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Analysis And Wind Tunnel Tests Of A Probe Used To Sense Altitude Through Measurement Of Static Pressure
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Book Synopsis Analysis and Wind Tunnel Tests of a Probe Used to Sense Altitude Through Measurement of Static Pressure by : K.D. Tillotson
Download or read book Analysis and Wind Tunnel Tests of a Probe Used to Sense Altitude Through Measurement of Static Pressure written by K.D. Tillotson and published by . This book was released on 1982 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis and Wind Tunnel Tests of a Static Pressure Probe Used to Sense Altitude Through Measurement of Static Pressure by : Kenneth Delmer Tillotson
Download or read book Analysis and Wind Tunnel Tests of a Static Pressure Probe Used to Sense Altitude Through Measurement of Static Pressure written by Kenneth Delmer Tillotson and published by . This book was released on 1980 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static pressure probe was tested to determine the feasibility of using the probe, as an integral part of a missile nose, to sense missile altitude. Experiments were conducted at Mach 2.0 and at Mach 1.51. At Mach 2.0, the static pressure probe will perform within altitude specifications of 25,000 feet + or - 2,000 feet at angles of attack ranging from - 8 to + 8 degrees. At Mach 2.0, within an angle-of-attack ranging from 0 to 6 degrees, the probe will measure free stream static pressure within 4 percent; a 4 percent error in measurement is equivalent to an altitude error of 900 feet. The missile nose shock will remain downstream of the probe pressure ports for flight Mach numbers above 1.5. (Author).
Book Synopsis An Analysis of Initial Static Pressure Probe Measurements in a Low-density Hypervelocity Wind Tunnel by : David E. Boylan
Download or read book An Analysis of Initial Static Pressure Probe Measurements in a Low-density Hypervelocity Wind Tunnel written by David E. Boylan and published by . This book was released on 1963 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An initial experimental program was previously conducted to study the problems in using static pressure probes for flow calibration purposes in low- density, hypervelocity wind tunnels with continuous flow. This data is reviewed in the light of more recent data on thermal transpiration. Results indicate that such probes may be used for what might be termed secondary calibrations, but care is required in interpreting the results. The present experiment yielded data which are compared to static pressures calculated from impact- pressure probe calibrations.
Book Synopsis Wind Tunnel Data Analysis Report on Oal 259, Static Probe Tests by : E. A. Bonney
Download or read book Wind Tunnel Data Analysis Report on Oal 259, Static Probe Tests written by E. A. Bonney and published by . This book was released on 1953 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were made using various designs of pressure probes mounted ahead of three different nose designs. These probes included the measurement of static pressure, ram pressure, and angle of attack and yaw in various combinations with each other in an angle of attack range up to 23 degrees. In addition, studies were made of the effect of hole size on the static pressure reading, effect of high angle of attack on these readings, the effect of flow out of the static holes, and the effect of the proximity of a shock wave, and the use of a unique slotted type probe design to minimize variations of static pressure reading with roll angle. It was found that, as the hole sizes were increased from .040 to .125 inches, the static pressure decreased very slightly so as to cause the indicated Mach number (when calculated from measured ram and static pressure) to vary from 1.77 to 1.79 (tunnel M = 1.73) at zero angle of attack. This discrepancy disappears at 6 degrees angle of attack at zero roll angle. A Mach number variation of less than .01 exists up to 5 to 6 degrees angle of attack with the NACA type probe (S). With the hemispherical type probe the indicated Mach number increases with angle of attack at a rate of approximately .01 for every 5 degrees angle of attack up to an angle of 8 degrees, after which it rises slightly more rapidly. (Author).
Download or read book NASA SP. written by and published by . This book was released on 1989 with total page 328 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Collection of Technical Papers by :
Download or read book A Collection of Technical Papers written by and published by . This book was released on 1982 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1993 with total page 712 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Book Synopsis Aeronautical Engineering: A Continuing Bibliography, 1982 Cumulative Index by :
Download or read book Aeronautical Engineering: A Continuing Bibliography, 1982 Cumulative Index written by and published by . This book was released on 1983 with total page 768 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Exploratory Wind Tunnel Tests of a Shock-swallowing Air Data Sensor at a Mach Number of Approximately 1.83 by :
Download or read book Exploratory Wind Tunnel Tests of a Shock-swallowing Air Data Sensor at a Mach Number of Approximately 1.83 written by and published by . This book was released on 1975 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis My Research Journey on Flow Measurements by : Muruga Lal Jeyan Jv
Download or read book My Research Journey on Flow Measurements written by Muruga Lal Jeyan Jv and published by Independently Published. This book was released on 2020-07-03 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A multi-hole conical probe is employed to determine the velocity of the air flow, totaland static pressures of the wind tunnel, wave angle in addition to estimating the noise of the testsegment. It twinkles with the unique qualities of being trouble-free, vigorous with the flexibility tobe applied even in ruthless situations. Our innovative conical wedge type probe is launched bymeans of AUTOCAD and engineered by exploiting the stain less steel material. The pressure holesare situated at the end of the conical probe which is applied to calculate the pressure and flowvelocity of the atmosphere. The novel probe is performed at supersonic settings by the effective useof the proficient Computational Fluid Dynamic Analysis (CFD analysis) software. It dischargesthe task of assessing the enduring competence of the projected probe under a variety of situationslike fixed pressure and temperature along with the velocity of the air flow at different machnumbers.
Book Synopsis Wind Tunnel Test Techniques by : Colin Britcher
Download or read book Wind Tunnel Test Techniques written by Colin Britcher and published by Academic Press. This book was released on 2023-10-20 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed Provides a discussion of similarity laws as well as material on statistical analysis Includes coverage on facility-to-facility and facility-to-CFD correlation Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing
Book Synopsis Pressure Probe Designs for Dynamic Pressure Measurements in a Supersonic Flow Field by :
Download or read book Pressure Probe Designs for Dynamic Pressure Measurements in a Supersonic Flow Field written by and published by . This book was released on 2001 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design and Evaluation of a New Boundary-layer Rake for Flight Testing by : Trong T. Bui
Download or read book Design and Evaluation of a New Boundary-layer Rake for Flight Testing written by Trong T. Bui and published by . This book was released on 2000 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new boundary-layer rake has been designed and built for flight testing on the NASA Dryden Flight Research Center F-15B/Flight Test Fixture. A feature unique to this rake is its curved body, which allows pitot tubes to be more densely clustered in the near-wall region than conventional rakes allow. This curved rake design has a complex three-dimensional shape that requires innovative solid-modeling and machining techniques. Finite-element stress analysis of the new design shows high factors of safety. The rake has passed a ground test in which random vibration measuring 12 g rms was applied for 20 min in each of the three normal directions. Aerodynamic evaluation of the rake has been conducted in the NASA Glenn Research Center 8x6 Supersonic Wind Tunnel at Mach 0-2. The pitiot pressures from the new rake agree with conventional rake data over the range of Mach numbers tested. The boundary-layer profiles computed from the rake data have been shown to have the standard logarithmic-law profile. Skin friction values computed from the rake data using the Clauser plot method agree with the Preston tube results and the van Driest II compressible skin friction correlation to approximately plus/minus 5 percent.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1984 with total page 1278 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1983 with total page 1166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1983 with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:
