Exploratory Wind Tunnel Tests Of A Shock Swallowing Air Data Sensor At A Mach Number Of Approximately 1 83
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Exploratory Wind Tunnel Tests Of A Shock Swallowing Air Data Sensor At A Mach Number Of Approximately 1 83
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Author :
language : en
Publisher:
Release Date : 1975
Exploratory Wind Tunnel Tests Of A Shock Swallowing Air Data Sensor At A Mach Number Of Approximately 1 83 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with categories.
Wind Tunnel Data Analysis Report On Oal 259 Static Probe Tests
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Author : E. A. Bonney
language : en
Publisher:
Release Date : 1953
Wind Tunnel Data Analysis Report On Oal 259 Static Probe Tests written by E. A. Bonney and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with categories.
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).
Wind Tunnel Flight Data Correlation U
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Author : James A. Behal
language : en
Publisher:
Release Date : 1971
Wind Tunnel Flight Data Correlation U written by James A. Behal and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Buffeting (Aerodynamics) categories.
A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
An Analysis Of Initial Static Pressure Probe Measurements In A Low Density Hypervelocity Wind Tunnel
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Author : David E. Boylan
language : en
Publisher:
Release Date : 1963
An Analysis Of Initial Static Pressure Probe Measurements In A Low Density Hypervelocity Wind Tunnel written by David E. Boylan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with Boundary layer categories.
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.
Wind Tunnel Investigation Of A Flush Airdata System At Mach Numbers From 0 7 To 1 4
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Author :
language : en
Publisher:
Release Date : 1990
Wind Tunnel Investigation Of A Flush Airdata System At Mach Numbers From 0 7 To 1 4 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with categories.
Exploratory Tests For Airplane Stability And Control Effectiveness In A Low Density Wind Tunnel At Mach Numbers Of 3 4 5 And 6
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Author :
language : en
Publisher:
Release Date : 1966
Exploratory Tests For Airplane Stability And Control Effectiveness In A Low Density Wind Tunnel At Mach Numbers Of 3 4 5 And 6 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with categories.
High Speed Wind Tunnel Testing
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Author : Alan Pope
language : en
Publisher: John Wiley & Sons
Release Date : 1965-01-15
High Speed Wind Tunnel Testing written by Alan Pope and has been published by John Wiley & Sons this book supported file pdf, txt, epub, kindle and other format this book has been release on 1965-01-15 with Science categories.
Wind Tunnel Tests At Supersonic Mach Numbers To Determine Heat Transfer Coefficients In The Shock Wave Boundary Layer Interaction Region On A Plane Surface
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Author : Lawrence R. Kelley
language : en
Publisher:
Release Date : 1962
Wind Tunnel Tests At Supersonic Mach Numbers To Determine Heat Transfer Coefficients In The Shock Wave Boundary Layer Interaction Region On A Plane Surface written by Lawrence R. Kelley and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with categories.
The objective was to provide experimentallydetermined heat transfer coefficients on a flatplate model to find a correlation between the heat transfer coefficients in the shock waveboundary layer interaction zone and such quantities as the effective Reynolds number, the free stream Mach number, and the strength of the wave. The tests were conducted at Mach 3.0 and 5.0 in two different wind tunnel circuits. The Mach 3.0 tests were performed using the Mach 3-4 variablegeometry nozzle, while the Mach 5.0 tests were performed with the Mach 4-6 variable-geometry nozzle. Both of these wind tunnel circuits have test sections approximately 21.5 inches square. Heat transfer coefficients at several stations were determined by measuring the amount of electrical power input required by nickel-chrome heating elements to maintain a given equilibrium temperature on the elements. The measurement was made for three or four different equilibrium temperatures, and the rate of change of power input with respect to the equilibrium temperature was then used to represent the heat transfer coefficient at that given station. (Author).
Wind Tunnel Investigation Of An All Flush Orifice Air Data System For A Large Subsonic Aircraft
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Author : Terry J. Larson
language : en
Publisher:
Release Date : 1980
Wind Tunnel Investigation Of An All Flush Orifice Air Data System For A Large Subsonic Aircraft written by Terry J. Larson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Air speed categories.
Exploratory Studies Of A Low Y High Mach Number Wind Tunnel Using Freon 14 As The Working Fluid
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Author : Albert R. George
language : en
Publisher:
Release Date : 1961
Exploratory Studies Of A Low Y High Mach Number Wind Tunnel Using Freon 14 As The Working Fluid written by Albert R. George and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with categories.