Download or read book Baseline Calibration of the NASA Lewis Research Center 8 by 6 Foot Supersonic Wind Tunnel 1991 and 1992 Tests written by and published by . This book was released on 1998 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Lewis 8 By 6 Foot Supersonic Wind Tunnel User Manual written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-29 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: The 8- by 6-Foot Supersonic Wind Tunnel (SWT) at Lewis Research Center is available for use by qualified researchers. This manual contains tunnel performance maps which show the range of total temperature, total pressure, static pressure, dynamic pressure, altitude, Reynolds number, and mass flow as a function of test section Mach number. These maps are applicable for both the aerodynamic and propulsion cycle. The 8- by 6-Foot Supersonic Wind Tunnel is an atmospheric facility with a test section Mach number range from 0.36 to 2.0. General support systems (air systems, hydraulic system, hydrogen system, infrared system, laser system, laser sheet system, and schlieren system are also described as are instrumentation and data processing and acquisition systems. Pretest meeting formats are outlined. Tunnel user responsibility and personal safety requirements are also stated. Soeder, Ronald H. Glenn Research Center...

Download or read book User Manual for NASA Lewis 10 by 10 Foot Supersonic Wind Tunnel Revised written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: This manual describes the 10- by 10-Foot Supersonic Wind Tunnel at the NASA Lewis Research Center and provides information for users who wish to conduct experiments in this facility. Tunnel performance operating envelopes of altitude, dynamic pressure, Reynolds number, total pressure, and total temperature as a function of test section Mach number are presented. Operating envelopes are shown for both the aerodynamic (closed) cycle and the propulsion (open) cycle. The tunnel test section Mach number range is 2.0 to 3.5. General support systems, such as air systems, hydraulic system, hydrogen system, fuel system, and Schlieren system, are described. Instrumentation and data processing and acquisition systems are also described. Pretest meeting formats and schedules are outlined. Tunnel user responsibility and personnel safety are also discussed. Soeder, Ronald H. Glenn Research Center...

Download or read book Aeropropulsion Facilities at the NASA Lewis Research Center written by Lewis Research Center and published by . This book was released on 1995 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Glenn 1 By 1 Foot Supersonic Wind Tunnel User Manual written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-03 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This manual describes the NASA Glenn Research Center's 1 - by 1 -Foot Supersonic Wind Tunnel and provides information for customers who wish to conduct experiments in this facility. Tunnel performance envelopes of total pressure, total temperature, and dynamic pressure as a function of test section Mach number are presented. For each Mach number, maps are presented of Reynolds number per foot as a function of the total air temperature at the test section inlet for constant total air pressure at the inlet. General support systems-such as the service air, combustion air, altitude exhaust system, auxiliary bleed system, model hydraulic system, schlieren system, model pressure-sensitive paint, and laser sheet system are discussed. In addition, instrumentation and data processing, acquisition systems are described, pretest meeting formats and schedules are outlined, and customer responsibilities and personnel safety are addressed.Seablom, Kirk D. and Soeder, Ronald H. and Stark, David E. and Leone, John F. X. and Henry, Michael W.Glenn Research CenterMACH NUMBER; REYNOLDS NUMBER; SUPERSONIC WIND TUNNELS; SUPERSONIC FLOW; TEST CHAMBERS; DATA ACQUISITION; MANUALS; WIND TUNNEL NOZZLES; DYNAMIC PRESSURE; WIND TUNNEL TESTS

