Some Preliminary Thoughts * Part I: Inviscid Hypersonic Flow * Hypersonic Shock and Expansion-Wave Relations * Local Surface Inclination Methods * Hypersonic Inviscid Flowfields: Approximate Methods * Hypersonic Inviscid Flowfields: Exact Methods * Part II: Viscous Hypersonic Flow * Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating * Hypersonic Viscous Interactions * Computational Fluid Dynamic Solutions of Hypersonic Viscous Flows * Part III: High-Temperature Gas Dynamics * High-Temperature Gas Dynamics: Some Introductory Considerations * Some Aspects of the Thermodynamics of Chemically Reacting Gases (Classical Physical Chemistry) * Elements of Statistical Thermodynamics * Elements of Kinetic Theory * Chemical Vibrational Nonequilibrium * Inviscid High-Temperature Equilibrium Flows * Inviscid High-Temperature Nonequilibrium Flows * Kinetic Theory Revisited: Transport Properties in High-Temperature Gases * Viscous High-Temperature Flows * Introduction to Radiative Gas Dynamics.

Hypersonic and high temperature gas dynamics

The performance of a Mach 6 viscous optimized waverider was calculated using the 3-D Navier-Stokes equations. The Mach 6 viscous optimized waverider was generated using MAXWARP, a code developed at the University of Maryland. The computations were performed using CFL3D, an implicit upwind-biased finite-volume algorithm developed at NASA Langley. Results show that good agreement was found between the calculated performance by MAXWARP and results from the Mach 6 Navier-Stokes computation. Furthermore, off-design performance of the Mach 6 optimized waverider was computed at Mach 4 and 8. The performance at these Mach numbers compared well with the performance of the viscous optimized waveriders specifically designed for these Mach numbers. Finally, contours of different flow parameters in the cross-flow plane were examined for the three calculations. The results indicate that the flow gradients are relatively small within the captured flow, and the variation itself is well behaved; thus, making the waverider configuration a promising choice for an engine/airframe design, especially for cruise-type applications.

Navier-Stokes computation of a viscous optimized waverider

The concept of a hypersonic waverider for applications in foreign planetary atmospheres is explored, particularly in regard to aeroassist for space vehicle trajectory modification. The overall concept of hypersonic waveriders is discussed in tutorial fashion. A partial review of past work is given, and the role of a new family of waveriders—th e viscous optimized waveriders generated at the University of Maryland—is highlighted. The mechanics of trajectory modification by aerodynamic vehicles with high lift-to-drag ratios in planetary atmospheres is explored. Actual hypersonic waverider designs for Mars and Venus atmospheres are presented. Moreover, they exhibit very high lift-to-drag ratios, as high as 15 in the atmosphere of Venus. These results graphically demonstrate that a hypersonic waverider is a viable candidate for aeroassist maneuvers in foreign planetary atmospheres.

Hypersonic Waveriders for Planetary Atmospheres

Analytic results from inviscid hypersonic small-disturbance theory for axisymmetric conical flow are used to generate waverider configurations valid for all values of Kb ^A/^5, where d is the semi vertex angle of the basic cone. By means of the calculus of variations, those configurations are sought that yield the maximum lift-todrag ratio subject to suitable constraints, such as fixed lift, fixed volume, fixed base area, fixed planform area, and so on. The inviscid analysis accounts for wave drag only, but the effects of viscous drag are discussed. For the fixed-lift constraint, two types of optimized configurations are found: types with pointed noses, and types with round noses with sharp leading edges. The results are analytic in nature and particularly suitable for studying the various tradeoffs that are involved in missile design. Comparison of the results with other types of lifting bodies suggests that properly selected cone-derived waveriders are among the best producers of large liftto-drag ratios.

Optimization of waverider configurations generated from axisymmetricconical flows

Experimental Forces and Moments on Cone-Derived Waveriders for M = 3 to 5

Surface pressure data are presented for two waverider lifting-body configurations in the Mach number range of 3-5 and unit Reynolds number of 2 X 106/ft. Angle of attack and sideslip angle were varied in the range ±20 deg. Comparison data are also given for an elliptic cone with a 1.87 major/minor axis ratio. The data complement earlier results for forces and moments. Present results corroborate the basic conical flow assumption and the first-order perturbation theory that underlie the waverider configuration design. Off-design data show smooth variations from the design conditions with no evidence of strong secondary shocks or deviations from ideal conical flow.

Experimental surface pressures on cone-derived waveriders for freestream M = 3-5

: Inviscid, supersonic conical flows past bodies whose cross-section deviates slightly from that of a right circular cone are studied by means of a perturbation technique. The effects of small angles of attack and yaw are included. Using the hypersonic small disturbances theory approximations, we have developed explicity results for the flow field velocity components, pressure, entropy, and shock shape for cases n, m = 1, 2, 3, 4. Comparisons of theory with experiment for n = 1, 2 are favorable. The streamsurfaces of the velocity field are calculated and possible waverider geometries that can be developed therefrom are discussed.

M. C. Jischke

Papers

Optimization of waverider configurations generated from axisymmetricconical flows

Experimental Forces and Moments on Cone-Derived Waveriders for M = 3 to 5

Experimental surface pressures on cone-derived waveriders for freestream M = 3-5

Optimization of waverider configurations generated from axisymmetricconical flows

Supersonic Flow Past Conical Bodies with Nearly Circular Cross Sections