Item Details

Transonic Wind-Tunnel Tests of an Error-Compensated Static-Pressure Probe

by Francis J. Capone
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
An investigation of the pressure-sensing characteristics of an error-compensated static-pressure probe mounted on the nose section of a missile body has been conducted in the Langley 16-foot transonic tunnel. The probe was free to rotate about its roll axis and was equipped with a vane so that the crossflow velocity component due to angles of attack of sideslip was always alined with the probe's vertical plane of symmetry. The probe was tested in five axial positions with respect to the missile nose at Mach numbers from 0.30 to 1.08 and at angles of attack from -2.7° to 15.3°. The test Reynolds number per foot varied from 1.79 x 10⁶ to 4.05 x 10⁶. Results showed that at a Mach number of 1.00 the static-pressure error decreased from 3.5 percent to 0.8 percent of the free-stream static pressure, as a result of a change in orifice location from 0.15 maximum missile diameter to 0.20 maximum missile diameter forward of the missile nose. Although compensation for pressure-sensing errors due to angles of attack up to 15.3 was maintained at Mach numbers from M = 0.30 to M = 0.50, there was an increase in error with an increase in angle of attack for Mach numbers between M = 0.50 and M = 1.08.
Description
15 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Report Number: L-1562.
  • Document ID: 19980236451.
  • "NASA TN D-961."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "August 1961."
  • Cover title.
  • Includes bibliographical references (p. 6).
Series Statement
NASA technical note ; D-961
Other Forms
Also available via Internet from NASA Technical Reports Server.
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

  • LEADER 03333nam a2200613Ia 4500
    001 011442376
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 070717s1961 dcua bt f000 0 eng d
    024
    8
      
    a| 19980236451
    035
      
      
    a| sdr-uiuc6395706
    035
      
      
    a| (OCoLC)156232447
    040
      
      
    a| FER c| FER
    049
      
      
    a| UIUU
    088
      
      
    a| L-1562
    100
    1
      
    a| Capone, Francis J.
    245
    1
    0
    a| Transonic wind-tunnel tests of an error-compensated static-pressure probe / c| by Francis J. Capone.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
    300
      
      
    a| 15 p. : b| ill. ; c| 26 cm.
    490
      
    0
    a| NASA technical note ; v| D-961
    500
      
      
    a| Report Number: L-1562.
    500
      
      
    a| Document ID: 19980236451.
    500
      
      
    a| "NASA TN D-961."
    500
      
      
    a| "Langley Research Center, Langley Air Force Base, Va."
    500
      
      
    a| "August 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 6).
    520
      
      
    a| An investigation of the pressure-sensing characteristics of an error-compensated static-pressure probe mounted on the nose section of a missile body has been conducted in the Langley 16-foot transonic tunnel. The probe was free to rotate about its roll axis and was equipped with a vane so that the crossflow velocity component due to angles of attack of sideslip was always alined with the probe's vertical plane of symmetry. The probe was tested in five axial positions with respect to the missile nose at Mach numbers from 0.30 to 1.08 and at angles of attack from -2.7° to 15.3°. The test Reynolds number per foot varied from 1.79 x 10⁶ to 4.05 x 10⁶. Results showed that at a Mach number of 1.00 the static-pressure error decreased from 3.5 percent to 0.8 percent of the free-stream static pressure, as a result of a change in orifice location from 0.15 maximum missile diameter to 0.20 maximum missile diameter forward of the missile nose. Although compensation for pressure-sensing errors due to angles of attack up to 15.3 was maintained at Mach numbers from M = 0.30 to M = 0.50, there was an increase in error with an increase in angle of attack for Mach numbers between M = 0.50 and M = 1.08.
    530
      
      
    a| Also available via Internet from NASA Technical Reports Server.
    538
      
      
    a| Mode of access: Internet.
    650
      
    7
    a| Reynolds number. 2| nasat
    650
      
    7
    a| Orifices. 2| nasat
    650
      
    7
    a| Mach number. 2| nasat
    650
      
    7
    a| Angle of attack. 2| nasat
    650
      
    7
    a| Transonic wind tunnels. 2| nasat
    650
      
    7
    a| Errors. 2| nasat
    650
      
    7
    a| Static pressure. 2| nasat
    650
      
    7
    a| Missile bodies. 2| nasat
    650
      
    7
    a| Free flow. 2| nasat
    650
      
    7
    a| Cross flow. 2| nasat
    650
      
    7
    a| Wind tunnel tests. 2| nasat
    650
      
    7
    a| Pressure sensors. 2| nasat
    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.30112106915033 y| 1961 r| pd q| bib

Access online

Google Preview