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Aerodynamic Characteristics And Pressure Distributions For An Executive Jet Baseline Airfoil Section
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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...
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:
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:
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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:
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Book Synopsis Manipulation and Control of Jets in Crossflow by : Ann R. Karagozian
Download or read book Manipulation and Control of Jets in Crossflow written by Ann R. Karagozian and published by Springer Science & Business Media. This book was released on 2003-06-12 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fundamental Non-Reactive Jets in Crossflow and Other Jet Systems; Background on Modeling, Dynamical Systems, and Control; Reactive Jets in Crossflow and Multiphase Jets; Controlled Jets in Crossflow and Control via Jet Systems;
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 Aerodynamic Design of Transport Aircraft by : E. Obert
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Book Synopsis Control of Fluid Flow by : Petros Koumoutsakos
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