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  • 1
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    Loads on bodies in wakes. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Loads on bodies in wakes resulting from crossflow at submerged body or from wake translation over submerged body, noting dynamic instability
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Forces induced on bodies in free wakes and three-dimensional cavities (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Wind tunnel model tests of forces induced on bodies in free wakes and three dimensional cavities
    Keywords: AERODYNAMICS
    Type: NASA-CR-74998 , LMSC-667990
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Dynamics of separated flow over blunt bodies Technical summary report (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Experimental static loads and quasi-steady methods for determining dynamics of separated flow over blunt bodies
    Keywords: AERODYNAMICS
    Type: NASA-CR-76912
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Analysis of flow separation effects on the dynamics of a large space booster. (1965)
    In:  Other Sources
    Details
    Publication Date: 2019-05-24
    Description: Aerodynamic damping of Saturn-Apollo vehicles dominated by separated flow
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 64-482
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Analysis of flow separation effects on the dynamics of a large space booster (1964)
    In:  Other Sources
    Details
    Publication Date: 2019-05-21
    Description: Flow separation effect on large space booster - saturn i /sa-1/ launch vehicle
    Keywords: SPACE SCIENCES
    Type: AIAA PAPER-64-482
    Format: text
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  • 6
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    Unsteady aerodynamic analysis of space shuttle vehicles. Part 3: Booster interference effects (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of the interference flow field on the space-shuttle boost configuration has been made. The results show that the interference effects can dominate the shuttle aerodynamics. Vortices shed from shock-induced flow separations on the forward portion of the vehicle affect the aerodynamic loads on the aft portion of the booster. Thus, the forebody and aft-body flow fields are coupled. This coupling and the associated time lag due to the finite convection speed of the vortices furnish a mechanism whereby the unsteady aerodynamics can cause undamping of certain low frequency elastic modes of the booster. A preliminary order-of-magnitude analysis of the aeroelastic stability of the shuttle booster indicates that negative aerodynamic damping could occur for at least one bending mode and be of sufficient magnitude to dominate the structural damping. The implication of these results, (with the possibility of undamped oscillations leading to structural failure), is serious enough to warrant further, more detailed analysis.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120124 , LMSC-D352320-PT-3
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  • 7
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    Unsteady aerodynamic analysis of space shuttle vehicles. Part 2: Steady and unsteady aerodynamics of sharp-edged delta wings (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of the steady and unsteady aerodynamics of sharp-edged slender wings has been performed. The results show that slender wing theory can be modified to give the potential flow static and dynamic characteristics in incompressible flow. A semiempirical approximation is developed for the vortex-induced loads, and it is shown that the analytic approximation for sharp-edged slender wings gives good prediction of experimentally determined steady and unsteady aerodynamics at M = 0 and M = 1. The predictions are good not only for delta wings but also for so-called arrow and diamond wings. The results indicate that the effects of delta planform lifting surfaces can be included in a simple manner when determining elastic launch vehicle dynamic characteristics. For Part 1 see (N73-32763).
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120123 , LMSC-D352320-PT-2
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  • 8
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    Review of delta wing space shuttle vehicle dynamics (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The unsteady aerodynamics of the delta planform, high cross range, shuttle orbiter were investigated. It has been found that these vehicles are subject to five unsteady flow phenomena that could compromise the flight dynamics. They are: (1) leeside shock induced separation, (2) sudden leading edge stall, (3) vortex burst, (4) bow shock-flap shock interaction, (5) forebody vorticity. Trajectory shaping is seen as the most powerful means of avoiding the detrimental effects of the stall phenomena. However, stall must be fixed or controlled when traversing the stall region. The other phenomena may be controlled by carefully programmed control deflections and some configuration modification. Ways to alter the occurrence of the various flow conditions are explored.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 861-932
    Format: text
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  • 9
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    Unsteady aerodynamic flow field analysis of the space shuttle configuration. Part 4: 747/orbiter aeroelastic stability (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A quasi-steady analysis of the aeroelastic stability of the lateral (antisymmetric) modes of the 747/orbiter vehicle was accomplished. The interference effect of the orbiter wake on the 747 tail furnishes an aerodynamic undamping contribution to the elastic modes. Likewise, the upstream influence of the 747 tail and aft fuselage on the orbiter beaver-tail rail fairing also is undamping. Fortunately these undamping effects cannot overpower the large damping contribution of the 747 tail and the modes are damped for the configurations analyzed. However, significant interference effects of the orbiter on the 747 tail have been observed in the pitch plane. The high response of the 747 vertical tail in the orbiter wave was also considered. Wind tunnel data points to flapping of the OMS pod wakes as the source of the wake resonance phenomenon.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144335 , LMSC-D057194-PT-4
    Format: application/pdf
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  • 10
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    Unsteady aerodynamic flow field analysis of the space shuttle configuration. Part 3: Unsteady aerodynamics of bodies with concave nose geometries (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of the unsteady aerodynamics of bodies with concave nose geometries was performed. The results show that the experimentally observed pulsating flow on spiked bodies and in forward facing cavities can be described by the developed simple mathematical model of the phenomenon. Static experimental data is used as a basis for determination of the oscillatory frequency of spike-induced flow pulsations. The agreement between predicted and measured reduced frequencies is generally very good. The spiked-body mathematical model is extended to describe the pulsations observed in forward facing cavities and it is shown that not only the frequency but also the pressure time history can be described with the accuracy needed to predict the experimentally observed time average effects. This implies that it should be possible to determine analytically the impact of the flow pulsation on the structural integrity of the nozzles for the jettisoned empty SRM-shells.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144334 , LMSC-D057194-PT-3
    Format: application/pdf
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