missile performance is very complex. Past trajectory optimization methods have been extremely problem dependent and require a high degree of familiarity to achieve success. A general computer code (CTOP) has been applied to ramjet-powered missiles to compute open-loop optimal trajectories. CTOP employs Chebyshev polynomial representations of the states and controls. This allows a transformation of the continuous optimal control problem to one of parameter optimization. With this method, the trajectory boundary conditions are always satisfied. State dynamics and path constraints are enforced via penalty functions. The presented results include solutions to minimum fuel-to-climb, minimum time-to-climb, and minimum time-to-target intercept problems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Optimal Control Applications and Methods; 1; Oct
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  • 20
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    Supersonic cruise vehicle research/business jet (1980)
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    Publication Date: 2011-08-18
    Description: A comparison study of a GE-21 variable propulsion system with a Multimode Integrated Propulsion System (MMIPS) was conducted while installed in small M = 2.7 supersonic cruise vehicles with military and business jet possibilities. The 1984 state of the art vehicles were sized to the same transatlantic range, takeoff distance, and sideline noise. The results indicate the MMIPS would result in a heavier vehicle with better subsonic cruise performance. The MMIPS arrangement with one fan engine and two satellite turbojet engines would not be appropriate for a small supersonic business jet because of design integration penalties and lack of redundancy.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Supersonic Cruise Res., 1979, Pt. 2; p 935-949
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  • 21
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    A family of supersonic airplanes: Technical and economic feasibility (1980)
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    Publication Date: 2011-08-18
    Description: To improve the prospects for success in the market place, the family approach is essential to the design of future supersonic airplanes. The evolution from a basic supersonic airplane to a family could follow historic patterns, with one exception: substantial changes in passenger carrying capacity will be difficult by the conventional fuselage "doughnut" approach so successfully used on the cylindrical fuselage of subsonic airplanes. The primary reasons for this difference include the requirement for highly integrated "area ruled" configurations, to give the desired high supersonic aerodynamic efficiency, and other physical limitations such as takeoff and landing rotation. A concept for a supersonic airplane family that could effectively solve the variable range and passenger capacity problem provides for modification of the fuselage cross section that makes it possible to build a family of three airplanes with four, five, and six abreast passenger seating. This is done by replacing or modifying portions of the fuselage. All airplanes share the same wing, engines, and major subsystems. Only small sections of the fuselage would be different, and aerodynamic efficiency need not be compromised.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Supersonic Cruise Res., 1979, Pt. 2; p 833-854
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  • 22
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    Overview of Boeing supersonic transport efforts, 1971 - 1979 (1980)
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    Publication Date: 2011-08-18
    Description: Following cancellation of the United States Supersonic Transport program, the status of the technology was assessed carefully and emphasis was put on finding solutions for what were considered the major technical difficulties. In particular, work on the breakthroughs needed to advance the technology was emphasized. Currently, solutions to all major technical problems are identified. Depending on the subject, either the problem is no longer a concern or the steps needed to bring about a solution are mapped out clearly. Throughout the NASA SCR program, important strides were made in the identification of design advances which would greatly improve supersonic airplane fuel efficiency, noise, and other performance and cost affecting parameters. Furthermore, these efforts created an atmosphere in which it was possible for new ideas to flourish and positive inventions to take place such as the variable cycle engine and the blended fuselage. These technical gains show that, given availability of such technology, advanced supersonic transports could be developed that would be economically successful and environmentally acceptable.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Supersonic Cruise Res., 1979, Pt. 2; p 821-832
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  • 23
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    Structural concept trends for commercial supersonic cruise aircraft design (1980)
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    Publication Date: 2011-08-18
    Description: Structural concept trends for future commercial supersonic transport aircraft are considered. Highlights, including the more important design conditions and requirements, of two studies are discussed. Knowledge of these design parameters, as determined through studies involving the application of flexible mathematical models, enabled inclusion of aeroelastic considerations in the structural-material concepts evaluation. The design trends and weight data of the previous contractual study of Mach 2.7 cruise aircraft were used as the basis for incorporating advanced materials and manufacturing approaches to the airframe for reduced weight and cost. Structural studies of design concepts employing advanced aluminum alloys, advanced composites, and advanced titanium alloy and manufacturing techniques are compared for a Mach 2.0 arrow-wing configuration concept. Appraisals of the impact of these new materials and manufacturing concepts to the airframe design are shown and compared. The research and development to validate the potential sources of weight and cost reduction identified as necessary to attain a viable advanced commercial supersonic transport are discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Supersonic Cruise Res., 1979 pt. 2; p 563-587
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  • 24
