Item Details

Wind-Tunnel Tests of Seven Static-Pressure Probes at Transonic Speeds

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
Wind-tunnel tests have been conducted to determine the errors of 3 seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 and at angles of attack from -1.7° to 8.4°. The test Reynolds number per foot varied from 3.35 x 10⁶ to 4.05 x 10⁶. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at ±37.5° from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of free-stream static pressure through the test angle-of-attack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of free-stream static pressure.
Description
30 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Report Number: L-1563.
  • Document ID: 19980227993.
  • "NASA TN D-947."
  • "Langley Research Center, Langley Field, Va."
  • "November 1961."
  • Cover title.
  • Includes bibliographical references (p. 8).
Series Statement
NASA technical note ; D-947
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/19980227993_1998386522.pdf.
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

  • LEADER 03150nam a2200577Ia 4500
    001 011443041
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 070417s1961 dcua bt f000 0 eng d
    024
    8
      
    a| 19980227993
    035
      
      
    a| sdr-uiuc6395514
    035
      
      
    a| (OCoLC)123194337
    040
      
      
    a| FER c| FER
    049
      
      
    a| UIUU
    088
      
      
    a| L-1563
    100
    1
      
    a| Capone, Francis J.
    245
    1
    0
    a| Wind-tunnel tests of seven static-pressure probes at transonic speeds / c| by Francis J. Capone.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
    300
      
      
    a| 30 p. : b| ill. ; c| 26 cm.
    490
      
    0
    a| NASA technical note ; v| D-947
    500
      
      
    a| Report Number: L-1563.
    500
      
      
    a| Document ID: 19980227993.
    500
      
      
    a| "NASA TN D-947."
    500
      
      
    a| "Langley Research Center, Langley Field, Va."
    500
      
      
    a| "November 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 8).
    520
      
      
    a| Wind-tunnel tests have been conducted to determine the errors of 3 seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 and at angles of attack from -1.7° to 8.4°. The test Reynolds number per foot varied from 3.35 x 10⁶ to 4.05 x 10⁶. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at ±37.5° from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of free-stream static pressure through the test angle-of-attack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of free-stream static pressure.
    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/19980227993_1998386522.pdf.
    538
      
      
    a| Mode of access: Internet.
    650
      
    7
    a| Rotation. 2| nasat
    650
      
    7
    a| Test ranges. 2| nasat
    650
      
    7
    a| Symmetry. 2| nasat
    650
      
    7
    a| bodies of revolution. 2| nasat
    650
      
    7
    a| Free flow. 2| nasat
    650
      
    7
    a| Wind tunnel tests. 2| nasat
    650
      
    7
    a| Transonic speed. 2| nasat
    650
      
    7
    a| Static pressure. 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.30112106872176 y| 1961 r| pd q| bib

Access online

Google Preview