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  • 1
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    On the flow processes in sharply inclined and stalled airfoils in parallel movement and rotation (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The purpose of this study is to obtain a deeper insight into the complicated flow processes on airfoils in the region of the buoyancy maxima. To this end calculated and experimental investigations are carried out on a straight stationary, a twisted stationary and a straight rotating rectangular wing. According to the available results the method gives results which can be applied sufficiently for flow applied firmly on all sides for all rotation values. The reliability of the method may be questioned for a flow undergoing transition from the attached to the separated state or for totally separated flow and higher rotation values.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77509 , NAS 1.15:77509
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A new method of evaluating the side wall interference effect on airfoil angle of attack by suction from the side walls (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A quantitative evaluation method of the suction effect from a suction plate on side walls is explained. It is found from wind tunnel tests that the wall interference is basically described by the summation form of wall interferences in the case of two dimensional flow and the interference of side walls.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77722 , NAS 1.15:77722 , NAL-TR-680
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A possibility of avoiding surface roughness due to insects (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Discussion of a method for eliminating turbulence caused by the formation of insect roughness upon the leading edges and fuselage, particularly in aircraft using BLC. The proposed technique foresees the use of elastic surfaces on which insect roughness cannot form. The operational characteristics of highly elastic rubber surface fastened to the wing leading edges and fuselage edges are examined. Some preliminary test results are presented. The technique is seen to be advantageous primarily for short-haul operations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77419 , NAS 1.15:77419 , Feb 01, 1963 - Feb 28, 1963; Junin; Argentina
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Kasprzyk airfoil. The first wind-tunnel tests (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The Kasprzyk slotted flap glider airfoil (the Kasper wing) enabling glider flight at 32 km/h and 0.5 m/sec descent speed was wind tunnel tested in the U.S. The test layout is described and reasons offered for discrepancies between wind tunnel results and Polish in flight data: high induced drag caused by relative size of model wing span and tunnel, by vortex attenuators on the model and their proximity to the tunnel wall, nonsimilarity between flow over a smooth wing and flow over the Kasprzyk wing with bound vortices, obstruction of the tunnel test chamber cross section by the model wing, discrepant Reynolds numbers, and model airfoil aspect ratio much smaller than the prototype. The overall results offer partial confirmation of the Kasprzyk theory, but further in tunnel and in flight studies are recommended.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77757 , NAS 1.15:77757
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Analysis of airfoil transitional separation bubbles (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A previously developed local inviscid-viscous interaction technique for the analysis of airfoil transitional separation bubbles, ALESEP (Airfoil Leading Edge Separation) has been modified to utilize a more accurate windward finite difference procedure in the reversed flow region, and a natural transition/turbulence model has been incorporated for the prediction of transition within the separation bubble. Numerous calculations and experimental comparisons are presented to demonstrate the effects of the windward differencing scheme and the natural transition/turbulence model. Grid sensitivity and convergence capabilities of this inviscid-viscous interaction technique are briefly addressed. A major contribution of this report is that with the use of windward differencing, a second, counter-rotating eddy has been found to exist in the wall layer of the primary separation bubble.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3791 , NAS 1.26:3791
    Format: application/pdf
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  • 6
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    Cold-air performance of compressor-drive turbine of department of energy upgraded automobile gas turbine engine. 3: Performance of redesigned turbine (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The aerodynamic performance of a redesigned compressor drive turbine of the gas turbine engine is determined in air at nominal inlet conditions of 325 K and 0.8 bar absolute. The turbine is designed with a lower flow factor, higher rotor reaction and a redesigned inlet volute compared to the first turbine. Comparisons between this turbine and the originally designed turbine show about 2.3 percentage points improvement in efficiency at the same rotor tip clearance. Two versions of the same rotor are tested: (1) an as cast rotor, and (2) the same rotor with reduced surface roughness. The effect of reducing surface roughness is about one half percentage point improvement in efficiency. Tests made to determine the effect of Reynolds number on the turbine performance show no effect for the range from 100,000 to 500,000.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83627 , E-2044 , DOE/NASA/50194-39 , NAS 1.15:83627 , USAAVSCOM-TR-84-C-7
    Format: application/pdf
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  • 7
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    Kinematics, influence functions and field quantities for disturbance propagation from moving disturbance sources (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A unified method is presented for deriving the influence functions of moving singularities which determine the field quantities in aerodynamics and aeroacoustics. The moving singularities comprise volume and surface distributions having arbitrary orientations in space and to the trajectory. Hence one generally valid formula for the influence functions which reveal some universal relationships and remarkable properties in the disturbance fields. The derivations used are completely consistent with the physical processes in the propagation field, such that treatment renders new descriptions for some standard concepts. The treatment is uniformly valid for subsonic and supersonic Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77410 , NAS 1.15:77410 , DFVLR-FB-83-01
    Format: application/pdf
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  • 8
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    Air intakes for a probative missile of rocket ramjet (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The methods employed to test air intakes for a supersonic guided ramjet powered missile being tested by ONERA are described. Both flight tests and wind tunnel tests were performed on instrumented rockets to verify the designs. Consideration as given to the number of intakes, with the goal of delivering the maximum pressure to the engine. The S2, S4, and S5 wind tunnels were operated at Mach nos. 1.5-3 for the tests, which were compartmentalized into fuselage-intake interaction, optimization of the intake shapes, and the intake performance. Tests were performed on the length and form of the ogive, the presence of grooves, the height of traps in the boundary layer, the types and number of intakes and the lengths and forms of diffusers. Attention was also given to the effects of sideslip, effects of the longitudinal and circumferential positions of the intakes were also examined. Near optimum performance was realized during Mach 2.2 test flights of the prototype rockets.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77407 , NAS 1.15:77407
    Format: application/pdf
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  • 9
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    Profile design for wings and propellers (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: It has now become customary to develop profiles for wings and propellers for a given employment of the aircraft. This is possible because methods and computers are available to study an entire series of variants in comparatively short time. The basic viewpoints for profile design are presented. It is shown that laminarization has its advantages in almost all cases, including the design of a turbine blade and the design of the profile of an airliner. The requirements which profiles have to satisfy are discussed along with the possibilities for increasing lift on profiles.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77785 , NAS 1.15:77785 , Probl. and Develop. Trends in Gen. Aviation Symp.; Mar 24, 1983 - Mar 25, 1983; Friedrichshafen; Germany
    Format: application/pdf
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  • 10
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    Unsteady flow characteristics in the near-wake of a two-dimensional obstacle (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The influence of the characteristics of the boundary layer separation on the formation of vortices and alternate paths in the wake of a bidimensional obstacle at high Reynolds numbers was studied by ultra fast visualization system. It is shown that there are alternate paths for laminar and turbulent flows, with similar flow characteristics. It is found that emission of vortices does not change substantially when the flow passes from laminar to turbulent. A film with a time scale change of 10,000 times illustrates some of the discussed phenomena.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77762 , NAS 1.15:77762 , AAAF-NT-79-08
    Format: application/pdf
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