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    Flowfield calculations past an entry probe with ablated nose shape (1980)
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    Publication Date: 2011-08-17
    Description: The effects of ablated nose shapes on the flowfield solutions are studied, using a time-dependent finite-difference method developed by Kumar, et al. (1979). Solutions are obtained for the laminar flow of a radiating mixture of H-He in chemical equilibrium past a blunt axisymmetric body at zero angle of attack. The freestream conditions correspond to a point on a typical Jovian entry trajectory, and the initial probe shape is a 45-deg half-angle spherically blunted cone. It is found that as nose bluntness increases, the following occur: in the nose region, shock standoff distances and radiative heating rates increase substantially; surface pressure level increases, but convective heating rates decrease.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; June 198
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  • 25
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    Unified treatment of lifting atmospheric entry (1980)
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    Publication Date: 2011-08-17
    Description: This paper presents a unified treatment of the effect of lift on peak acceleration during atmospheric entry. Earlier studies were restricted to different regimes because of approximations invoked to solve the same transcendental equation. This paper shows the connection between the earlier studies by employing a general expression for the peak acceleration and obtains solutions to the transcendental equation without invoking the earlier approximations. Results are presented and compared with earlier studies where appropriate.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 17; Mar
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  • 26
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    Composite aircraft structures (1980)
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    Publication Date: 2011-08-18
    Description: In late 1975, the Aircraft Energy Efficiency (ACEE) program was initiated by NASA in order to accelerate the development of selected technologies which showed promise for substantial improvements in the fuel efficiency of commercial transport aircraft. A description is presented of the status of the composite structure development programs which form one of the six sections of the ACEE program. Six aircraft components are currently being developed under NASA contract by three major transport manufacturers. The components include the upper aft rudder of the Douglas DC-10, the inboard ailerons of the Lockheed L-1011, the elevators of the Boeing 727, the vertical stabilizers for the Lockheed L-1011 and Douglas DC-10, and the horizontal stabilizers of the Boeing 737. It is found that the composite components show a high potential for achieving cost comparability with the metal parts they are designed to replace.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 27
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    Theoretical and Experimental studies of aerodynamic interference effects (1980)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Theoretical studies of aerodynamic forces on winglets shed considerable light on the mechanism by which these devices can reduce drag at constant total lift and on the necessity for proper alignment and cambering to achieve optimum favorable interference. Results of engineering studies, wind tunnel tests and performance predictions are reviewed for installations proposed for the AMST YC-14 and the KC-135 airplanes. The other major area of aerodynamic interference discussed is that of engine nacelle installations. Slipper and overwing nacelles have received much attention because of their potential for noise reduction, propulsive lift and improved ground clearance. A major challenge is the integration of such nacelles with the supercritical flow on the upper surface of a swept wing in cruise at high subsonic speeds.
    Keywords: AERODYNAMICS
    Type: AGARD Subsonic(Transonic Configuration Aerodyn.; 19 p
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  • 28
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    Numerical solution techniques for unsteady transonic aerodynamics problems (1980)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Basic concepts of finite difference solution techniques for unsteady transonic flows are presented. The hierarchy of mathematical forumulations that approximate the Navier-Stokes equations are reviewed. The basic concepts involved in constructing numerical algorthms to solve these formulations are given. Semi-implicit and implicit schemes are constructed and analyzed. The discussion focuses primarily on techniques for solving the low frequency transonic small disturbance equation. This is the simplest formulation that contains the essence of inviscid unsteady transonic flow physics. The low frequency formulation is emphasized here because codes based on this theory can be run in minutes of processor time on currently available computers. Furthermore, numerical techniques involved in solving this simple formulation also apply to the more complicated formulations. Extensions to these formulations are briefly described. An indication of the present capability for solving unsteady transonic flows is provided. Important areas of future research for the advancement of computational unsteady transonic aerodynamics are described.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Unsteady Aerodyn.; 24 p
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  • 29
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    Use of advanced computers for aerodynamic flow simulation (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The current and projected use of advanced computers for large-scale aerodynamic flow simulation applied to engineering design and research is discussed. The design use of mature codes run on conventional, serial computers is compared with the fluid research use of new codes run on parallel and vector computers. The role of flow simulations in design is illustrated by the application of a three dimensional, inviscid, transonic code to the Sabreliner 60 wing redesign. Research computations that include a more complete description of the fluid physics by use of Reynolds averaged Navier-Stokes and large-eddy simulation formulations are also presented. Results of studies for a numerical aerodynamic simulation facility are used to project the feasibility of design applications employing these more advanced three dimensional viscous flow simulations.
