Item Details

Aerodynamic Loading Characteristics at Mach Numbers From 0.80 to 1.20 of a 1/10-Scale Three-Stage Scout Model

by Thomas C. Kelly
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
Aerodynamic loads results have been obtained in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.80 to 1.20 for a 1/10-scale model of the upper three stages of the Scout vehicle. Tests were conducted through an angle-of-attack range from -8° to 8° at an average test Reynolds number per foot of about 4.0 x 10⁶. Results indicated that the peak negative pressures associated with expansion corners at the nose and transition flare exhibit sizeable variations which occur over a relatively small Mach number range. The magnitude of the variations may cause the critical local loading condition for the full-scale vehicle to occur at a Mach number considerably lower than that at which the maximum dynamic pressure occurs in flight. The addition of protuberances simulating antennas and wiring conduits had slight, localized effects. The lift carryover from the nose and transition flare on the cylindrical portions of the model generally increased with an increase in Mach number.
Description
64 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Report Number: L-1607.
  • Document ID: 19980231071.
  • "NASA TN D-945."
  • "Langley Research Center, Langley Field, Va."
  • "September 1961."
  • Cover title.
  • Includes bibliographical references (p. 7).
Series Statement
NASA technical note ; D-945
Other Forms
Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/11/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980231071_1998388430.pdf.
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Technical Details

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    a| Aerodynamic loading characteristics at Mach numbers from 0.80 to 1.20 of a 1/10-scale three-stage scout model / c| by Thomas C. Kelly.
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    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
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    a| 64 p. : b| ill. ; c| 26 cm.
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    a| NASA technical note ; v| D-945
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    a| Report Number: L-1607.
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    a| Document ID: 19980231071.
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    a| "NASA TN D-945."
    500
      
      
    a| "Langley Research Center, Langley Field, Va."
    500
      
      
    a| "September 1961."
    500
      
      
    a| Cover title.
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    a| Includes bibliographical references (p. 7).
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    a| Aerodynamic loads results have been obtained in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.80 to 1.20 for a 1/10-scale model of the upper three stages of the Scout vehicle. Tests were conducted through an angle-of-attack range from -8° to 8° at an average test Reynolds number per foot of about 4.0 x 10⁶. Results indicated that the peak negative pressures associated with expansion corners at the nose and transition flare exhibit sizeable variations which occur over a relatively small Mach number range. The magnitude of the variations may cause the critical local loading condition for the full-scale vehicle to occur at a Mach number considerably lower than that at which the maximum dynamic pressure occurs in flight. The addition of protuberances simulating antennas and wiring conduits had slight, localized effects. The lift carryover from the nose and transition flare on the cylindrical portions of the model generally increased with an increase in Mach number.
    530
      
      
    a| Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/11/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980231071_1998388430.pdf.
    538
      
      
    a| Mode of access: Internet.
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    7
    a| Transonic wind tunnels. 2| nasat
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    7
    a| Cylindrical bodies. 2| nasat
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    7
    a| Simulation. 2| nasat
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    a| Protuberances. 2| nasat
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    a| Dynamic pressure. 2| nasat
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    7
    a| Critical loading. 2| nasat
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    7
    a| Angle of attack. 2| nasat
    650
      
    7
    a| Military vehicles. 2| nasat
    650
      
    7
    a| Aerodynamic characteristics. 2| nasat
    650
      
    7
    a| Wind tunnel tests. 2| nasat
    650
      
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    a| Launch vehicles (Astronautics) x| Aerodynamics.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106872150 y| 1961 r| pd q| bib

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