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Book Dhc 6 Twin Otter Tailplane Airfoil Section Testing in the Ohio State University 7x10 Wind Tunnel

Download or read book Dhc 6 Twin Otter Tailplane Airfoil Section Testing in the Ohio State University 7x10 Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: Ice contaminated tailplane stall (ICTS) has been found to be responsible for 16 accidents with 139 fatalities over the last three decades, and is suspected to have played a role in other accidents and incidents. The need for fundamental research in this area has been recognized at three international conferences sponsored by the FAA since 1991. In order to conduct such research, a joint NASA/FAA Tailplane Icing Program was formed in 1994: the Ohio State University has played an important role in this effort. The program employs icing tunnel testing, dry wind tunnel testing, flight testing, and analysis using a six-degrees-of-freedom computer code tailored to this problem. A central goal is to quantify the effect of tailplane icing on aircraft stability and control to aid in the analysis of flight test procedures to identify aircraft susceptibility to ICTS. This report contains the results ot testing of a full scale 2D model of a tailplane section of NASA's Icing Research Aircraft, with and without ice shapes, in an Ohio State University 7 x 10 Low Speed wind tunnel in 1994. The results have been integrated into a comprehensive database of aerodynamic coefficients and stability and control derivatives that will permit detailed analysis of flight test results with the analytical computer program. The testing encompassed a full range of angles of attack and elevator deflections, as well as two velocities to evaluate Reynolds number effects. Lift, drag, pitching moment, and hinge moment coefficients were obtained. In addition. instrumentation for use during flight testing was verified to be effective, all components showing acceptable fidelity. Comparison of clean and iced airfoil results show the ice shapes causing a significant decrease in the magnitude of CLmax (from -1.3 to -0.64) and associated stall angle (from -18.6 deg to -8.2 deg). Furthermore, the ice shapes caused an increase in hinge moment coefficient of approximately 0.02, the change being markedly abrupt

Book Additional Testing of the Dhc 6 Twin Otter Tailplane Iced Airfoil Section in the Ohio State University 7x10 Low Speed Wind Tunnel

Download or read book Additional Testing of the Dhc 6 Twin Otter Tailplane Iced Airfoil Section in the Ohio State University 7x10 Low Speed Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-27 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: The need for fundamental research in Ice Contaminated Tailplane Stall (ICTS) was established through three international conferences sponsored by the FAA. A joint NASA/FAA Tailplane Icing Program was formed in 1994 with the Ohio State University playing a critical role for wind tunnel and analytical research. Two entries of a full-scale 2-dimensional tailplane airfoil model of a DHC-6 Twin Otter were made in The Ohio State University 7x10 ft wind tunnel. This report describes the second test entry that examined additional ice shapes and roughness, as well as airfoil section differences. The addition data obtained in this test fortified the original database of aerodynamic coefficients that permit a detailed analysis of flight test results with an OSU-developed analytical program. The testing encompassed a full range of angles of attack and elevator deflections at flight Reynolds number conditions. Aerodynamic coefficients, C(L), C(M), and C(He), were obtained by integrating static pressure coefficient, C(P), values obtained from surface taps. Comparisons of clean and iced airfoil results show a significant decrease in the tailplane aeroperformance (decreased C(Lmax), decreased stall angle, increased C(He)) for all ice shapes with the grit having the lease affect and the LEWICE shape having the greatest affect. All results were consistent with observed tailplane stall phenomena and constitute an effective set of data for comprehensive analysis of ICTS.Gregorek, Gerald and Dresse, John J. and LaNoe, Karine and Ratvasky, Thomas (Technical Monitor)Glenn Research CenterDE HAVILLAND AIRCRAFT; HORIZONTAL TAIL SURFACES; WIND TUNNEL TESTS; AERODYNAMIC COEFFICIENTS; AIRFOIL PROFILES; AIRCRAFT ICING; AIRCRAFT PERFORMANCE; LOW SPEED WIND TUNNELS; ANGLE OF ATTACK; FLIGHT CONDITIONS; REYNOLDS NUMBER; PRESSURE DISTRIBUTION; SURFACE ROUGHNESS; AIRCRAFT STABILITY; BOUNDARY LAYERS; FULL SCALE TESTS; PITCHING MOMENTS...