    Keywords: AERODYNAMICS
    Type: AGARD The Use of Computers as a Design Tool; 12 p
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  • 30
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    Wind tunnel test results of a new leading edge flap design for highly swept wings, a vortex flap (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A leading edge flap design for highly swept wings, called a vortex flap, was tested on an arrow wing model in a low speed wind tunnel. A vortex flap differs from a conventional plain flap in that it has a leading edge tab which is counterdeflected from the main portion of the flap. This results in intentional separation at the flap leading edge, causing a vortex to form and lie on the flap. By trapping this vortex, the vortex flap can result in significantly improved wing flow characteristics relative to conventional flaps at moderate to high angles of attack, as demonstrated by the flow visualization results of this tests.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Supersonic Cruise Res. 1979, Pt. 1; p 131-147
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  • 31
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    Supersonic wings with significant leading-edge thrust at cruise (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Experimental/theoretical correlations are presented which show that significant levels of leading edge thrust are possible at supersonic speeds for certain planforms which match the theoretical thrust distribution potential with the supporting airfoil geometry. The analytical process employed spanwise distribution of both it and/or that component of full theoretical thrust which acts as vortex lift. Significantly improved aerodynamic performance in the moderate supersonic speed regime is indicated.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Supersonic Cruise Res. 1979, Pt. 1; p 229-246
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  • 32
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    Some considerations of aerodynamic heating (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 399-411
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  • 33
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    The use of conincal and cylindrical fields in supersonic wing theory (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 341-353
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  • 34
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    Summary of NACA submerged-inlet investigations (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 49-52
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  • 35
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    Lift and drag characteristics of a wing with several angles of sweep at high subsonic speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 21-28
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  • 36
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    Investigation of side inlets at supersonic speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 53-57
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  • 37
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    A review of recent information relating to the drag rise of airplanes (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 3-13
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  • 38
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    Air inlets (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 307-322
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  • 39
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    Characteristics of wing sections at transonic speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 127-149
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  • 40
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    A review of approximate methods in subsonic compressible flow (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 29-46
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  • 41
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    Flight characteristics at transonic speeds. 1: P-80A airplane investigation (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 153-162
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  • 42
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    Nacelles for high critical speeds on straight and swept wings (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 59-64
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  • 43
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    Landing characteristics of high-speed wings (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 29-40
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  • 44
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    Airplane wing leading edge variable camber flap (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The invention and design of an aerodynamic high lift device which provided a solution to an aircraft performance problem are described. The performance problem of converting a high speed cruise airfoil into a low speed aerodynamic shape that would provide landing and take-off characteristics superior to those available with contemporary high lift devices are addressed. The need for an improved wing leading edge device that would complement the high lift performance of a triple slotted trailing edge flap is examined. The mechanical and structural aspects of the variable camber flap are discussed and the aerodynamic performance aspects only as they relate to the invention and design of the device are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 225-235
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  • 45
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    The use of source and sink concepts in the calculation of wing characteristics at supersonic speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 355-365
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  • 46
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    Helicopter research problems (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA: Univ. Conf. on Aerodyn.; p 267-285
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  • 47
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    Flying and handling qualities of airplanes (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA: Univ. Conf. on Aerodyn.; p 251-264
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  • 48
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    Prediction of Wing Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 151-166
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  • 49
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    Characteristics of wing sections at subcritical speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 109-125
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  • 50
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    Characteristics of a triangular-winged aircraft. 1: Performance data (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 169-172
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  • 51
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    Two-dimensional supersonic wing theory (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 325-340
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  • 52
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    Prediction of the aerodynamic characteristics of wings of arbitrary plan form (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 95-100
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  • 53
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    Nose inlets (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 43-48
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  • 54
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    Airfoil section characteristics at high subsonic speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 15-20
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  • 55
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    A survey of methods for the calculation of flow around bodies of revolution at supersonic speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 377-395
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  • 56
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    Characteristics of a triangular-winged aircraft. 2: Stability and control (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 163-179
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  • 57
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    Unsteady lift in high-speed flight (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 367-376
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  • 58
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    Maximum-lift and stalling characteristics of wings (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 167-183
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  • 59
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    Stability of the laminar boundary layer (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 3-26
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  • 60
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    Effects on inlet technology on cruise speed selection (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The impact of cruise speed on technology level for certain aircraft components is examined. External-compression inlets were compared with mixed compression, self starting inlets at cruise Mach numbers of 2.0 and 2.3. Inlet engine combinations that provided the greatest aircraft range were identified. Results show that increased transonic to cruise corrected air flow ratio gives decreased range for missions dominated by supersonic cruise. It is also found important that inlets be designed to minimize spillage drag at subsonic cruise, because of the need for efficient performance for overland operations. The external compression inlet emerged as the probable first choice at Mach 2.0, while the self starting inlet was the probable first choice at Mach 2.3. Airframe propulsion system interference effects were significant, and further study is needed to assess the existing design methods and to develop improvements.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Supersonic Cruise Res., 1979, pt. 1; p 391-411
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  • 61
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    Prediction of nacelle aerodynamic interference effects at low supersonic Mach numbers (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The accuracy of analytical predictions of nacelle aerodynamic interference effects at low supersonic speeds are studied by means of test versus theory comparisons. Comparisons shown include: (1) isolated wing body lift, drag, and pitching moments; (2) isolated nacelle drag and pressure distributions; (3) nacelle interference shock wave patterns and pressure distributions on the wing lower surface; (4) nacelle interference effects on wing body lift, drag, and pitching moments; and (5) total installed nacelle interference effects on lift, drag, and pitching moment. The comparisons also illustrate effects of nacelle location, nacelle spillage, angle of attack, and Mach numbers on the aerodynamic interference. The initial results seem to indicate that the methods can satisfactorily predict lift, drag, pitching moment, and pressure distributions of installed engine nacelles at low supersonic Mach numbers with mass flow ratios from 0.7 to 1.0 for configurations typical of efficient supersonic cruise airplanes.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Supersonic Cruise Res. 1979, Pt. 1; p 171-203
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  • 62
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    Results of a low-speed wind tunnel test of the MDC 2.2M supersonic cruise aircraft configuration (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of a low speed test conducted in the Full Scale Tunnel at NASA Langley using an advanced supersonic cruise vehicle configuration are presented. These tests used a 10 percent scale model of a configuration that had demonstrated high aerodynamic performance at Mach 2.2 during a previous test program. The low speed model has leading and trailing edge flaps designed to improve low speed lift to drag ratios at high lift and includes devices for longitudinal and lateral/directional control. The results obtained during the low speed test program have shown that full span leading edge flaps are required for maximum performance. The amount of deflection of the leading edge flap must increase with C sub L to obtain the maximum benefit. Over 80 percent of full leading edge suction was obtained up to lift off C sub L's of 0.65. A mild pitch up occurred at about 6 deg angle of attack with and without the leading edge flap deflected. The pitch up is controllable with the horizontal tail. Spoilers were found to be preferable to spoiler/deflectors at low speeds. The vertical tail maintained effectiveness up to the highest angle of attack tested but the tail on directional stability deteriorated at high angles of attack. Lateral control was adequate for landing at 72 m/sec in a 15.4 m/sec crosswind.
