Flight Investigation Of Boundary Layer And Profile Drag Characteristics Of Smooth Wing Sections Of A P 47d Airplane

Author : John A. Zalovcik
Publisher : Unknown
Page : 38 pages
File Size : 43,9 Mb
Release : 1945
Category : Aerodynamics
ISBN : UFL:31262081049743

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Flight Investigation of Boundary-layer and Profile-drag Characteristics of Smooth Wing Sections of a P-47D Airplane by John A. Zalovcik Pdf

Summary: A flight investigation was made of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane. Measurements were made at three stations on the wing: boundary-layer measurements were made on the upper surface of the left wing in the slip-stream at 25 percent semispan; pressure-distribution measurements were made on the upper surface of the left wing at 63 percent semispan; and wake surveys were made at 63 percent semispan of the right wing. The tests were made in straight flight and in turns over a range of conditions in which airplane lift coefficients from 0.15 to 0.68, Reynolds numbers from 7.7 x 106 to 19.7 x 106, and Mach numbers from 0.25 to 0.69 were obtained. The results of the investigation indicated a minimum profile-drag coefficient of 0.0062 for the smooth section at 63 percent semispan. At the highest Mach number attained in the tests, the critical Mach number was exceeded by at least 0.04 with no evidence of compressibility shock losses appearing in the form of increased width of the wake or increased profile-drag coefficient. For flight conditions approaching the critical Mach number, variations in Mach number of as much as 0.17 appeared to have no effect on the profile-drag coefficient. In the slipstream, transition occurred at least as far back as 20 percent chord on the upper surface at low lift coefficients.

Author : John A. Zalovcik,Fred L. Daum
Publisher : Unknown
Page : 22 pages
File Size : 47,5 Mb
Release : 1946
Category : Aerodynamics
ISBN : UFL:31262081049917

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Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint by John A. Zalovcik,Fred L. Daum Pdf

Summary: A flight investigation was made at high speeds to determine the profile drag of a P-47D airplane wing having production surfaces covered with camouflage paint. The profile drag of a wing section somewhat out-board of the flap was determined by means of wake surveys in tests made over a range of airplane lift coefficients from 0.06 to 0.69 and airplane Mach numbers from 0.25 to 0.78. The results of the tests indicated that a minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach numbers less than 0.67. Below the Mach number at which compressibility shock occurred, variations in Mach number of as much as 0.2 appeared to have no effect on profile-drag coefficient. The variation in Reynolds number corresponding to this variation in Mach number, however, was appreciable and may have had some effect on the results obtained. Comparison of the Mach number at which shock losses were first evident in the wake with the critical Mach number indicated that shock was not evident until the critical Mach number was exceeded by at least 0.025.

Author : Anonim
Publisher : Unknown
Page : 612 pages
File Size : 41,7 Mb
Release : 1948
Category : Science
ISBN : UIUC:30112101039847

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Bibliography of Scientific and Industrial Reports by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 664 pages
File Size : 48,7 Mb
Release : 1949
Category : Aeronautics
ISBN : UVA:X004173284

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A Selected Listing of NASA Scientific and Technical Reports for ... by Anonim Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 616 pages
File Size : 49,6 Mb
Release : 1949
Category : Aeronautics
ISBN : MSU:31293201271115

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Index of NACA Technical Publications by United States. National Advisory Committee for Aeronautics Pdf

Author : Anonim
Publisher : Unknown
Page : 984 pages
File Size : 44,7 Mb
Release : 1977
Category : Astronautics
ISBN : MINN:31951D00023604W

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NASA Reference Publication by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 622 pages
File Size : 44,5 Mb
Release : 194?
Category : Aeronautics
ISBN : UFL:31262081528621

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Wartime Report by Anonim Pdf

Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 716 pages
File Size : 48,7 Mb
Release : 2024-07-01
Category : Aeronautics
ISBN : STANFORD:36105024825973

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NACA Wartime Report by United States. National Advisory Committee for Aeronautics Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 274 pages
File Size : 50,8 Mb
Release : 2024-07-01
Category : Aeronautics
ISBN : UOM:39015006078375

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Wartime Report by United States. National Advisory Committee for Aeronautics Pdf

Author : Hans U. Meier,Peter Bradshaw
Publisher : Springer Science & Business Media
Page : 512 pages
File Size : 48,9 Mb
Release : 2012-12-06
Category : Science
ISBN : 9783642829949

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Perspectives in Turbulence Studies by Hans U. Meier,Peter Bradshaw Pdf

