Several Methods for Aerodynamic Reduction of Static-pressure Sensing Errors for Aircraft at Subsonic, Near-sonic, and Low Supersonic Speeds PDF Download
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Author: Virgil S. Ritchie
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Tests were conducted in transonic wind tunnels to investigate and verify experimentally methods for aerodynamically reducing errors due to sensor position, bow-wave passage, and angle of attack. The results indicated that aerodynamics devices of simple design may be employed to reduce errors in sensing static pressure to less than 0.5 percent at Mach numbers from about 0.40 to 1.15.
Author: Virgil S. Ritchie
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Tests were conducted in transonic wind tunnels to investigate and verify experimentally methods for aerodynamically reducing errors due to sensor position, bow-wave passage, and angle of attack. The results indicated that aerodynamics devices of simple design may be employed to reduce errors in sensing static pressure to less than 0.5 percent at Mach numbers from about 0.40 to 1.15.
Author: Virgil S. Ritchie
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 23
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 344
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 616
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Author: Francis J. Capone
Publisher:
ISBN:
Category : Transonic wind tunnels
Languages : en
Pages : 20
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Book Description
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.
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 852
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Author: Francis J. Capone
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
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.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 590
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
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