Item Details

Free-Flight Investigation of Heat Transfer to an Unswept Cylinder Subjected to an Incident Shock and Flow Interference From an Upstream Body at Mach Numbers Up to 5.50

by Howard S. Carter and Robert E. Carr
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 10⁶ to 1.87 x 10⁶. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
Description
34 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19980227751.
  • "NASA TN D-988."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "October 1961."
  • Cover title.
  • Includes bibliographical references (p. 11).
Series Statement
NASA technical note ; D-988
Other Forms
Also available via Internet from NASA Technical Reports Server.
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

  • LEADER 03001cam a2200493Ia 4500
    001 011448587
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 070716s1961 dcua bt f000 0 eng d
    024
    8
      
    a| 19980227751
    035
      
      
    a| sdr-uiuc6395638
    035
      
      
    a| (OCoLC)155848410
    040
      
      
    a| FER c| FER d| FER
    049
      
      
    a| UIUU
    088
      
      
    a| L-879
    100
    1
      
    a| Carter, Howard S.
    245
    1
    0
    a| Free-flight investigation of heat transfer to an unswept cylinder subjected to an incident shock and flow interference from an upstream body at Mach numbers up to 5.50 / c| by Howard S. Carter and Robert E. Carr.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
    300
      
      
    a| 34 p. : b| ill. ; c| 26 cm.
    490
      
    0
    a| NASA technical note ; v| D-988
    500
      
      
    a| Document ID: 19980227751.
    500
      
      
    a| "NASA TN D-988."
    500
      
      
    a| "Langley Research Center, Langley Air Force Base, Va."
    500
      
      
    a| "October 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 11).
    520
      
      
    a| Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 10⁶ to 1.87 x 10⁶. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
    530
      
      
    a| Also available via Internet from NASA Technical Reports Server.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Heat x| Transmission.
    650
      
    0
    a| Aerodynamic heating.
    700
    1
      
    a| Carr, Robert E.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
    2
      
    a| Langley Research Center.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106914895 y| 1961 r| pd q| bib

Access online

Google Preview