Book NASA s Contributions to Aeronautics Flight environment operations flight testing and research

Download or read book NASA s Contributions to Aeronautics Flight environment operations flight testing and research written by and published by . This book was released on 2010 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.

Book NASA FAA Tailplane Icing Program Overview

Download or read book NASA FAA Tailplane Icing Program Overview written by Thomas P. Ratvasky and published by . This book was released on 1999 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA s Contributions to Aeronautics

Download or read book NASA s Contributions to Aeronautics written by Richard Hallion and published by National Aeronautics and Space Administration Headquarters. This book was released on 2010 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.

Book In Flight Aerodynamic Measurements of an Iced Horizontal Tailplane

Download or read book In Flight Aerodynamic Measurements of an Iced Horizontal Tailplane written by Thomas P. Ratvasky and published by . This book was released on 1999 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Collection and Analysis of Wind tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates

Download or read book Collection and Analysis of Wind tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates written by WIlliam R. Bates and published by . This book was released on 1947 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of 19 isolated tail surfaces have been determined by wind-tunnel tests and tests have also been made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. Thes data from these tests have been collected and analyzed.

Book Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers

Download or read book Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1946 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-dimensional data for 24 airfoil sections tested in the 1.31- by 1.74-foot high-speed tunnel at Guidonia, Italy, are presented. The test Mach numbers ranged from 0.40 to 0.94 and Reynolds numbers ranged from 340,000 to 420,000. The results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections.

Book Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics

Download or read book Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics written by John Stack and published by . This book was released on 1931 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of scale and turbulence on the lift and drag of five airfoils, the N.A.C.A. 0006 , the N.A.C.A. 0021, the Clark Y, The U.S.A 35-A, and the U.S.N. P.S.6, hve been investigated in the Variable Density Wind Tunnel. Tests were made over a wide scale for only two different conditions of turbulence.

Book Wind tunnel Investigation of Control surface Characteristics

Download or read book Wind tunnel Investigation of Control surface Characteristics written by H. Page Hoggard and published by . This book was released on 1944 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure-distribution tests have been made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The 15-percent bevel was tested with the bevel corner faired with both large and small radii. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of the horizontal and vertical tail surfaces.

Book The Characteristics of 78 Related Airfoil Sections from Tests in the Variable density Wind Tunnel

Download or read book The Characteristics of 78 Related Airfoil Sections from Tests in the Variable density Wind Tunnel written by Eastman N. Jacobs and published by . This book was released on 1933 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of a large group of related airfoils was made in the N.A.C.A. variable-density wind tunnel at a large value of the Reynolds Number. The tests were made to provide data that may be directly employed for a rational choice of the most suitable airfoil section for a given application. The variation of the aerodynamic characteristics with variations in thickness and mean-line form were therefore systematically studied.

Book Wind tunnel Investigation of Control surface Characteristics

Download or read book Wind tunnel Investigation of Control surface Characteristics written by M. Leroy Spearman and published by . This book was released on 1945 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Wind-tunnel tests have been made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap having a chord 25 percent of the airfoil chord and a balancing tab having a chord 50 percent of the airfoil chord or 200 percent of the flap chord so linked that the tab would deflect at a given rate with respect to the flap. Three linkage ratios were tested on the model. The tests indicated that the flap and tab could be linked to give hinge-moment balance with flap deflection and with angle of attack and yet have greater lift effectiveness than a plain flap of similar size with a conventional balancing tab having a chord 20 percent of the flap chord linked to give hinge-moment balance with flap deflection only.