    Keywords: AERODYNAMICS
    Type: Supersonic Cruise Res. 1979, Pt. 1; p 35-57
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  • 63
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    NASA general aviation stall/spin flight testing (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: A comprehensive program incorporating spin tunnel, static and rotary balance wind tunnel, full scale wind tunnel, free flight radio control model, flight simulation, and full scale flight testing was undertaken. Work includes aerodynamic definition of various configurations at high angles of attack, testing of stall and spin prevention concepts, definition of spin and spin recovery characteristics, and development of test techniques and emergency spin recovery systems. Some of the more interesting results to date are presented for the first airplane in the program in the areas of tail design, wind leading edge design, mass distribution, center of gravity location, and small airframe changes, with associated pilot observations. Design philosophy of the spin recovery parachute system is discussed, in addition to test techniques.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Society of Experimental Test Pilots Tech. Rev., Vol. 15, No. 1; p 36-49
    Format: text
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  • 64
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    The Quiet Short-haul Research Aircraft (QSRA) (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: The Quiet Short-Haul Research Aircraft (QSRA) is to be used as a flight facility for advanced flight experiments in terminal area operations. The overall objective of the QSRA program is to expand the technology base of the upper surface blowing propulsive lift concept in order to establish design criteria for the aircraft industry and to establish criteria for advanced STOL aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Society of Experimental Test Pilots Soc. of Exptl. Test Pilots Tech. Rev., Vol. 14, No. 4; p 77-93
    Format: text
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  • 65
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    The oblique wing-research aircraft (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: The AD-1 airplane was designed as a low cost, low speed manned research tool to evaluate the flying qualities of the oblique wing concept. The airplane is constructed primarily of foam and fiberglass and incorporates simplicity in terms of the onboard systems. There are no hydraulics, the control system is cable and torque tube, and the electrical systems consist of engine driven generators which power the battery for engine start, cockpit gages, trim motors, and the onboard data system. The propulsion systems consist of two Microturbo TRS-18 engines sea level trust rated at 220 pounds. The airplane weighs approximately 2100 pounds and has a performance potential in the range of 200 knots and an altitude of 15,000 feet.
    Keywords: AERODYNAMICS
    Type: Society of Experimental Test Pilots Tech. Rev., Vol. 15, No. 1; p 4-5
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  • 66
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    TRANSEP: A program for high lift separated flow about airfoils (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method and program called TRANSEP is presented that can be used for the analysis of the flow about a low speed airfoil under high lift, massive separation conditions. Since the present program is a modification of the direct-inverse TRANDES code, it can also be used for the design and analysis of transonic airfoils, including the effects of weak viscous interaction. Interactions on program usage, program modifications to convert TRANDES to TRANSEP, and sample cases and results are given.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3376 , NAS 1.26:3376
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  • 67
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    Development of Integrated Programs for Aerospace-vechicle Design (IPAD). IPAD user requirements: Implementation (first-level IPAD) (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The requirements implementation strategy for first level development of the Integrated Programs for Aerospace Vehicle Design (IPAD) computing system is presented. The capabilities of first level IPAD are sufficient to demonstrated management of engineering data on two computers (CDC CYBER 170/720 and DEC VAX 11/780 computers) using the IPAD system in a distributed network environment.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-162713 , NAS 1.26:162713 , D6-IPAD-70016-D-1
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  • 68
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    Results of design studies and wind tunnel tests of high-aspect-ratio supercritical wings for an energy efficient transport (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These basic characteristics of critical wings included wing area, aspect ratio, average thickness, and sweep as well as practical constraints on the planform and thickness near the wing root to allow for the landing gear. Within these constraints, a large matrix of wing designs was studied with spanwise variations in the types of airfoils and distribution of lift as well as some small planform changes. The criteria by which the five candidate wings were chosen for testing were the cruise and buffet characteristics in the transonic regime and the compatibility of the design with low speed (high-lift) requirements. Five wing-wide-body configurations were tested in the NASA Ames 11-foot transonic wind tunnel. Nacelles and pylons, flap support fairings, tail surfaces, and an outboard aileron were also tested on selected configurations.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159332 , NAS 1.26:159332 , ACEE-06-FR-9894
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  • 69
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    A semi-analytic approach to the self induced motion of vortex sheets (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The rolling up of the trailing vortex sheet produced by a wing of finite span was calculated as a series expansion in time. For a vorticity distribution corresponding to a wing with cusped tips, the shape of the sheet was found by summing the series using Pade approximants. The sheet remains analytic for some time but ultimately develops an exponential spiral at the tips. The centroid of vorticity was conserved to high accuracy.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166182 , SU-JIAA-TR-32
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  • 70
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    Flow visualization study of spanwise blowing applied to the F-4 fighter aircraft configuration (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Water tunnel studies were performed to define the changes that occur in vortex flow fields above the wing due to spanwise blowing over the inboard and outboard wing panels and over the trailing-edge flaps. Flow visualization photographs were obtained for angles of attack up to 30 deg and sideslip angles up to 10 deg. The sensitivity of the vortex flows to changes in flap deflection angle, nozzle position, and jet momentum coefficient was determined. Deflection of the leading edge flap delayed flow separation and the formation of the wing vortex to higher angles of attack. Spanwise blowing delayed the breakdown of the wing vortex to farther outboard and to higher angles of attack. Spanwise blowing over the trailing edge flap entrained flow downward, producing a lift increase over a wide range of angles of attack. The sweep angle of the windward wing was effectively reduced in sideslip. This decreased the stability of the wing vortex, and it burst farther inboard. Reduced wing sweep required a higher blowing rate to maintain a stable vortex. A vortex could be stabilized on the outboard wing panel when an outboard blowing nozzle was used. Blowing from both an inboard and an outboard nozzle was found to have a favorable interaction.
