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  • AERODYNAMICS  (845)
  • 1980-1984  (845)
  • 1983  (479)
  • 1981  (366)
  • 1
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    Current developments lighter than air systems (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Lighter than air aircraft (LTA) developments and research in the United States and other countries are reviewed. The emphasis in the U.S. is on VTOL airships capable of heavy lift, and on long endurance types for coastal maritime patrol. Design concepts include hybrids which combine heavier than air and LTA components and characteristics. Research programs are concentrated on aerodynamics, flight dynamics, and control of hybrid types.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84744 , NAS 1.15:84744
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental investigation of the flow on the suction side of a thin Delta wing (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Surface oil flow patterns were photographed and pressure distribution measurements were carried out on a sharp edged delta wing of aspect ratio lambda = 1.0 in order to determine the influence of Reynolds number and of vortex breakdown on the flow on the suction side of the wing. The formation of the secondary vortex occurs due to separation of a laminar boundary layer in the front part of the wing and due to separation of a turbulent boundary layer in the rear part of the wing. In the case of turbulent separation, the secondary separation line is closer to the wing leading edge than in the laminar case. The position of the transition depends on the Reynolds number and on the angle of incidence. The breakdown of a vortex above the wing leads to a kink in the secondary separation line.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75897
    Format: application/pdf
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  • 3
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    Rain and deicing experiments in a wind tunnel (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Comments on films of tests simulating rain and ice conditions in a wind tunnel are presented, with the aim of studying efficient methods of overcoming the adverse effects of rain and ice on aircraft. In the experiments, lifesize models and models of the Mirave 4 aircraft were used. The equipment used to simulate rain and ice is described. Different configurations of landing and takeoff under conditions of moderate or heavy rain at variable angles of incidence and of skipping and at velocities varying from 30 to 130 m/sec are reproduced in the wind tunnel. The risks of erosion of supersonic aircraft by the rain during the loitering and approach phases are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77077 , NAS 1.15:77077 , May 29, 1967 - May 31, 1967; Paris
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Separation behavior of boundary layers on three-dimensional wings (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An inverse boundary layer procedure for calculating separated, turbulent boundary layers at infinitely long, crabbing wing was developed. The procedure was developed for calculating three dimensional, incompressible turbulent boundary layers was expanded to adiabatic, compressible flows. Example calculations with transsonic wings were made including viscose effects. In this case an approximated calculation method described for areas of separated, turbulent boundary layers, permitting calculation of this displacement thickness. The laminar boundary layer development was calculated with inclined ellipsoids.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75877
    Format: application/pdf
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  • 5
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    Some characteristic quantities of Karman-Trefftz profiles (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: For von Karman-Trefftz profiles, the characteristics which determine profile shape (profile nose dimensions, maximum thickness and position: tail slope and curvature) are stated as a function of transformation variables using the Timman method. The profile is obtained by iterative deformation of a von Karman profile with known transformation, corresponding as well as possible to the desired profile. The figures and relations which enable a good choice of the required profile are given.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77013 , NAS 1.15:77013
    Format: application/pdf
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  • 6
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    Experimental determination of the inertia constants of an airplane or of a missile (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The possibility to measure the inertia constants of an airplane or of a missile by a unique experimental set up without having to materialize axes of rotation was investigated. It is sufficient to suspend the structure appropriately, to obtain the six natural modes determined by the suspension and to introduce these results as data into a computer. If the structure is very flexible it is necessary to take into account the first natural modes of deformation. Experiments on rigid and flexible models led to precise results and allow consideration of full scale measurements. The final goal is to provide, by a standard ground vibration test completed by the measured characteristics of the suspension modes, the set of data necessary for flutter calculations and for the determination of all the inertia constants.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77767 , NAS 1.15:77767
    Format: application/pdf
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  • 7
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    Reduction of the shock wave intensity by modifying the transonic blade trailing edge (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: It is shown that the shock wave intensity can be decreased by using modified trailing edge configurations to reduce or even completely compensate for the effect of the finite thickness of the trailing edge. A theoretical analysis is presented together with numerical results for two supersonic streams flowing off the trailing edge at different velocities. The analysis is based on an ideal gas model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77029 , NAS 1.15:77029
    Format: application/pdf
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  • 8
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    Flow mechanism and experimental investigation of a rotating stall in transonic compressors (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The flow characteristics of the rotating stall in compressors is studied, and a flow model is developed along with a theoretical calculation method based on vortex theory. A detailed theoretical calculation is completed for a two dimensional flow field in a transonic rotor in a rotating stall, and the result is in good agreement with experimental findings. The oscillograms of time-varying stall characteristic parameters recorded for the onset, growth, and cessation processes of rotating stall are analyzed, and some new flow phenomena deserving of further investigation are discovered. These include serious separation of individual blades, often preceding the onset of rotating stall in compressors with very small blade-camber angles, and periodical variation of the circumferential width of the stall cell with time, accompanied by periodical oscillation of the width of the stall cell in the radial direction of the blade. The circumferential and radial oscillation frequencies are the same.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77373 , NAS 1.15:77373
    Format: application/pdf
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  • 9
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    Wind tunnel investigations of glider fuselages with different waistings and wing arrangements (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The parameters fuselage pinch glider wing arrangement and fuselage leading edge radius of nine glider configurations were investigated in wind tunnel tests. Laminar separation bubbles were found on strongly recessed fuselages. These separations in the juncture between fuselage and wing are essential in the prevention of harmful aerodynamic drag. Drag reduction was measured with increasing pinch and the wing arrangement in the rear. These results are only valid for laminar flow on the fuselage leading edge.
    Keywords: AERODYNAMICS
    Format: application/pdf
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  • 10
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    Laminarization of a boundary layer in a supersonic nozzle by cooling of the surface (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The concept of cooling of the surface of wind tunnel walls in order to laminarize the boundary layer, and thereby eliminate perturbations in the working area, is discussed. Equations are given, which are used to calculate the temperature conditions under which the flow in the boundary layer will be stably laminar.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77341 , NAS 1.15:77341
    Format: application/pdf
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