Searched for: author%3A%22Ohman%2C+L.H.%22
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document
Öhman, L.H. (author)
A momentum analysis has been performed of the flow through a propeller in compressible flow, leading to integral expressions for torque and thrust in terms of local flow quantities such as flow angles, total pressure and Mach number, that can be derived from live-hole pressure probe measurements in the near slipstream. Such data, obtained for...
report 1995
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Ohman, L.H. (author), Brown, D. (author), Chan, Y.Y. (author), Galway, R.D. (author), Hashim, S.M. (author), Khalid, M. (author), Malek, A. (author), Mokry, M. (author), Tang, N. (author), Thain, J. (author)
The NAE 5ftx5ft blowdown wind tunnel has undergone a major upgrade of its transonic testing capabilities. Two entirely new test sections, one for testing two-dimensional models (2D) and one for testing three-dimensional models and reflection plane models (3D), have been constructed. The two test sections are parts of the so-called Roll-in Roll...
report 1990
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Ohman, L.H. (author), Brown, D. (author), Bowker, A.J. (author), Ellis, F.A. (author)
Although the NAE 5 ft X 5 ft Blowdown Wind Tunnel was conceived in the 1950's, with commissioning in 1962/63, it has stood the test of time very well and is still, in 1985, in heavy demand. We may cite three main reasons for this situation: (i) the basic wind tunnel design was fundamentally very sound, (li) the wind tunnel circuit and its...
report 1985
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Lee, B.H.K. (author), Ohman, L.H. (author)
Buffet characteristics of the BGK No. 1 shockless airfoil have been investigated. Fluctuating pressure measurements along the airfoil chord and unsteady force balance data have been obtained in various regions inside the buffet régime close to the onset boundary curve. The Mach number range where buffet intensity reaches high values is...
report 1983
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Kacprzynski, J.J. (author), Ohman, L.H. (author)
A shockless lifting airfoil designed for shockless inviscid flow at M∞ = 0. 75 with CL = 0. 63 was tested at high Reynolds numbers up to 27 X 10σ in design and off-design conditions. The experimental results are compared against theoretical results, showing in general good agreement.
report 1971
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Ohman, L.H. (author)
A general method for performance analysis of satellite launching vehicles bas been developed. The method is based on the establishment of certain mission velocity requirements and assumptions of realistic IOBses due to gravity and aerooynamic drag. Any detailed trajeetory calculations are therefore circumvented. The method is tested against data...
report 1966
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Dixon, R.C. (author), Ohman, L.H. (author)
Aeroelastic effects on the stabilising fins of three high performance sounding rockets have been investigated at supersonic Mach numbers using experimentally determined flexibility coefficients . The aerodynamic farces have been estimated by means of a second - order two - dimensional hybrid theory , taking the wing tip Mach co ne effect into...
report 1965
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Ohman, L.H. (author)
Stability data are presented for two families of bodies ; cone -cylinder and ogive-cylinder configurations with nose fineness ratios of 7 , 5 and 3 and lengths of the cylindrical section up to 15 diameters, for Mach numbers 1.1 to 5. The tabulated results include, apart from the stability derivatives, disturbance velocities and pressure...
report 1964
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Ohman, L.H. (author)
A method of determining the surface flow velocities for arbitrary pointed bodies of revolution in complex supersonic flow, j.e., flow due te constant incidence, constant pitching velocity and constant lateral acceleration, has been derived and a corresponding numerical procedure developed . The method is based on a solution suggested by M. J....
report 1964
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Ohman, L.H. (author)
An analysis of the dynamic behaviour of a ballistic non-rolling missile rapidly ascending through the atmosphere has been performed. Both the boosting and coasting phase have been considered in plane motion. It has been shown that the three original governing equations under certain, yet realistic, conditions can be reduced to a single second...
report 1964
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Ohman, L.H. (author), Dixon, R.C. (author)
Flutter analysis of a rocket fin at Mach numbers from 2 to 7 has been performed. The analysis is based on a number of preassigned mode shapes with piston theory representing the aerodynamic forces. Various mode combinations, effects of reduced stiffness due to kinetic heating, effects of structural damping and thickness effects as given by 2nd...
report 1963
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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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