    Keywords: AERODYNAMICS
    Type: NASA-CR-163096 , NOR-80-138
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  • 71
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    Study of materials performance model for aircraft interiors (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A demonstration version of an aircraft interior materials computer data library was developed and contains information on selected materials applicable to aircraft seats and wall panels, including materials for the following: panel face sheets, bond plies, honeycomb, foam, decorative film systems, seat cushions, adhesives, cushion reinforcements, fire blocking layers, slipcovers, decorative fabrics and thermoplastic parts. The information obtained for each material pertains to the material's performance in a fire scenario, selected material properties and several measures of processability.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-152378
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    An evaluation of NASA's program for improving aircraft fuel efficiency (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The report provides commentary and recommendations where appropriate on each of the major elements of the program. Key findings of the committee included a recommendation that closer ties be established between NASA and the FAA to expedite the use and acceptance of the new technology. The committee also cited the potential for fuel savings through an imporved air traffic control system and recommended that the management of NASA and the FAA discuss ways and means to work together to exploit more effectively the capabilities and responsibilities of each to develop air traffic control.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-164015 , PB81-116790
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  • 73
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    Development of advanced techniques for rotorcraft state estimation and parameter identification (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An integrated methodology for rotorcraft system identification consists of rotorcraft mathematical modeling, three distinct data processing steps, and a technique for designing inputs to improve the identifiability of the data. These elements are as follows: (1) a Kalman filter smoother algorithm which estimates states and sensor errors from error corrupted data. Gust time histories and statistics may also be estimated; (2) a model structure estimation algorithm for isolating a model which adequately explains the data; (3) a maximum likelihood algorithm for estimating the parameters and estimates for the variance of these estimates; and (4) an input design algorithm, based on a maximum likelihood approach, which provides inputs to improve the accuracy of parameter estimates. Each step is discussed with examples to both flight and simulated data cases.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-159297
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  • 74
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    Unsteady transonic small disturbance theory with strong shock waves (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory to correct the transonic small disturbance (TSD) equation to treat strong shock waves in unsteady flow is developed. The technique involves the addition of higher order terms, which are formally of negligible magnitude, to the low frequency TSD equation. These terms are then chosen such that any shock waves in the flow have strengths approximately equal to the appropriate Rankine-Hugoniot shock strength. Two correcting approaches are investigated. The first is to derive a correction for the mean steady flow and then simply use this corrected form for oscillatory flows. The second is to derive a correction for both steady and oscillatory parts of the flow. This second development is the most satisfactory and comparisons of the present results with Euler equation results are generally favorable, particularly regarding shock location, although there are some discrepancies in the pressure distribution in the leading edge region.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166157 , NEAR-TR-230
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  • 75
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    Aerodynamic effects of nearly uniform slipstreams on thin wings in the transonic regime (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified model is used to describe the interaction between a propeller slipstream and a wing in the transonic regime. The undisturbed slipstream boundary is assumed to coincide with an infinite circular cylinder. The undisturbed slipstream velocity is rotational and is a function of the radius only. In general, the velocity perturbation caused by introducing a wing into the slipstream is also rotational. By making small disturbance assumptions, however, the perturbation velocity becomes nearly potential, and an approximation for the flow is obtained by solving a potential equation.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152351
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  • 76
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    Experimental aerodynamic characteristics of two V/STOL fighter/attack aircraft configurations at Mach numbers from 0.4 to 1.4 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel test was conducted to measure the aerodynamic characteristics of two horizontal attitude takeoff and landing V/STOL fighter/attack aircraft concepts. In one concept, a jet diffuser ejector was used for the vertical lift system; the other used a remote augmentation lift system (RALS). Wind tunnel tests to investigate the aerodynamic uncertainties and to establish a data base for these types of concepts were conducted over a Mach number range from 0.2 to 2.0. The present report covers tests, conducted in the 11 foot transonic wind tunnel, for Mach numbers from 0.4 to 1.4. Detailed effects of varying the angle of attack (up to 27 deg), angle of sideslip (-4 deg to +8 deg), Mach number, Reynolds number, and configuration buildup were investigated. In addition, the effects of wing trailing edge flap deflections, canard incidence, and vertical tail deflections were explored. Variable canard longitudinal location and different shapes of the inboard nacelle body strakes were also investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81234 , A-8338
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  • 77
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    Experimental determination of unsteady blade element aerodynamics in cascades. Volume 2: Translation mode cascade (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A two dimensional cascade of harmonically oscillating airfoils was designed to model a near tip section from a rotor which was known to have experienced supersonic translational model flutter. This five bladed cascade had a solidity of 1.52 and a setting angle of 0.90 rad. Unique graphite epoxy airfoils were fabricated to achieve the realistic high reduced frequency level of 0.15. The cascade was tested over a range of static pressure ratios approximating the blade element operating conditions of the rotor along a constant speed line which penetrated the flutter boundary. The time steady and time unsteady flow field surrounding the center cascade airfoil were investigated.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165166 , EDR-10361-VOL-2
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  • 78
