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Aerodynamic Characteristics And Pressure Distributions For An Executive Jet Baseline Airfoil Section
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Book Synopsis Aerodynamic Characteristics and Pressure Distributions for an Executive-jet Baseline Airfoil Section by : Dennis O. Allison
Download or read book Aerodynamic Characteristics and Pressure Distributions for an Executive-jet Baseline Airfoil Section written by Dennis O. Allison and published by . This book was released on 1993 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722927851 Total Pages :112 pages Book Rating :4.9/5 (278 download)
Book Synopsis Aerodynamic Characteristics and Pressure Distributions for an Executive-Jet Baseline Airfoil Section by : National Aeronautics and Space Administration (NASA)
Download or read book Aerodynamic Characteristics and Pressure Distributions for an Executive-Jet Baseline Airfoil Section 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 wind tunnel test of an executive-jet baseline airfoil model was conducted in the adaptive-wall test section of the NASA Langley 0.3-Meter Transonic Cryogenic Tunnel. The primary goal of the test was to measure airfoil aerodynamic characteristics over a wide range of flow conditions that encompass two design points. The two design Mach numbers were 0.654 and 0.735 with corresponding Reynolds numbers of 4.5 x 10(exp 6) and 8.9 x 10(exp 6) based on chord, respectively, and normal-force coefficients of 0.98 and 0.51, respectively. The tests were conducted over a Mach number range from 0.250 to 0.780 and a chord Reynolds number range from 3 x 10(exp 6) to 18 x 10(exp 6). The angle of attack was varied from -2 deg to a maximum below 10 deg with one exception in which the maximum was 14 deg for a Mach number of 0.250 at a chord Reynolds number of 4.5 x 10(exp 6). Boundary-layer transition was fixed at 5 percent of chord on both the upper and lower surfaces of the model for most of the test. The adaptive-wall test section had flexible top and bottom walls and rigid sidewalls. Wall interference was minimized by the movement of the adaptive walls, and the airfoil aerodynamic characteristics were corrected for any residual top and bottom wall interference. Allison, Dennis O. and Mineck, Raymond E. Langley Research Center AERODYNAMIC CHARACTERISTICS; AERODYNAMIC INTERFERENCE; AIRFOIL PROFILES; BOUNDARY LAYER TRANSITION; FLOW CHARACTERISTICS; PRESSURE DISTRIBUTION; WIND TUNNEL TESTS; ANGLE OF ATTACK; CRYOGENIC WIND TUNNELS; MACH NUMBER; REYNOLDS NUMBER; TRANSONIC WIND TUNNELS; WALL FLOW...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722951566 Total Pages :124 pages Book Rating :4.9/5 (515 download)
Book Synopsis Assessment of Dual-Point Drag Reduction for an Executive-Jet Modified Airfoil Section by : National Aeronautics and Space Administration (NASA)
Download or read book Assessment of Dual-Point Drag Reduction for an Executive-Jet Modified Airfoil Section 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 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents aerodynamic characteristics and pressure distributions for an executive-jet modified airfoil and discusses drag reduction relative to a baseline airfoil for two cruise design points. A modified airfoil was tested in the adaptive-wall test section of the NASA Langley 0.3-Meter Transonic Cryogenic Tunnel (0.3-m TCT) for Mach numbers ranging from 0.250 to 0.780 and chord Reynolds numbers ranging from 3.0 x 10(exp 6) to 18.0 x 10(exp 6). The angle of attack was varied from minus 2 degrees to almost 10 degrees. Boundary-layer transition was fixed at 5 percent of chord on both the upper and lower surfaces of the model for most of the test. The two design Mach numbers were 0.654 and 0.735, chord Reynolds numbers were 4.5 x 10(exp 6) and 8.9 x 10(exp 6), and normal-force coefficients were 0.98 and 0.51. Test data are presented graphically as integrated force and moment coefficients and chordwise pressure distributions. The maximum normal-force coefficient decreases with increasing Mach number. At a constant normal-force coefficient in the linear region, as Mach number increases an increase occurs in the slope of normal-force coefficient versus angle of attack, negative pitching-moment coefficient, and drag coefficient. With increasing Reynolds number at a constant normal-force coefficient, the pitching-moment coefficient becomes more negative and the drag coefficient decreases. The pressure distributions reveal that when present, separation begins at the trailing edge as angle of attack is increased. The modified airfoil, which is designed with pitching moment and geometric constraints relative to the baseline airfoil, achieved drag reductions for both design points (12 and 22 counts). The drag reductions are associated with stronger suction pressures in the first 10 percent of the upper surface and weakened shock waves. Allison, Dennis O. and Mineck, Raymond E. Langley Research Center AIRFOIL PROFILES; ANGLE OF ATTACK; BOUNDARY LAYER TRANSITION; DRAG RE...
