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document
Shen, P.S. (author), Jones, D.J. (author)
report 1967
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Khalid, M. (author), Jones, D.J. (author)
This report contains an analysis of the experimental results obtained from four supercritical natural laminar flow (NLF) airfoils investigated in the NAE High Reynolds Number Test Facility. The airfoils have maximum thickness to chord ratios of 0.10, 0.13, 0.16 and 0.21 and were designed for a lift coefficient of CL = 0.6. Their design Mach...
report 1990
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Jones, Harry D. (author)
report 1972
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Jones, J.S. (author)
report 1996
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Moore, K.C. (author), Jones, J.G. (author)
The design of half-ring wing-body combinations with prescribed wing loadings at supersonic speeds is discussed. A particular load distribution, that behaves near a side edge like the square of the distance from the edge, is considered in detail. In addition to finding wing and optimum body shapes, wave and vortex drag and wing pressure...
report 1962
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Jones, C.E. (author)
report 1961
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Shen, P.S. (author), Jones, D.J. (author)
The incompressible, three-dimensional, laminar boundary layer flow on a flat plate about a half-cone protuberance has been investigated bath by experiment in the NAE water tunnel and by analysis using Cooke's small cross-flow momentum integral method. Three half cones of semi-apex angles 7½, 10° and 12½, were tested at a Reynolds number of 2 x...
report 1967
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Jones, D.J. (author), South, J.C. (author)
The method of lines is used in this report for solving one linear, two nonlinear elliptic boundary value problems and a linear eigenvalue problem. An analysis of the stability and convergence is made in the linear cases.
report 1979
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Jones, D.J. (author)
report 1968
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Jones, J.G. (author), Tomlinson, B.N. (author)
Several aspects of the simulation of flight in turbulence are reviewed, including mathematical models of aircraft response to turbulence, models and measured properties of atmospheric turbulence, and the subjective reactions of the human pilot. Pilots appear to be particularly sensitive to the large, intermittent, peaks that occur in the...
report 1971
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Zbrozek, J.K. (author), Jones, J.G. (author)
The buffet loads occurring during a transient incursion into the buffet regime due either to a gust or a manoeuvre are briefly discussed. Review of the experimental evidence suggests that although there are substantial effects of the rate of change of incidence on the value of CLmax there is no real evidence that buffet boundaries behave in the...
report 1965
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Addicott, E.W. (author), Jones, R.W. (author)
An analogue computer programme was derived, making as few approximations as possible, for the calculation of the flight path of an aircraft leaving the end of a ship-borne catapult. Using his 'complete' calculation, it was shown that, for most aircraft, other approximations could be made without significantly impairing the accuracy of the result...
report 1966
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Jones, D.A. (author), Reason, B.R. (author)
The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.
report 1964
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Cooke, J.C. (author), Jones, O.K. (author)
Certain three-dimensional surfaces studied by Townend have the property that at every streamwise section a supersonic air stream is compressed isentropically in the form of a reversed Prandtl-Meyer flow. If all the compressions are centred on points lying on one straight line the flow is conical. Such a surface may be of use as an engine intake....
report 1964
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Jones, J.G. (author)
A method is presented for designing the lower surface of a lifting configuration for high supersonic speeds using the known flow field past a nonlifting circular cone. The leading edge can be prescribed on the conical shock wave and the lower surface is obtained by replacing the stream surface through this leading edge by a solid surface....
report 1963
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Khalid, . (author), Jones, D.J. (author)
Further wind tunnel tests have been carried out on the NAE 10" chord supercritical NLF airfoil NAE 68-060-21:1. This airfoil in previous tests showed very low drag levels when free transition was allowed on the model. In the main part of the current investigation, performed at chord Reynolds number of about 7,9 and 13 million, transition was...
report 1986
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Jones, J.G. (author)
The influence of a discrete atmospheric gust on the response of an aircraft is dependent on two primary parameters, the maximum change in gust velocity w and the gradient distance H. As the response of an aircraft is a function of the gradient distance, different aircraft having maximum response at differing gradient distances, an important...
report 1979
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Jones, J.G. (author)
The response te the lateral oomponent of turbulance of an airoraft with a saturating yaw-damper is investigated. Booton's concept of the equivalent gain of a non-linear element is used in finding the variation of root mean square amplitude of aircraft response with root mean Sqpare gust level. In addition the spectral distortion due to non...
report 1965
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Jones, R.T. (author)
report
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Jones, E.B. (author), Webster, B.N. (author), Birmingham, R.W. (author), Roskilly, A.P. (author)
report
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