The present volume entitled "Perspectives in Turbulence Stud ies" is dedicated to Dr. Ing. E. h. Julius C. Rotta in honour of his 75th birthday. J. C. Rotta, born on January 1, 1912, started his outstanding career in an unusual way, namely in a drawing office (1928 - 1931). At the same time he - as a purely self taught perso- took a correspondence course in airplane construction. From 1934 to 1945 he worked in the aircraft industry on different subjects in the fields of flight mechanics, structures, air craft design, and aerodynamics. In 1945 he moved to Gottingen and worked from that time at the Aerodynamische Versuchsanstalt (AVA, now DFVLR) and the Max-Planck-Institut fur Stromungsforschung (1947-1958), interrupted only by a stay in the U. S. at the Glenn L. Martin Company (1954 - 1955) and a visiting professorship at the Laval University in Quebec, Canada (1956). Already during his activities in industry, Dr. Rotta discovered his special liking for aerodynamics. In Gottingen, he was attracted by Ludwig Prandtl's discussions about problems associated with turbulence and in particular his new contribution to fully developed turbulence, published in 1945. At that time, W. Heisenberg and C. F. v. Weizacker pub lished their results on the energy spectra of isotropic turbu lence at large wave numbers. Since that time his main research interest in reasearch has been in turbulence problems.

Author : R.W. Barnwell,M.Y. Hussaini
Publisher : Springer Science & Business Media
Page : 415 pages
File Size : 43,9 Mb
Release : 2012-12-06
Category : Science
ISBN : 9781461228721

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Natural Laminar Flow and Laminar Flow Control by R.W. Barnwell,M.Y. Hussaini Pdf

Research on laminar flow and its transition to turbulent flow has been an important part of fluid dynamics research during the last sixty years. Since transition impacts, in some way, every aspect of aircraft performance, this emphasis is not only understandable but should continue well into the future. The delay of transition through the use of a favorable pressure gradient by proper body shaping (natural laminar flow) or the use of a small amount of suction (laminar flow control) was recognized even in the early 1930s and rapidly became the foundation of much of the laminar flow research in the U.S. and abroad. As one would expect, there have been many approaches, both theoretical and experimental, employed to achieve the substantial progress made to date. Boundary layer stability theories have been formu lated and calibrated by a good deal of wind tunnel and flight experiments. New laminar now airfoils and wings have been designed and many have been employed in aircraft designs. While the early research was, of necessity, concerned with the design of subsonic aircraft interest has steadily moved to higher speeds including those appropriate to planetary entry. Clearly, there have been substantial advances in our understanding of transition physics and in the development and application of transition prediction methodolo gies to the design of aircraft.

Author : John A. Zalovcik,Richard B. Skoog
Publisher : Unknown
Page : 44 pages
File Size : 52,8 Mb
Release : 1945
Category : Aerodynamics
ISBN : UFL:31262081049800

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Flight Investigation of Boundary-layer Transition and Profile Drag of an Experimental Low-drag Wing Installed on a Fighter-type Airplane by John A. Zalovcik,Richard B. Skoog Pdf

A boundary-layer-transition and profile-drag investigation was conducted in flight by the National Advisory Committee for Aeronautics on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F and supplied by the Army Air Forces. The wing incorporates airfoil section that vary from an NACA 66(215)-1(16.5), a = 1.0 at the plane of symmetry to an NACA 67(115)-213, a = 0.7 at the tip. The surface of the wing as constructed was found to have such a degree of waviness that it had to be refinished in order to obtain the performance generally expected of low-drag airfoils. Measurements were made at a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed. Tests were made in normal flight - that is, in level flight and in shallow dives - at indicated airspeeds ranging from about 150 to 300 miles per hour and in steady turns at 300 miles per hour with normal acceleration from 2g to 4g. These speed and acceleration limits were imposed by structural considerations. The tests in normal flight covered a range of section lift coefficient from about 0.58 to 0.15, of Reynolds number from about 9 x 106 to 18 x 106, and of Mach number from about 0.27 to 0.53. In the tests in turns at 300 miles per hour, the range of section lift coefficient was extended to 0.63.

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 200 pages
File Size : 44,7 Mb
Release : 1947
Category : Electronic
ISBN : UIUC:30112032439538

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Wartime Report Release List by United States. National Advisory Committee for Aeronautics Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 1276 pages
File Size : 40,6 Mb
Release : 1955
Category : Aeronautics
ISBN : RUTGERS:39030037542794

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Technical Note - National Advisory Committee for Aeronautics by United States. National Advisory Committee for Aeronautics Pdf

Author : Richard M. Gundzik,Charles E. Feiler
Publisher : Unknown
Page : 678 pages
File Size : 43,9 Mb
Release : 1954
Category : Alloys
ISBN : STANFORD:36105024831740

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Corrosion of Metals of Construction by Alternate Exposure to Liquid and Gaseous Fluorine by Richard M. Gundzik,Charles E. Feiler Pdf

The corrosion of 3S-0 and 52S-0 aluminum, AISI 347, and 321 stainless steels, "A" nickel, and low-leaded brass has been determined from the weight change of specimens exposed alternately to liquid and gaseous fluorine. Experiments were continued for a total exposure time up to 3 1/2 months. It was found that corrosion is negligible under the conditions of the experiments. No visual differences were observed between those surfaces exposed to the gaseous phase only and those exposed to both the liquid and the gaseous phases.