document

Normal reflection of a plane gaseous detonation wave in a tube

Makomaski, A.H. (author)

A method, together with a FORTRAN IV computer program, is presented for the calculation of the trajectory and properties of a shock wave generated on normal reflection of an idealized gaseous detonation wave in a tube. The detonation wave is assumed to be formed by energetic ignition resulting in zero detonation induction distance. The...

report 1967

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Error oscillations in inertial navigation systems

Couperthwaite, W.J. (author)

Inertial navigation system errors are analysed in more detail than is found in the readily available literature, particularly in respect of the long period errors. The existence is shown of oscillatory errors of three different periods: 84 minutes, a nominal 24 hours and a less important Foucault period. The basic equations are essentially non...

report 1967

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The effect of "ground-to-air cycles" on the fatigue crack propagation in 2024-T3 Alclad sheet material

Schijve, J. (author), de Rijk, P. (author)

Constant-amplitude tests and simplified flight-simulation tests with 10 or 50 gust cycles per flight were performed. The effect of the ground-to-air cycle is compared with the Palmgren-Miner prediction. Optical and electron microscope observations of the fracture are presented.

report 1966

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Metingen in stationaire en niet stationaire asymmetrische vluchten ter bepaling van de stabiliteits- en besturingseigenschappen van het vliegtuig Beechcraft Queen Air, PH-NLR

Mooij, H.A. (author)

In dit rapport wordt een onderzoek beschreven dat werd uitgevoerd om de stabiliteits- en besturingsafgeleiden van het stelsel bewegingsvergelijkingen voor de dwarsbeweging van het Queen Air laboratoriumvliegtuig van het NLR te bepalen. Twee vliegtuig- en vliegtoestanden zijn onderzocht. Een vooronderzoek was erop gericht met een analoge...

report 1966

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Free-flight measurements of heat transfer and observations of transition on a caret wing at mach numbers up to 3.6

Picken, J. (author), Greenwood, G.H. (author)

Local heat transfer and surface pressure were measured on a caret wing incorporated in a four-wing Maikapar body. The design Mach number was 2.47 and the design incidence 12.130. Data were obtained over a Mach number range of 1.6 to 3.6 at Reynolds numbers based on ridge line length and free-stream conditions of up to 24 million. Transition...

report 1965

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A flight simulation study of difficulties in piloting large jet transport aircraft through severe atmospheric disturbances

Perry, D.H. (author), Burnham, J. (author)

A ground based flight simulator, having motion freedoms in pitch and roll, has been used to study the difficulties of flying a representative jet transport aircraft through severe storm turbulence. Random atmospheric disturbances of RMS velocity 15 ft/sec, combined with longer term draughts in the vertical plane of up to 200 ft/sec were studied...

report 1965

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Een methode ter bepaling van contourafwijkingen van een supersone windtunnel met instelbaar keelstuk

Tigchelaar, H. (author)

Verslag van periode van praktisch werk van 21 juni t/m 23 augustus I965 bij het Nationaal Lucht- en Ruimtevaartlaboratorium te Amsterdam.

report 1965

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Some notes on the calculation of the zero-lift wave drag of slender wings with swept trailing edges

Beasley, J.A. (author)

The calculation of the zero-lift wave drag for a wing with subsonic leading edges and supersonic swept trailing edges is described. The methods of Eminton and of Cahn and Olstad are used to evaluate the double integral which occurs in the formula for the wave drag; techniques of applying the methods to the type of area distribution associated...

report 1965

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The longitudinal response of a flexible slender aircraft to random turbulence

Huntley, E. (author)

The responses of a slender supersonic transport aircraft flying through random turbulence have been evaluated for the cruise condition. The problem was simplified by assuming that the aircraft responds only in heave, pitch and longitudinal bending as defined by the fundamental normal mode and by using piston theory aerodynamics. The results show...

report 1964

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An investigation of the statistical distribution of constant amplitude fatigue endurances for a maraging steel

Cicci, F. (author)

report 1964

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Rain erosion. Part IV: An assessment of various materials and de-icing systems

King, R.B. (author)

This Report discusses the rain erosion resistance of materials tested since the publication of Parts II and IV (Reports No. Chem 510 and 521). It includes sections on miscellaneous coatings and materials, and on several de-icing systems for engine intakes and leading edge applications. The effect of structural alterations to the test rig on the...

report 1964

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Low-energy spherical underwater explosions

Heuckroth, L.E. (author)

report 1964

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Stress-strain relations for some dislocation models

Rooke, D.P. (author)

It is shown that the basic model of the exhaustion theory of transient creep(2-4) is unable to account for certain observed phenomena. Several more complex models are proposed and studied.

report 1963

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Low-speed wind-tunnel tests on the Vickers-supermarine N.113 (scimitar) withblowing over trailing-edge flaps

Anscombe, A. (author), Butler, S.F.J. (author), Guyett, M.B. (author)

report 1963

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On optimum relay controls

Mufti, I.H. (author)

The problem of optimum control under various performance criteria for systems which are described by second-order differential equat ions is discussed. The maximum principle of Pontriagin is explained and applied to the solutions of these equations

report 1963

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A photogrammetric method of determining the mode shapes of vibrating objects, and results for a thin wing

Ohman, L.H. (author), van Wijk, M.C. (author)

A photogrammetric method of measuring the maximum displacements of a harmonically oscillating structure is described. A photographic exposure is taken of reference marks on the oscillating object and the photogrammetric measurements are made on the negative plate. The method has been applied to determine the normal mode shapes of a thin wing....

report 1962

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1/12-scale model tests of an open circuit VTOL propulsion tunnel. Part I and II

Brown, D. (author)

Part I: Selection of and basic testing of a suitable configuration using an external air supply. Part II: Tests with the addition of a Bellmouth intake and driving fan.

report 1962

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A consideration of the similarity requirements for aerothermoelastic test on reduced scale models

Molyneux, W.G. (author)

The similarity requirements for model tests are established and different possibilities with regard to relaxations of these requirements are examined with the aim of devising an acceptable experimental technique, for representative tests on models of reduced scale. It appears that the representation of heating effects must of necessity be rather...

report 1962

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Numerieke oplossingsmethoden voor de bepaling van temperatuursverdelingen in aerodynamisch verhitte constructies

de Jonge, J.B. (author)

In dit rapport, dat een vervolg is op het NLL rapport TM S.548, wordt de numerieke oplossing van warmtegeleidingsvraagstukken met behulp van differentiemethoden nader bestudeerd. Twee differentiemethoden worden aan de hand van een eenvoudig rekenvoorbeeld vergeleken. Als voorbeeld voor de berekening van temperatutirsverdelingen in aërodynamisch...

report 1961

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An approximate theory of equilibrium one-dimensional steady, and unsteady expanding flows of an ideal dissociating gas

Stalker, R.J. (author)

An analysis has been undertaken of the one-dimensional flow of an ideal dissociating gas in a nozzle, and in unsteady expansion in a constant area tube . Approximate expressions, based on a low temperature assumpt i on , have been derived to predict, in the fermer case, the variation of dissociation fraction and pressure with area ratio, and in...

report 1961