2 edition of **Hypersonic similarity solutions for airfoils supporting exponential shock waves** found in the catalog.

Hypersonic similarity solutions for airfoils supporting exponential shock waves

Julian D. Cole

- 337 Want to read
- 18 Currently reading

Published
**1968**
by Rand Corporation in Santa Monica, Calif
.

Written in English

- Aerofoils.,
- Shock waves.,
- Aerodynamics, Hypersonic.

**Edition Notes**

Statement | [by] J.D. Cole and J. Aroesty. |

Series | Rand Corporation. Research memorandum -- RM-5724, Research memorandum (Rand Corporation) -- RM-5724. |

Contributions | Aroesty, J. |

The Physical Object | |
---|---|

Pagination | 44 p. |

Number of Pages | 44 |

ID Numbers | |

Open Library | OL18747381M |

Hypersonic vehicle design is a complicated and ongoing process. As a conventional rule of thumb, hypersonic flow can be defined as flow above Mach 5. However, this number is not set in stone, and only refers to an approximate Mach number where certain physical flow phenomena become important such as strong shock waves, thin shock. Hypersonic Airfoil with Power Law Shock Waves. B. A, Wagner* CNLS & C-3, B25S Los Alamos, N,M. S Introduction. paper the flow field over a class of two-dimensiorml lifting slwfnrrs the viewpoint of inviscid, hypersonic slnall-(listurl)nll.{’ theory (HSDT). It is WCIIknown that a flow field in which the shock.

Since thin shock layers are so common in hypersonic flight, designers must be careful to prevent the shock wave from one component of the aircraft from adversely interfering with another component. In addition, a hypersonic vehicle will likely utilize some kind of ramjet or scramjet engine. Finally we look at the role, which shock waves play in hypersonic airbreathing propulsion and in aerothermodynamic airframe/propulsion integration of CAV’s [9]. It is recalled that the flight-speed range of turbojet engines is up to Ыж = 3 to 4, that of ramjet engines 3 ^ M^ 6, and of scramjet engines 6 ^ M^

The inviscid hypersonic aerodynamic characteristics of circularly blunt- wedge airfoils are derived from numerical solutions. Hy-personic wedge theory based on explicit oblique-shock equations is shown to provide rapid estimates of the pressures over both sharp and blunt airfoils. The effects of varying. History. The first manufactured object to achieve hypersonic flight was the two-stage Bumper rocket, consisting of a WAC Corporal second stage set on top of a V-2 first stage. In February , at White Sands, the rocket reached a speed of 8, km/h (5, mph), or approximately Mach The vehicle, however, burned on atmospheric re-entry, and only charred remnants were found.

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A study of airfoil optimization, using the equations of hypersonic gas dynamics to explore the "Newtonian chine strip" theory that airfoil concavity enhances the lift-to-drag ratio for a fixed drag penalty. The flow behind concave and convex exponential shock waves is investigated, and the corresponding airfoil surfaces are by: 5.

Cole and J. Aroesty, Hypersonic similarity sol- utions for airfoils supporting exponential shock waves. A1AA MS, (). Hui, A solution for hypersonic flow past slender bodies.

Fluid Mech. 48, (). Hui and H. Hemdan, Higher order simi- larity solutions for hypersonic flow past by: 1. A solution to the hypersonic small disturbance equations is obtained for a class of two-dimensional bodies supporting logarithmic shock waves by reducing the partial differential equation to an.

This book presents a basic study of the behaviour of compressible gases, including gas dynamic equations, isentropic flow, isothermal flow, and shock waves. Hypersonic similarity solutions for. 3. Interaction of Disturbances with a Shock Wave 4. Flows Past Wedgelike Bodies and Slender Airfoils at Large Angles of Attack 5.

Approximate Method Using Shock and Simple Wave Relations (Shock-Expansion Method) 6. Generalization to Flows Past Bodies of Revolution Chapter V Effect of Slight Leading Edge Blunting on Hypersonic Flows Past Bodies Edition: 1.

We gratefully acknowledge support from the Simons Foundation and member institutions. > math > arXiv Hypersonic Similarity for the Two Dimensional Steady Potential Flow with Large Data. Authors: Jie Kuang, the shock solution structures (after scaling) are consistent, when the Mach number of the flow is sufficiently.