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 1995 with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalogue, United States Public Documents by :
Download or read book Monthly Catalogue, United States Public Documents written by and published by . This book was released on 1994-12 with total page 950 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 1994 with total page 744 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Assessment of Dual-point Drag Reduction for an Executive-jet Modified Airfoil Section by : Dennis O. Allison
Download or read book Assessment of Dual-point Drag Reduction for an Executive-jet Modified Airfoil Section written by Dennis O. Allison and published by . This book was released on 1996 with total page 124 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 1995 with total page 1686 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 Effects of Forward Contour Modification on the Aerodynamic Characteristics of the NACA 641-212 Airfoil Section by : Raymond Morton Hicks
Download or read book Effects of Forward Contour Modification on the Aerodynamic Characteristics of the NACA 641-212 Airfoil Section written by Raymond Morton Hicks and published by . This book was released on 1975 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of an 11-percent-thick Symmetrical Supercritical Airfoil at Mach Numbers Between 0.30 and 0.85 by :
Download or read book Aerodynamic Characteristics of an 11-percent-thick Symmetrical Supercritical Airfoil at Mach Numbers Between 0.30 and 0.85 written by and published by . This book was released on 1969 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections by : Carl Kaplan
Download or read book A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections written by Carl Kaplan and published by . This book was released on 1945 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Determination of the Pressure Distribution and Aerodynamic Characteristics of Airfoils by Means of Electrical Equipotential Lines by : Harry M. Flake
Download or read book The Determination of the Pressure Distribution and Aerodynamic Characteristics of Airfoils by Means of Electrical Equipotential Lines written by Harry M. Flake and published by . This book was released on 1942 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of Aerodynamic Characteristics and Wing Pressure Distributions of an Airplane with Variable-sweep Wings Modified for Laminar Flow by : James B. Hallissy
Download or read book Wind-tunnel Investigation of Aerodynamic Characteristics and Wing Pressure Distributions of an Airplane with Variable-sweep Wings Modified for Laminar Flow written by James B. Hallissy and published by . This book was released on 1989 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Enginnering: A Cumulative Index to a Continuing Bibliography (supplement 312) by :
Download or read book Aeronautical Enginnering: A Cumulative Index to a Continuing Bibliography (supplement 312) written by and published by . This book was released on 1994 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Aerodynamic Characteristics of an Airfoil Optimized for Maximum Lift Coefficient by : Gene J. Bingham
Download or read book Low-speed Aerodynamic Characteristics of an Airfoil Optimized for Maximum Lift Coefficient written by Gene J. Bingham and published by . This book was released on 1972 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics, Temperature, and Noise Measurements of a Large-scale External-flow Jet-augmented-flap Model with Turbojet Engines Operating by : Marvin P. Fink
Download or read book Aerodynamic Characteristics, Temperature, and Noise Measurements of a Large-scale External-flow Jet-augmented-flap Model with Turbojet Engines Operating written by Marvin P. Fink and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.
