Determination of shapes for minimum drag for a given lift and base area in linearized supersonic flow

This report presents a new method to find shapes that attain minimum wave drag under certain constraints. The constraints considered here are given values for the base area and the lift. The configuration is assumed to be embedded in a volume enclosed by two opposing circular Mach cones, one going through the most forward point of the...

On the determination of optium shapes with finite nose angles

This report presents a method for the determination of axially-symmetric shapes with a given base area that are optimum with respect to wave drag in supersonic flow and which have finite nose angles. Use has been made of the exact non-linear differential equations for supersonic flow together with the shock equations. The computed results...

A programme for the construction of a "first characteristic" Flow around a cone with or without inclination

This report gives a programme for the determination of the flow around a circular cone. Both the cases of zero-inclination and of a small inclination have been considered. The programme is written in the international machine language ALGOL and can therefore be operated on any computer having an ALGOL compiler. The purpose of this investigation...

Potential theorethical sescription of the flow in a jet deflected by a circular cylinder - Coanda effect

The Coanda effect, being an expedient for the application of blowing boundary layer control^, has been investigated by the NLH to gain an insight into the basic principle and the laws by which it is governed, Within the framework of this investigation a potential theory is developed which, at any rate leads to a qualitative prediction of the...

On the calculation of the propeller noise field around aircraft

A method is given for the calculation of the noise field of a propeller. This method is slightly different from that of Garrick and Watkins. It is believed that the differences in the results indicate the order of the inaccuracy due to the approximations inherent in the two methods. The noise field of two propellers is calculated to show these...

The design of optimum body-ring wing configurations in supersonic flow at zero lift

A survey is given of the results obtained at the NLR with respect to the determination of optimum body-ring wing configurations at zero lift. It is shown that if reliable data are required for practical shapes the use of exact flow theories is essential. The pressure distribution on the optimum configuration considered here is such that the...