Download or read book Cone Probe Rake Design and Calibration for Supersonic Wind Tunnel Models written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 314 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of experimental investigations were conducted at the NASA Langley Unitary Plan Wind Tunnel (UPWT) to calibrate cone-probe rakes designed to measure the flow field on 1-2% scale, high-speed wind tunnel models from Mach 2.15 to 2.4. The rakes were developed from a previous design that exhibited unfavorable measurement characteristics caused by a high probe spatial density and flow blockage from the rake body. Calibration parameters included Mach number, total pressure recovery, and flow angularity. Reference conditions were determined from a localized UPWT test section flow survey using a 10deg supersonic wedge probe. Test section Mach number and total pressure were determined using a novel iterative technique that accounted for boundary layer effects on the wedge surface. Cone-probe measurements were correlated to the surveyed flow conditions using analytical functions and recursive algorithms that resolved Mach number, pressure recovery, and flow angle to within +/-0.01, +/-1% and +/-0.1deg , respectively, for angles of attack and sideslip between +/-8deg. Uncertainty estimates indicated the overall cone-probe calibration accuracy was strongly influenced by the propagation of measurement error into the calculated results. Won, Mark J. Ames Research Center 537-07-20...

Download or read book Flowfield Measurements in the NASA Lewis Research Center 9 By 15 Foot Low Speed Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the NASA Lewis 9- by 15-Foot Low-Speed Wind Tunnel to determine the flow characteristics in the test section during wind tunnel operation. In the investigation, a 20-probe horizontally-mounted Pitot-static flow survey rake was used to obtain cross-sectional total and static pressure surveys at four axial locations in the test section. At each axial location, the cross-sectional flowfield surveys were made by repositioning the Pitot-static flow survey rake vertically. In addition, a calibration of the new wind tunnel rake instrumentation, used to determine the wind tunnel operating conditions, was performed. Boundary laser surveys were made at three axial locations in the test section. The investigation was conducted at tunnel Mach numbers 0.20, 0.15, 0.10, and 0.05. The test section profile results from the investigation indicate that fairly uniform total pressure profiles (outside the test section boundary layer) and fairly uniform static pressure and Mach number profiles (away from the test section walls and downstream of the test section entrance) exist throughout in the wind tunnel test section. Hughes, Christopher E. Glenn Research Center...

Download or read book NASA Lewis 9 By 15 Foot Low Speed Wind Tunnel User Manual written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This manual describes the 9- by 15-Foot Low-Speed Wind Tunnel at the Lewis Research Center and provides information for users who wish to conduct experiments in this atmospheric facility. Tunnel variables such as pressures, temperatures, available tests section area, and Mach number ranges (0.05 to 0.20) are discussed. In addition, general support systems such as air systems, hydraulic system, hydrogen system, laser system, flow visualization system, and model support systems are described. Instrumentation and data processing and acquisition systems are also discussed. Soeder, Ronald H. Glenn Research Center...

Download or read book The NASA Langley 8 Foot Transonic Pressure Tunnel Calibration written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-12 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Langley 8-Foot Transonic Pressure Tunnel is a continuous-flow, variable-pressure wind tunnel with control capability to independently vary Mach number, stagnation pressure, stagnation temperature, and humidity. The top and bottom walls of the test section are axially slotted to permit continuous variation of the test section Mach number from 0.2 to 1.2, the slot-width contour provides a gradient-free test section 50 in. long for Mach numbers equal to or greater than 1.0 and 100 in. long for Mach numbers less than 1.0. The stagnation pressure may be varied from 0.25 to 2.0 atm. The tunnel test section has been recalibrated to determine the relationship between the free-stream Mach number and the test chamber reference Mach number. The hardware was the same as that of an earlier calibration in 1972 but the pressure measurement instrumentation available for the recalibration was about an order of magnitude more precise. The principal result of the recalibration was a slightly different schedule of reentry flap settings for Mach numbers from 0.80 to 1.05 than that determined during the 1972 calibration. Detailed tunnel contraction geometry, test section geometry, and limited test section wall boundary layer data are presented. Brooks, Cuyler W., Jr. and Harris, Charles D. and Reagon, Patricia G. Langley Research Center...