Further, Hui [7] found another similarity solution for two-dimensional flow, with a logarithmic shock wave. Both Cole and Arosety and Hui's solution, like that of Sedov, assumed infinite freestream Mach number, M~.'t To show the effect of finite values of M~, Hui and Hemdan[8] perturbed the two sol- utions [6,7] and reduced the perturbation.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Similarity solutions for oscillating pointed-nose slender axisymmetric bodies—part ii: curved bodies Acta Astronautica, Vol.

49, No. 11 Analytical Model of Unsteady Shock Motion on Hypersonic Forebodies. John J. Bertin, United States Air Force Academy. Russell M.

Cummings. © | Pearson | Available | Pearson | Available. A self-similar model for one-dimensional unsteady isothermal and adiabatic flows behind a strong exponential shock wave driven out by a cylindrical piston moving with time according to an exponential law in an ideal gas in the presence of azimuthal magnetic field and variable density is discussed in a rotating atmosphere.

The ambient medium is assumed to possess radial, axial and. A method based on the use of the two-approximation theory developed in [1, 2] is proposed for the computation of hypersonic flow past a conical wing with a Mach-type shock configuration.

The Normal Shock Wave Oblique and Curved Shocks Mach Number Independence Principle Real-Fluid Effects II. Small-Disturbance Theory Introduction and Basic Equations Hypersonic Similitude Unified Supersonic-Hypersonic Similitude Strip Theory Examples of Small-Disturbance Solutions Similar Solutions Experimental studies of hypersonic shock-wave boundary-layer interactions Two classes of shock-wave boundary-layer interactions were studied experimentally in a shock tunnel in which a low Reynolds number, turbulent flow at Mach 8 was developed on a cold, flat test surface.

The two classes of interactions were: (1) a swept interaction generated by a wedge ('fin') mounted. A computer algorithm has been developed to determine the bluntbody flow fields supporting symmetric parabolic and paraboloidal shock waves at infinite free stream Mach number.

Solutions are expressed in an analytic form as high‐order power series, in the coordinate normal to the shock, whose coefficients can be determined exactly. McGraw-Hill Book Company, New York. ISBN Albert A. Merrill (–) Instructor in Aeronautics, –, – First Instructor in Aeronautics at Caltech.

Inthe Boston Aeronautical Society was formed with Merrill, William H. Pickering, and James Means forming the executive committee. Inhe learned. The Similarity Law for Nonsteady Hypersonic Flows and Requirements for the Dynamical Similarity of Related Bodies in Free Flight, NACA TN No.

() Google Scholar Lighthill, M.J.: Higher Approximations in General Theory of High Speed Aerodynamics. Hypersonic Aerodynamics Introduction Hypersonic vehicles are commonplace. There are many more of them than the supersonic aircraft discussed in the last chapter. Applications include missiles, launch vehicles and entry bodies.

A huge effort has been made developing hypersonic aerodynamics methods and configurations. The self-similar solution for adiabatic flow headed by a magnetogasdynamic cylindrical shock wave in a rotating non-ideal gas is obtained by Vishwakarma et al.

Sedov () (see Rao and Ramana ) indicated that a limiting case of a self-similar flow-field with a power-law shock is the flow-field formed with an exponential shock. However, as the Mach number increases to hypersonic speeds, the shock wave approaches the surface of the body.

Thus, as the ow velocity changes direction after crossing the shock, the ow appears to be de ected by the body similar to Newtonian ow theory. Transonic Flow Past Unswept Airfoils Wave Drag Reduction by Design Airfoil Contour Wave Drag Approaches Supercritical Airfoil Sections Swept Wings at Transonic Speeds Wing—Body Interactions and the “Area Rule” Second-Order Area-Rule Considerations Forward Swept.Southwest Research Institute engineers are advancing what researchers know about hypersonic flight.

A new study presented at the Joint Army-Navy-NASA-Air Force (JANNAF) Propulsion Meeting describes a series of tests conducted at SwRI’s San Antonio headquarters that elucidate the conditions a future aircraft may experience traveling faster than 10 times the speed of sound.

X was the only manned aircraft to fly at low hypersonic speeds, i.e. at Mach 6. During its re-entry, space shuttle also acquires such speeds. The distance between shock wave, generated by a hypersonic aircraft and the aircraft is smaller than in case of supersonic aircraft.