The calculation of aerodynamic characteristics of wing-body combinations at subsonic flight speeds

Surface panel methods and finite difference methods are reviewed with respect to the use in the design of aeroplanes. It is concluded that there is a need for inverse surface panel type methods to diminish the trial and error character of the design process. Finite difference methods based on transonic small perturbation theory have to be based...

De wijze waarop wiskunde wordt gebruikt bij het onderzoek door het Nationaal Lucht- en Ruimtevaartlaboratorium

In deze voordracht is gepoogd om aan te geven wat er wordt verwacht van het toepassen van wiskunde in het Nationaal Lucht- en Ruimtevaartlaboratorium NLR. Hierbij staat centraal dat de bepaling van de waarde van de toepassing van de wiskxinde plaatsvindt binnen niet-wiskundige technische disciplines. Na een beschrijving van de taken van het NLR...

An hierarchic multi-suppliers computer network of a research laboratory with two settlements

For the aerospace laboratory NLR in the Netherlands the considerations are discussed that formed the basis of along-term plan to realize an optimal computer network. In the optimization process up to now the laboratory switched from a situation in which in each of both settlements one central close shop computer centre was available to a...

On the use of "panel methods" for predicting subsonic flow abour aerofoils and aircraft configurations

With the availability of large capacity computers there is a tendency for potential flow calculations to play a more important role in the process of aircraft development. The possibility for accurate prediction of aerodynamic characteristics had been widely increased by the development of socalled "panel methods". These are based on the...

Development of a method for predicting wing pressure distributions in subsonic flow: report on an intermediate solution

A method is described for predicting pressure distributions on wings in subcriticial attached flow. The method comprises the following basic elements. - linearized lifting surface theory the surface source panel method of Hess and Smith - approximate, uniformly valid, second-order corrections to be applied to the results of lifting surface...

An approximate method for the calculation of the pressure distribution on wing-body combinations at subcritical speeds

Paper presented at the AGARD Specialist Meeting "Aerodynamic Interference", Silver Spring, Maryland , 28 - 30 September 1970

Computer programmes in use at NLR for the calculation of flow details around wing-body combinations at subsonic speeds

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Note concerning the standard method for predicting pressure distributions on swept wings in subsonic flow available at NLR

An approximate method for the determination of the pressure distribution on wings in the lower critical speed range

Tho design of aircraft for efficient flight at high subsonic speeds demands for methods by which the pressure distributions on wings can be predicted accurately. The present paper is concerned with an approximating method that is based on the fact that the main characteristics of subsonic flow about wings are described rather well by the...

A digital computer programme for predicting pressure distributions on swept wings in subsonic flow according to a semi-empirical method

A computer programme is presented for the application of a semi-empirical method, based on work from the Royal Aircraft Establishment, for calculation of the pressure distribution on wings in subsonic attached flow. A comparison of calculated results with results of experiments is made with the purpose to determine some of the boundaries of the...

Calculated and measured pressure-distributions at subsonic speeds on a non-lifting wing, mounted on a body

Pressure measurements on a non-lifting 55 swept wing-body combination have been performed at subsonic speeds in the 2.00x1.60 m2 high speed windtunnel (HST) of the National Aerorpace Laboratory ITLR, Amsterdam. The model for there tests has been made available by the Royal Aircraft Establishment at Farnborough. The results of these measurements...

De berekening van drukverdelingen over de neuzen van F 28 vleugels, ten behoeve van de bepaling van de drukweeratand uit gemeten drukverdelingen.

Aan laodellen van de Fokker F 28 zijn drukmetingen uitgevoerd ten behoeve van de bepaling van de verdeling van draagkracht en torsiemoment over de vleugel. Later is nagegaan of deze drukmetingen tevens zijn te gebruiken voor de bepaling van de verdeling van de weerstand. Hierbij is gebleken dat er een te gering aantal drukken op het voorste deel...

Beschouwingen over de rol van drukverdelings-berekeningsmethoden bij de vormgeving van vliegtuigvleugels voor hoog-subsone snelheden

In this paper, a discussion is given of some of the aerodynamic difficulties involved in the design of wings for high-subsonic speeds, and of the theoretical methods available to calculate sub-critical pressure distributions. It appears that until now only one of these methods, being in fact a semi-emperical one, is developed far enough to be of...