Download or read book NASA Ames Laminar Flow Supersonic Wind Tunnel Lfswt Tests of a 10 Deg Cone at Mach 1 6 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-07 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work is part of the ongoing qualification of the NASA Ames Laminar Flow Supersonic Wind Tunnel (LFSWT) as a low-disturbance (quiet) facility suitable for transition research. A 10 deg cone was tested over a range of unit Reynolds numbers (Re = 2.8 to 3.8 million per foot (9.2 to 12.5 million per meter)) and angles of incidence (O deg to 10 deg) at Mach 1.6. The location of boundary layer transition along the cone was measured primarily from surface temperature distributions, with oil flow interferometry and Schlieren flow visualization providing confirmation measurements. With the LFSWT in its normal quiet operating mode, no transition was detected on the cone in the test core, over the Reynolds number range tested at zero incidence and yaw. Increasing the pressure disturbance levels in the LFSWT test section by a factor of five caused transition onset on the cone within the test core, at zero incidence and yaw. When operating the LFSWT in its normal quiet mode, transition could only be detected in the test core when high angles of incidence (greater than 5 deg) for cones were set. Transition due to elevated pressure disturbances (Tollmien-Schlichting) and surface trips produced a skin temperature rise of order 4 F (2.2 C). Transition due to cross flows on the leeward side of the cone at incidence produced a smaller initial temperature rise of only order 2.5 F (1.4 C), which indicates a slower transition process. We can conclude that these cone tests add further proof that the LFSWT test core is normally low-disturbance (pressure fluctuations greater than 0.1%), as found by associated direct flow quality measurements discussed in this report. Furthermore, in a quiet test environment, the skin temperature rise is sensitive to the type of dominant instability causing transition. The testing of a cone in the LFSWT provides an excellent experiment for the development of advanced transition detection techniques. Wolf, Stephen W. D. and Laub, James A. Ames Research C...

Download or read book Wind Tunnel and Propulsion Test Facilities written by Philip S. Antón and published by Minnesota Historical Society. This book was released on 2004 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: The National Aeronautics and Space Administration's (NASA's) wind tunnel and propulsion test facilities continue to be important to U.S. competitiveness across the military, commercial, and space sectors. Unfortunately, management issues are creating real risks to these facilities. This technical report supports a companion monograph (Wind Tunnel and Propulsion Test Facilities: An Assessment of NASA's Capabilities to Serve National Needs, MG-178-NASA/OSD), providing more detailed data, observations, and conclusions about the future of NASA's wind tunnel and propulsion test facilities.

Download or read book Acoustical Evaluation of the NASA Lewis 9 by 15 Foot Low Speed Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The test section of the NASA Lewis 9- by 15-Foot Low Speed Wind Tunnel was acoustically treated to allow the measurement of acoustic sources located within the tunnel test section under simulated free field conditions. The treatment was designed for high sound absorption at frequencies above 250 Hz and to withstand tunnel airflow velocities up to 0.2 Mach. Evaluation tests with no tunnel airflow were conducted in the test section to assess the performance of the installed treatment. This performance would not be significantly affected by low speed airflow. Time delay spectrometry tests showed that interference ripples in the incident signal resulting from reflections occurring within the test section average from 1.7 dB to 3.2 dB wide over a 500 to 5150 Hz frequency range. Late reflections, from upstream and downstream of the test section, were found to be insignificant at the microphone measuring points. For acoustic sources with low directivity characteristics, decay with distance measurements in the test section showed that incident free field behavior can be measured on average with an accuracy of +/- 1.5 dB or better at source frequencies from 400 Hz to 10 kHz. The free field variations are typically much smaller with an omnidirectional source. Dahl, Milo D. and Woodward, Richard P. Glenn Research Center...

