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  • 1
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    Low aspect ratio wing code validation experiment (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 10; p. 1744-1752.
    Format: text
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  • 2
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    The relevance of recent advances in unsteady aerodynamics to the space shuttle program (1970)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Prediction of steady and unsteady airloads on space shuttles
    Keywords: AERODYNAMICS
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 223-237
    Format: text
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  • 3
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    Low aspect ratio wing experiment (1994)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: This test was initiated to provide validation data on low aspect ratio wings at transonic speeds. The test was conducted so that the data obtained would be useful in the validation of codes, and all boundary condition data required would be measured as part of the test. During the conduct of the test, the measured quantities were checked for repeatability, and when the data would not repeat, the cause was tracked down and either eliminated or included in the measurement uncertainty. The accuracy of the data was in the end limited by wall imperfections of the wind tunnel in which the test was run.
    Keywords: AERODYNAMICS
    Type: AGARD, A Selection of Experimental Test Cases for the Validation of CFD Codes, Volume 2; 11 p
    Format: text
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  • 4
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    Analysis of aerothermal loads on spherical dome protuberances (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 23; 650-656
    Format: text
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  • 5
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    Results from several experiments at White Sands Missile Range aimed at assessment of falling-sphere density data (1969)
    In:  CASI
    Details
    Publication Date: 2013-06-04
    Description: Evaluation of atmospheric density data obtained by inflatable falling spheres
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON STATUS OF PASSIVE INFLATABLE FALLING-SPHERE TECHNOL. FOR ATMOSPHERIC SENSING TO 100 KM 1969; P 271-279
    Format: application/pdf
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  • 6
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    Effect of thickness on airfoil surface noise (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Noise emission from very small chord and very large chord airfoils was measured with eleven 0.63 cm microphones placed along a horizontal semicircle (4.57 m radius) that was centered at the leading edge of the test airfoil. The noise signals were analyzed by an automated spectrum analyzer which yielded 1/3-octave band sound pressure level spectra for each microphone, and the data were corrected to remove the effects of atmospheric attenuation and jet noise. It is found that the effect of thickness is large and must be accounted for in any fundamental airfoil noise theory that attempts to describe the noise emitted from real airfoils. Incident mean velocity gradients and compressibility must also be taken into account. The effect of thickness increases with frequency, with thick airfoils being quieter than thin ones.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Mar. 198
    Format: text
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  • 7
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    Experimental and analytical investigation of fan flow interaction with downstream struts (1985)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An investigation which was designed to provide insight into the fundamental aspects of fan rotor-downstream strut interaction was undertaken. High response, miniature pressure transducers were embedded in the rotor blades of an experimental fan rig. Five downstream struts were placed at several downstream locations in the discharge flow annulus of the single-stage machine. Significant interaction of the rotor blade surface pressures with the flow disturbance produced by the downstream struts was measured. Several numerical procedures for calculating the quasi-steady rotor response due to downstream flow obstructions were developed. A preliminary comparison of experimental and calculated fluctuating blade pressures on the rotor blades shows general agreement between the experimental and calculated values.
    Keywords: AERODYNAMICS
    Type: NASA-CR-175756 , NAS 1.26:175756 , IR-1
    Format: application/pdf
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  • 8
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    Optimization of multi-element airfoils for maximum lift (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two theoretical methods are presented for optimizing multi-element airfoils to obtain maximum lift. The analyses assume that the shapes of the various high lift elements are fixed. The objective of the design procedures is then to determine the optimum location and/or deflection of the leading and trailing edge devices. The first analysis determines the optimum horizontal and vertical location and the deflection of a leading edge slat. The structure of the flow field is calculated by iteratively coupling potential flow and boundary layer analysis. This design procedure does not require that flow separation effects be modeled. The second analysis determines the slat and flap deflection required to maximize the lift of a three element airfoil. This approach requires that the effects of flow separation from one or more of the airfoil elements be taken into account. The theoretical results are in good agreement with results of a wind tunnel test used to corroborate the predicted optimum slat and flap positions.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt.1; p 237-253
    Format: application/pdf
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  • 9
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    Relationship between the aerodynamic damping derivatives measured as a function of instantaneous angular displacement and the aerodynamic damping derivatives measured as a function of oscillation amplitude (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Aerodynamic damping derivatives measured as function of instantaneous angular displacement and relationship to damping derivatives measured as function of oscillation amplitude
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-2855
    Format: application/pdf
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  • 10
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    Experimental studies of shock wave/wall jet interaction in hypersonic flow (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The interaction between a planar shock wave and a wall jet produced by slot cooling in turbulent hypersonic flow was experimentally studied. Detailed distributions of heat transfer and pressure are obtained in the incident shock/wall jet interaction region for a series of shock strengths and impingement positions for two nozzle heights. The major result is that the cooling film could be readily dispersed by relatively weak incident shocks such that the peak heating in the recompression region was not significantly reduced by even the largest levels of film cooling. Regions of boundary layer separation were induced in the film cooling layer, the size of which first increased and then decreased with increasing film cooling. The size of the separated regions and magnitude of the recompression heating were not strongly influenced by the thickness of the cooling film or point of shock impingement relative to the exit plane of the nozzles.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0607
    Format: text
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