Analytical and scale model research aimed at improved hangglider design

Research consisted of a theoretical analysis which attempts to predict aerodynamic characteristics using lifting surface theory and finite-element structural analysis as well as an experimental investigation using 1/5 scale elastically similar models in the NASA Ames 2m x 3m (7' x 10') wind tunnel. Experimental data were compared with theoretical results in the development of a computer program which may be used in the design and evaluation of ultralight gliders

Forebody tangential blowing for control at high angles of attack

A feasibility study to determine if the use of tangential leading edge blowing over the forebody could produce effective and practical control of the F-18 HARV aircraft at high angles of attack was conducted. A simplified model of the F-18 configuration using a vortex-lattice model was developed to obtain a better understanding of basic aerodynamic coupling effects and the influence of forebody circulation on lifting surface behavior. The effect of tangential blowing was estimated using existing wind tunnel data on normal forebody blowing and analytical studies of tangential blowing over conical forebodies. Incorporation of forebody blowing into the flight control system was investigated by adding this additional yaw control and sideforce generating actuator into the existing F-18 HARV simulation model. A control law was synthesized using LQG design methods that would schedule blowing rates as a function of vehicle sideslip, angle of attack, and roll and yaw rates

Aerodynamics, aeroelasticity, and stability of hang gliders. Experimental results

One-fifth-scale models of three basic ultralight glider designs were constructed to simulate the elastic properties of full scale gliders and were tested at Reynolds numbers close to full scale values. Twenty-four minor modifications were made to the basic configurations in order to evaluate the effects of twist, reflex, dihedral, and various stability enhancement devices. Longitudinal and lateral data were obtained at several speeds through an angle of attack range of -30 deg to +45 deg with sideslip angles of up to 20 deg. The importance of vertical center of gravity displacement is discussed. Lateral data indicate that effective dihedral is lost at low angles of attack for nearly all of the configurations tested. Drag data suggest that lift-dependent viscous drag is a large part of the glider's total drag as is expected for thin, cambered sections at these relatively low Reynolds numbers

Role of dynamic Jahn-Teller distortions in Na2C60 and Na2CsC60 studied by NMR

Through 13C NMR spin lattice relaxation (T1) measurements in cubic Na2C60, we detect a gap in its electronic excitations, similar to that observed in tetragonal A4C60. This establishes that Jahn-Teller distortions (JTD) and strong electronic correlations must be considered to understand the behaviour of even electron systems, regardless of the structure. Furthermore, in metallic Na2CsC60, a similar contribution to T1 is also detected for 13C and 133Cs NMR, implying the occurence of excitations typical of JT distorted C60^{2-} (or equivalently C60^{4-}). This supports the idea that dynamic JTD can induce attractive electronic interactions in odd electron systems.Comment: 3 figure

Using automatic differentiation with the quasi-procedural method for multidisciplinary design optimaization

As computers have become increasingly powerful, the field of design optimization has moved toward higher fidelity models (involving many more variables) in the early stages of design. One way in which this movement has manifested itself is in the increasing popularity of multidisciplinary design optimization (MDO). Because the models used in MDO are large and very complicated, a modular design is desirable. Because there are many- design parameters to optimize, derivatives must be computed accurately and efficiently. This paper describes how the quasi-procedural program architecture developed by Takai and Kroo [9] and the technique of automatic differentiation [6] can be combined to effectively address these needs. The two techniques are explained, the manner in which they were integrated into a single framework is described, and the result of using this framework for an optimization problem in airplane design is presented

Study on a camber adaptive winglet

Morphing structures are devices intended to be implemented in specific parts of the aircraft such to improve some aspects of the flight such as performance and maneuverability. More specifically for the wings, the in flight capability of adaptation of airfoil profile and control surfaces bring possibility to the aircraft operate at optimum performance condition during all flight phases. Morphing structures can only lead to optimal flight maneuverability and performance conditions if the morphed geometry leads to an improved flight condition. Aiming at the reduction of the lift induced drag in all flight phases, this research focus on the application of the genetic optimization algorithm for the definition of the camber section of an winglet. This research proposes the optimization at four different flight phases namely: climb, heavy cruise, mid cruise and light cruise. BLWF – a full potential equation solver coupled with 3D boundary layer modelling – is adopted in the aerodynamic performance, e.g. lift and drag ratio, calculation. A conventional genetic algorithm is adopted in the optimization of the camber of the airfoil composing the winglet. This paper describes the optimization procedure and compares geometries showing that the in flight change of the winglet geometry can sensibly contribute to the improvement of the aircraft performance reducing the fuel consumption

Comparison of Two Multidisciplinary Optimization Strategies for Launch-Vehicle Design

The investigation focuses on development of a rapid multidisciplinary analysis and optimization capability for launch-vehicle design. Two multidisciplinary optimization strategies in which the analyses are integrated in different manners are implemented and evaluated for solution of a single-stage-to-orbit launch-vehicle design problem. Weights and sizing, propulsion, and trajectory issues are directly addressed in each optimization process. Additionally, the need to maintain a consistent vehicle model across the disciplines is discussed. Both solution strategies were shown to obtain similar solutions from two different starting points. These solutions suggests that a dual-fuel, single-stage-to-orbit vehicle with a dry weight of approximately 1.927 x 10(exp 5)lb, gross liftoff weight of 2.165 x 10(exp 6)lb, and length of 181 ft is attainable. A comparison of the two approaches demonstrates that treatment or disciplinary coupling has a direct effect on optimization convergence and the required computational effort. In comparison with the first solution strategy, which is of the general form typically used within the launch vehicle design community at present, the second optimization approach is shown to he 3-4 times more computationally efficient

Correlation Time-of-flight Spectrometry of Ultracold Neutrons

The fearures of the correlation method used in time-of-flight spectrometry of ultracold neutrons are analyzed. The time-of-flight spectrometer for the energy range of ultracold neutrons is described, and results of its testing by measuring spectra of neutrons passing through interference filters are presented.Comment: 16 pages, 5 figure