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    Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted of isolated convergent-divergent nozzles to determine the effect of several design parameters on nozzle performance. Tests were conducted using high pressure air for propulsion simulation at Mach numbers from 0.60 to 2.86 at an angle of attack of 0 deg and at nozzle pressure ratios from jet off to 46.0. Three power settings (dry, partial afterburning, and maximum afterburning), three nozzle lengths, and nozzle expansion ratios from 1.22 to 2.24 were investigated. In addition, the effects of nozzle throat radius and a cusp in the external boattail geometry were studied. The results of this study indicate that, for nozzles operating near design conditions, increasing nozzle length increases nozzle thrust-minus-drag performance. Nozzle throat radius and an external boattail cusp had negligible effects on nozzle drag or internal performance.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1766 , L-13974
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  • 79
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    Wind-tunnel measurements and comparison with flight of the boundary layer and heat transfer on a hollow cylinder at Mach 3 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The wind tunnel tests were conducted both with and without boundary layer trips at Mach 3 and nominal free stream Reynolds numbers per meter ranging from 3.3 x 10 the 6th power. Instrumentation consisted of pressure orifices, thermocouples, a boundary layer pitot pressure rake, and a floating element skin friction balance. Measurements from both wind tunnel and flight were compared with existing engineering prediction methods.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1789 , L-14044
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  • 80
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    Rotary balance data for a single engine general aviation design having a high aspect-ratio canard for an angle-of-attack range of 30 deg to 90 deg (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic characteristics obtained in a helical flow environment utilizing a rotary balance located in the Langley spin tunnel are presented in plotted form. The configurations tested included the basic airplane, various control deflections, two canard locations, and wing leading edge modifications, as well as airplane components.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3170
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  • 81
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    YF-12 cooperative airframe/propulsion control system program, volume 1 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several YF-12C airplane analog control systems were converted to a digital system. Included were the air data computer, autopilot, inlet control system, and autothrottle systems. This conversion was performed to allow assessment of digital technology applications to supersonic cruise aircraft. The digital system was composed of a digital computer and specialized interface unit. A large scale mathematical simulation of the airplane was used for integration testing and software checkout.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-163099 , SP-5317 , H-1136
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  • 82
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    Calculation of two dimensional vortex/surface interference using panel methods (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The application of panel methods to the calculation of vortex/surface interference characteristics in two dimensional flow was studied over a range of situations starting with the simple case of a vortex above a plane and proceeding to the case of vortex separation from a prescribed point on a thick section. Low order and high order panel methods were examined, but the main factor influencing the accuracy of the solution was the distance between control stations in relation to the height of the vortex above the surface. Improvements over the basic solutions were demonstrated using a technique based on subpanels and an applied doublet distribution.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159334 , REPT-79-13
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  • 83
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    A modified T-value method for selection of strain gages for measuring loads on a low aspect ratio wing (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique which may be useful for selecting strain gages for use in load equations is described. The technique is an adaptation of the previously used T-value method and is applied to a multispar structure. The technique, called the modified T-value method, is used to reduce the number of strain gages used in a load equation from twelve to two. A parallel reduction is made by calculating relative equation accuracies from three applied load distributions. The equations developed from the modified T-value method proved to be accurate more consistently than the T-value method.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1748 , H-1108
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  • 84
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    A mathematical model of the CH-53 helicopter (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical model suitable for real time simulation of the CH-53 helicopter is presented. This model, which is based on modified nonlinear classical rotor theory and nonlinear fuselage aerodynamics, will be used to support terminal-area guidance and navigation studies on a fixed-base simulator. Validation is achieved by comparing the model response with that of a similar aircraft and by a qualitative comparison of the handling characteristics made by experienced pilots.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81238 , A-8345
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  • 85
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    The effect of thermal stresses on the integrity of three built-up aircraft structures (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A Mach 6 flight was simulated in order to examine heating effects on three frame/skin specimens. The specimens included: a titanium truss frame with a lockalloy skin; a stainless steel z-frame with a lockalloy skin; and a titanium z-frame with a lockalloy skin. Thermal stresses and temperature were measured on these specimens for the purpose of examining their efficiency, performance, and integrity. Measured thermal stresses were examined with respect to material yield strengths, buckling criteria, structural weight, and geometric locations. Principal thermal stresses were studied from the standpoint of uniaxial stress assumptions. Measured thermal stresses were compared to predicted values.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81352 , H-1138
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  • 86
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    Induced drag ideal efficiency factor of arbitrary lateral-vertical wing forms (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A relatively simple equation is presented for estimating the induced drag ideal efficiency factor e for arbitrary cross sectional wing forms. This equation is based on eight basic but varied wing configurations which have exact solutions. The e function which relates the basic wings is developed statistically and is a continuous function of configuration geometry. The basic wing configurations include boxwings shaped as a rectangle, ellipse, and diamond; the V-wing; end-plate wing; 90 degree cruciform; circle dumbbell; and biplane. Example applications of the e equations are made to many wing forms such as wings with struts which form partial span rectangle dumbbell wings; bowtie, cruciform, winglet, and fan wings; and multiwings. Derivations are presented in the appendices of exact closed form solutions found of e for the V-wing and 90 degree cruciform wing and for an asymptotic solution for multiwings.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3357