Download or read book Space shuttle wind tunnel testing program summary written by A. M. Whitnah and published by . This book was released on 1984 with total page 536 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Real Time Wall Interference Correction System of the NASA Ames 12 Foot Pressure Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 206 pages. Available in PDF, EPUB and Kindle. Book excerpt: An improved version of the Wall Signature Method was developed to compute wall interference effects in three-dimensional subsonic wind tunnel testing of aircraft models in real-time. The method may be applied to a full-span or a semispan model. A simplified singularity representation of the aircraft model is used. Fuselage, support system, propulsion simulator, and separation wake volume blockage effects are represented by point sources and sinks. Lifting effects are represented by semi-infinite line doublets. The singularity representation of the test article is combined with the measurement of wind tunnel test reference conditions, wall pressure, lift force, thrust force, pitching moment, rolling moment, and pre-computed solutions of the subsonic potential equation to determine first order wall interference corrections. Second order wall interference corrections for pitching and rolling moment coefficient are also determined. A new procedure is presented that estimates a rolling moment coefficient correction for wings with non-symmetric lift distribution. Experimental data obtained during the calibration of the Ames Bipod model support system and during tests of two semispan models mounted on an image plane in the NASA Ames 12 ft. Pressure Wind Tunnel are used to demonstrate the application of the wall interference correction method. Ulbrich, Norbert Ames Research Center NASA/CR-1998-208537, A-98-11989, NAS 1.26:208537 NAS2-13605...

Download or read book Investigation of a Technique for Measuring Dynamic Ground Effect in a Subsonic Wind Tunnel written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-20 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: To better understand the ground effect encountered by slender wing supersonic transport aircraft, a test was conducted at NASA Langley Research Center's 14 x 22 foot Subsonic Wind Tunnel in October, 1997. Emphasis was placed on improving the accuracy of the ground effect data by using a "dynamic" technique in which the model's vertical motion was varied automatically during wind-on testing. This report describes and evaluates different aspects of the dynamic method utilized for obtaining ground effect data in this test. The method for acquiring and processing time data from a dynamic ground effect wind tunnel test is outlined with details of the overall data acquisition system and software used for the data analysis. The removal of inertial loads due to sting motion and the support dynamics in the balance force and moment data measurements of the aerodynamic forces on the model is described. An evaluation of the results identifies problem areas providing recommendations for future experiments. Test results are validated by comparing test data for an elliptical wing planform with an Elliptical wing planform section with a NACA 0012 airfoil to results found in current literature. Major aerodynamic forces acting on the model in terms of lift curves for determining ground effect are presented. Comparisons of flight and wind tunnel data for the TU-144 are presented.Graves, Sharon S.Langley Research CenterGROUND EFFECT (AERODYNAMICS); AERODYNAMIC FORCES; SUBSONIC WIND TUNNELS; WIND TUNNEL TESTS; DATA ACQUISITION; AIRCRAFT DESIGN; AERODYNAMIC CONFIGURATIONS; AIRCRAFT CONFIGURATIONS; SLENDER WINGS; WING PLANFORMS; SUPERSONIC TRANSPORTS; TU-144 AIRCRAFT; VERTICAL MOTION

Download or read book Calibration of the 13 By 13 Inch Adaptive Wall Test Section for the Langley 0 3 Meter Transonic Cryogenic Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 13 by 13 inch adaptive wall test section was installed in the 0.3 Meter Transonic Cryogenic Tunnel circuit. This new test section is configured for 2-D airfoil testing. It has four solid walls. The top and bottom walls are flexible and movable whereas the sidewalls are rigid and fixed. The wall adaptation strategy employed requires the test section wall shapes associated with uniform test section Mach number distributions. Calibration tests with the test section empty were conducted with the top and bottom walls linearly diverged to approach a uniform Mach number distribution. Pressure distributions were measured in the contraction cone, the test section, and the high speed diffuser at Mach numbers from 0.20 to 0.95 and Reynolds numbers from 10 to 100 x 10 (exp 6)/per foot. Mineck, Raymond E. and Hill, Acquilla S. Langley Research Center AIRFOIL PROFILES; CALIBRATING; FLEXIBILITY; FLOW DISTRIBUTION; WIND TUNNEL WALLS; ADAPTIVE CONTROL; CRYOGENIC WIND TUNNELS; MACH NUMBER; PRESSURE DISTRIBUTION; REYNOLDS NUMBER; TRANSONIC WIND TUNNELS...

Download or read book Apollo Wind Tunnel Testing Program written by William C. Moseley (Jr.) and published by . This book was released on 1966 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: