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Wind Tunnel Investigation Of The Flow Correction For A Model Mounted Angle Of Attack Sensor At Angles Of Attack From 10 Deg To 110 Deg
Download Wind Tunnel Investigation Of The Flow Correction For A Model Mounted Angle Of Attack Sensor At Angles Of Attack From 10 Deg To 110 Deg full books in PDF, epub, and Kindle. Read online Wind Tunnel Investigation Of The Flow Correction For A Model Mounted Angle Of Attack Sensor At Angles Of Attack From 10 Deg To 110 Deg ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Wind-tunnel Investigation of the Flow Correction for a Model-mounted Angle of Attack Sensor at Angles of Attack from -10 Deg to 110 Deg by :
Download or read book Wind-tunnel Investigation of the Flow Correction for a Model-mounted Angle of Attack Sensor at Angles of Attack from -10 Deg to 110 Deg written by and published by . This book was released on 1979 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1980 with total page 1280 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 1980 with total page 1406 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Determination of Corrections to Flow Direction Sensor Measurements Over an Angle-of-attack Range from 0 Degree to 85 Degrees by :
Download or read book Determination of Corrections to Flow Direction Sensor Measurements Over an Angle-of-attack Range from 0 Degree to 85 Degrees written by and published by . This book was released on 1985 with total page 56 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 1980 with total page 884 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 1980 with total page 1422 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1988 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Initial Experimental Investigation of the Aerodynamic Load on the Wing of a Model Caused by a Blast-induced Gust that Increases the Angle of Attack Into the Stall Region by : Harold B. Pierce
Download or read book Initial Experimental Investigation of the Aerodynamic Load on the Wing of a Model Caused by a Blast-induced Gust that Increases the Angle of Attack Into the Stall Region written by Harold B. Pierce and published by . This book was released on 1955 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: An initial experimental investigation has been completed on the aerodynamic load imposed on the wing of an airplane model by a blast-induced gust which increased the angle of attack well beyond the stall angle. Pressure distributions at intervals of 1 millisecond were derived along the wing chord. Comparison of these distributions with distributions obtained from steady-flow wind-tunnel tests and potential-flow calculations showed that neither of the latter methods was adequate to predict the loads in the transient conditions of the blast. A traveling peak of negative pressure was disclosed that is believed to be of significance for the high angle-of-attack case. It was attributed to a vortex formed by the diffraction of the blast wave around the wing. The normal-force coefficients obtained from the flight pressure distributions were approximately twice those predicted from wind-tunnel tests for the first 12 milliseconds after blast arrival or for about 75 percent of the time the angle of attack was above the stall.
Book Synopsis Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion by : J. F. Herman
Download or read book Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion written by J. F. Herman and published by . This book was released on 1980 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test program and an analytical study were conducted to investigate aerodynamic hysteresis phenomena on the F-4 aircraft. The wind tunnel test was conducted in the Arnold Engineering Development Center (AEDC) Aerodynamic Wind Tunnel (4T) to investigate the source of aerodynamic hysteresis in static aerodynamic data. The wind tunnel test also provided data that were used in a motion simulation study of the effect of hysteresis on predicted aircraft motion. Static longitudinal lateral directional force and moment data and wing pressure data were obtained on a 0.5-scale model (without pylons or external stores) with various simulated leading-edge slats. These data include the effects of Mach number, angle of attack, model movement, and time dependence on the aerodynamic hysteresis characteristics. Data are presented for the Mach number range from 0.7 to 0.95 at angles of attack from -4 to 24 deg at zero deg sideslip angle and for sideslipe angles from -12 to 12 deg at angles of attack of 5, 10, 15, and 20 deg. Six-degrees-of-freedom motion simulation studies were used to assess the effect of hysteresis in the rolling-moment coefficient on the prediction of aircraft motion. Simulations of various flight maneuvers were conducted both with and without hysteresis in the aerodynamic data. (Author).
Book Synopsis Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections by : E. O. Pearson
Download or read book Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-foot-span Fighter-type Wing of NACA 230-series Airfoil Sections written by E. O. Pearson and published by . This book was released on 1945 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Book Synopsis Wind-tunnel Investigation of a Large 35 ̊swept-wing Jet Transport Model with an External-flow Jet-augmented Double-slotted Flap by : Kiyoshi Aoyagi
Download or read book Wind-tunnel Investigation of a Large 35 ̊swept-wing Jet Transport Model with an External-flow Jet-augmented Double-slotted Flap written by Kiyoshi Aoyagi and published by . This book was released on 1971 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests of swept wing jet transport aircraft model with four pod mounted engines under wing and external flow, jet augmented double slotted flap.
Book Synopsis Flow Field Measurements Around an Ogive-cylinder at Angles of Attack Up to 15 Degrees for Mach Numbers 3.5 and 4 by : William C. Ragsdale
Download or read book Flow Field Measurements Around an Ogive-cylinder at Angles of Attack Up to 15 Degrees for Mach Numbers 3.5 and 4 written by William C. Ragsdale and published by . This book was released on 1972 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow field was surveyed at one station (X/D = 6.5) on an ogive- cylinder having a tangent ogive nose with a fineness ratio of 4. The surveys were performed with pitot tubes and cone pressure probes at angles of attack of 0, 5, 10 and 15 degrees for Mach numbers 3.52 and 4.07. Surface static pressures were also measured. The results of the tests are presented in tabular and plotted form. Comparisons are made with inviscid flow fields calculations and with experimental results from other investigations.
Book Synopsis Analysis of Post-support and Wind-tunnel Wall Interference on Flow Field about Subsonic High-lift High-speed Research Configuration by : Wendy B. Lessard
Download or read book Analysis of Post-support and Wind-tunnel Wall Interference on Flow Field about Subsonic High-lift High-speed Research Configuration written by Wendy B. Lessard and published by . This book was released on 2000 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The present study was performed to determine how significant the interference effects of the wind-tunnel model support system and tunnel walls can be for a high-speed configuration during takeoff and landing conditions. A 5-percent scale model of the Technology Concept Airplane was recently tested in the Langley 14- by 22-Foot Subsonic Tunnel. The model was numerically modeled with and without the support and tunnel walls and compared with experimental data. Detailed analysis of the flow provided additional insight concerning what effects the postsupport and tunnel walls had on the flow field. This study revealed that although the overall forces and moments could be experimentally accounted for, the detailed flow features, such as the surface pressure distributions, could not be accurately simulated without including the post in the computations.
Book Synopsis Development of a Flush Airdata Sensing System on a Sharp-nosed Vehicle for Flight at Mach 3 to 8 by : Mark C. Davis
Download or read book Development of a Flush Airdata Sensing System on a Sharp-nosed Vehicle for Flight at Mach 3 to 8 written by Mark C. Davis and published by . This book was released on 2000 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA Dryden Flight Research Center has developed a flush airdata sensing (FADS) system on a sharp-nosed, wedge-shaped vehicle. This paper details the design and calibration of a real-time angle-of-attack estimation scheme developed to meet the onboard airdata measurement requirements for a research vehicle equipped with a supersonic-combustion ramjet engine. The FADS system has been designed to perform in flights at speeds between Mach 3 and Mach 8 and at angles of attack between -6° and 12°. The description of the FADS architecture includes port layout, pneumatic design, and hardware integration. Predictive models of static and dynamic performance are compared with wind-tunnel results across Mach and angle-of-attack range. Results indicate that static angle-of-attack accuracy and pneumatic lag can be adequately characterized and incorporated into a real-time algorithm.
Book Synopsis Computation of Wind Tunnel Wall Effects for Complex Models Using a Low-order Panel Method by : Dale L. Ashby
Download or read book Computation of Wind Tunnel Wall Effects for Complex Models Using a Low-order Panel Method written by Dale L. Ashby and published by . This book was released on 1994 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 by : L. J. Obery
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 written by L. J. Obery and published by . This book was released on 1951 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation to determine the external and internal flow characteristics of a typical ram-jet-inlet configuration of an external-compression type utilizing an isentropic spike and a subsonic diffuser was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel. The model was investigated of a range of mass-flow ratios at angles of attack up to 10 degrees, free-stream Mach numbers of 1.59, 1.79, and 1.99, and a Reynolds number of approximately 2,400,000 based on inlet diameter.