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  • 87
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    Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at Mach numbers of 2.96, 3.96, and 4.63 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The longitudinal and lateral directional aerodynamic characteristics for two Mach 5 cruise aircraft concepts were determined for test Mach numbers of 2.96, 3.96, and 4.63. Estimates from hypersonic impact theory and first order supersonic linearized theory were compared with data to indicate the usefulness of these methods. The method which applied tangent cone empirical theory to the body and tangent wedge theory to the wings and to the horizontal and vertical tails provided the best estimates. The tangent cone empirical theory applied to all components showed poor agreement with data, and the linear theory estimates were accurate only for lift coefficient and drag coefficient at low angles of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1767 , L-13868
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  • 88
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    Full scale visualization of the wing tip vortices generated by a typical agricultural aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The trajectories of the wing tip vortices of a typical agricultural aircraft were experimentally determined by flight test. A flow visualization method, similar to the vapor screen method used in wind tunnels, was used to obtain trajectory data for a range of flight speeds, airplane configurations, and wing loadings. Detailed measurements of the spanwise surface pressure distribution were made for all test points. Further, a powered 1/8 scale model of the aircraft was designed, built, and used to obtain tip vortex trajectory data under conditions similar to that of the full-scale test. The effects of light wind on the vortices were demonstrated, and the interaction of the flap vortex and the tip vortex was clearly shown in photographs and plotted trajectory data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159382
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  • 89
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    A conservative implicit finite difference algorithm for the unsteady transonic full potential equation (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An implicit finite difference procedure is developed to solve the unsteady full potential equation in conservation law form. Computational efficiency is maintained by use of approximate factorization techniques. The numerical algorithm is first order in time and second order in space. A circulation model and difference equations are developed for lifting airfoils in unsteady flow; however, thin airfoil body boundary conditions have been used with stretching functions to simplify the development of the numerical algorithm.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81211 , AVRADCOM-TR-80-A-14
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  • 90
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    Assessment of variable camber for application to transport aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The potential benefits were determined for the variable camber of commercial transport airplanes designed for intercontinental and domestic missions. A variable camber concept was developed and incorporated into airplanes designed for the two missions. Benefits were evaluated by comparing the mission performance and direct operating costs for the variable camber airplanes with those for reference airplanes designed for the same missions but having fixed geometry high speed wings. Several technical uncertainties associated with implementing variable camber were also examined.
    Keywords: AERODYNAMICS
    Type: NASA-CR-158930
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  • 91
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    Bibliography on aerodynamics of airframe/engine integration of high-speed turbine-powered aircraft, volume 1 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This bibliography was developed as a first step in the preparation of a monograph on the subject of the aerodynamics of airframe/engine integration of high speed turbine powered aircraft. It lists 1535 unclassified documents published mainly in the period from 1955 to 1980. Primary emphasis was devoted to aerodynamic problems and interferences encountered in the integration process; however, extensive coverage also was given to the characteristics and problems of the isolated propulsion system elements. A detailed topic breakdown structure is used. The primary contents of the individual documents are indicated by the combination of the document's title and its location within the framework of the bibliography.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81814 , L-13251-VOL-1
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  • 92
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    A computer program for cyclic plasticity and structural fatigue analysis (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computerized tool for the analysis of time independent cyclic plasticity structural response, life to crack initiation prediction, and crack growth rate prediction for metallic materials is described. Three analytical items are combined: the finite element method with its associated numerical techniques for idealization of the structural component, cyclic plasticity models for idealization of the material behavior, and damage accumulation criteria for the fatigue failure.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-163101 , H-1139
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  • 93
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    Full scale wind tunnel investigation of a bearingless main helicopter rotor (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A stability test program was conducted to determine the effects of airspeed, collective pitch, rotor speed and shaft angle on stability and loads at speeds beyond that attained in the BMR/BO-105 flight test program. Loads and performance data were gathered at forward speeds up to 165 knots. The effect of cyclic pitch perturbations on rotor response was investigated at simulated level flight conditions. Two configuration variations were tested for their effect on stability. One variable was the control system stiffness. An axially softer pitch link was installed in place of the standard BO-105 pitch link. The second variation was the addition of elastomeric damper strips to increase the structural damping. The BMR was stable at all conditions tested. At fixed collective pitch, shaft angle and rotor speed, damping generally increased between hover and 60 knots, remained relatively constant from 60 to 90 knots, then decreased above 90 knots. Analytical predictions are in good agreement with test data up to 90 knots, but the trend of decreasing damping above 90 knots is contrary to the theory.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152373 , D210-11659-1
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  • 94
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    Preliminary design characteristics of a subsonic business jet concept employing an aspect ratio 25 strut braced wing (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advantages of replacing the conventional wing on a transatlantic business jet with a larger, strut braced wing of aspect ratio 25 were evaluated. The lifting struts reduce both the induced drag and structural weight of the heavier, high aspect ratio wing. Compared to the conventional airplane, the strut braced wing design offers significantly higher lift to drag ratios achieved at higher lift coefficients and, consequently, a combination of lower speeds and higher altitudes. The strut braced wing airplane provides fuel savings with an attendant increase in construction costs.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159361
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  • 95
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    Transonic rotor noise: Theoretical and experimental comparisons (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two complementary methods of describing the high speed rotor noise problem are discussed. The first method uses the second order transonic potential equation to define and characterize the nature of the aerodynamic and acoustic fields and to explain the appearance of radiating shock waves. The second employs the Ffowcs Williams and Hawkings equation to successfully calculate the acoustic far field. Good agreement between theoretical and experimental waveforms is shown for transonic hover tip Mach numbers from 0.8 to 0.9.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81236 , A-8342 , AVRADCOM-TR-80-A-12
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  • 96
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    The XV-15 tilt rotor research aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design characteristics of the XV-15 Tilt rotor research aircraft are presented. Particular attention is given to the following: control system; conversion system; and propulsion system. Flight test results are also reported.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81244 , AVRADCOM-TR-80-A-15 , A-8343
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  • 97
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    A fan pressure ratio correlation in terms of Mach number and Reynolds number for the Langley 0.3 meter transonic cryogenic tunnel (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Calibration data for the two dimensional test section of the Langley 0.3 Meter Transonic Cryogenic Tunnel were used to develop a Mach number-Reynolds number correlation for the fan pressure ratio in terms of test section conditions. Well established engineering relationships combined to form an equation which is functionally analogous to the correlation. A geometric loss coefficient which is independent of Reynolds number or Mach number was determined. Present and anticipated uses of this concept include improvement of tunnel control schemes, comparison of efficiencies for operationally similar wind tunnels, prediction of tunnel test conditions and associated energy usage, and determination of Reynolds number scaling laws for similar fluid flow systems.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1752 , L-13713
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  • 98
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    Estimation of wing nonlinear aerodynamic characteristics at supersonic speeds (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computational system for estimation of nonlinear aerodynamic characteristics of wings at supersonic speeds was developed and was incorporated in a computer program. This corrected linearized theory method accounts for nonlinearities in the variation of basic pressure loadings with local surface slopes, predicts the degree of attainment of theoretical leading edge thrust, and provides an estimate of detached leading edge vortex loadings that result when the theoretical thrust forces are not fully realized.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1718 , L-13589
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  • 99
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    Analytical and experimental study of mean flow and turbulence characteristics inside the passages of an axial flow inducer (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The inviscid and viscid effects existing within the passages of a three bladed axial flow inducer operating at a flow coefficient of 0.065 are investigated. The blade static pressure and blade limiting streamline angle distributions were determined and the three components of mean velocity, turbulence intensities, and turbulence stresses were measured at locations inside the inducer blade passage utilizing a rotating three sensor hotwire probe. Applicable equations were derived for the hotwire data reduction analysis and solved numerically to obtain the appropriate flow parameters. The three dimensional inviscid flow in the inducer was predicted by numerically solving the exact equations of motion, and the three dimensional viscid flow was predicted by incorporating the dominant viscous terms into the exact equations. The analytical results are compared with the experimental measurements and design values where appropriate. Radial velocities are found to be of the same order as axial velocities within the inducer passage, confirming the highly three dimensional characteristic of inducer flow. Total relative velocity distribution indicate a substantial velocity deficiency near the tip at mid-passage which expands significantly as the flow proceeds toward the inducer trailing edge. High turbulence intensities and turbulence stresses are concentrated within this core region. Considerable wake diffusion occurs immediately downstream of the inducer trailing edge to decay this loss core. Evidence of boundary layer interactions, blade blockage effects, radially inward flows, annulus wall effects, and backflows are all found to exist within the long, narrow passages of the inducer.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3333 , PSU-AERSP-74-2
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  • 100
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    Numerical lifting line theory applied to drooped leading-edge wings below and above stall (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical iterative solution to the classical Prandtl lifting-line theory, suitably modified for poststall behavior, is used to study the aerodynamic characteristics of straight rectangular finite wings with and without leading-edge droop. This study is prompted by the use of such leading-edge modifications to inhibit stall/spins in light general aviation aircraft. The results indicate that lifting-line solutions at high angle of attack can be obtained that agree with experimental data to within 20%, and much closer for many cases. Therefore, such solutions give reasonable preliminary engineering results for both drooped and undrooped wings in the poststall region. However, as predicted by von Karman, the lifting-line solutions are not unique when sectional negative lift slopes are encountered. In addition, the present numerical results always yield symmetrical lift distributions along the span, in contrast to the asymmetrical solutions observed by Schairer in the late 1930's. Finally, a series of parametric tests at low angle of attack indicate that the effect of drooped leading edges on aircraft cruise performance is minimal.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 17; Dec. 198
    Format: text
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