Transonic data memorandum: Aerofoils having a specified form of upper-surface pressure and distribution Details and comments on design

Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies /

Fischetti, Thomas L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...

Research data supporting "Design Study for a Laminar-Flying-Wing Aircraft": Surface Pressures - LFW aerofoil surface pressure coefficients in the form used for the suction calculation

Saeed, T. I.
Graham, W. R.

April 2015

These files provide the LFW aerofoil surface pressure coefficients in the form used for the suction ...

Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel /

Johnson, William G. (William Garland), 1944-
Eichmann, Otto.
Hill, Acquilla S.
Langley Research Center.

January 1985

Prepared at Langley Research Center.Bibliography: p. 390.Mode of access: Internet

Drag-rise Mach number of aerofoils having a specified form of upper-surface pressure distribution Charts and comments on design

Engineering Sciences Data Unit, London (UK)

January 1971

SIGLELD:3769.95V(ESDU--71019) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

Calculation and measurement of transonic flows over aerofoils with novel rear sections

Ashill, P.R
Royal Aerospace Establishment, Farnborough (United Kingdom)

January 1988

SIGLEAvailable from British Library Document Supply Centre- DSC:8670.19(RAE-TM-AERO--2145) / BLDSC -...

Pressure distribution on wing-body-flap configurations at subsonic speed

Bitomsky, U

January 1993

In 2 volsSIGLEAvailable from British Library Document Supply Centre- DSC:DX178237 / BLDSC - British ...

Transonic data memorandum Axial pressure coefficient distributions for spherically blunted secant ogive forebodies of fineness ratio 1.0, 1.5 and 2.0 at zero incidence in transonic flow

Engineering Sciences Data Unit, London (United Kingdom)

January 1983

SIGLEAvailable from British Library Lending Division - LD:3769.95v(ESDU--83018) / BLDSC - British Li...

A summary of experimental data on wing characteristics at transonic speeds

Nonweiler, T.
Royal Aircraft Establishment, Farnborough (UK)

January 1948

SIGLELD:8678.3(RAE-TM--AERO--1953) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

Hypersonic aerodynamics on flat plates and thin aerofoils

Khorrami, A.F

January 1991

SIGLEAvailable from British Library Document Supply Centre- DSC:D79662 / BLDSC - British Library Doc...

A comparison of two new methods for the design of aerofoils with specific pressure distributions

Vezza, M.
Galbraith, R.A.McD
Glasgow Univ. (United Kingdom). Dept. of Aeronautics and Fluid Mechanics

January 1983

SIGLEAvailable from British Library Lending Division - LD:7620.935(GU-AERO--8303) / BLDSC - British ...

Pressure distributions on some delta wings at M=4

Moore, K.C.
Squire, L.C.
Royal Aircraft Establishment, Farnborough (UK)

January 1980

SIGLELD:8717.806(RAE-TR--80068) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

The vibation analysis of aerofoil section blading

Grigg, R

January 1981

SIGLEAvailable from British Library Document Supply Centre- DSC:D41961/81 / BLDSC - British Library ...

Aerodynamic and heat transfer measurements on blading for a high rim-speed transonic turbine

Wedlake, E.T
Leversuch, N.P.
Harasgama, S.P.
Kingcombe, R.C.
Royal Aircraft Establishment (RAE), Farnborough (United Kingdom)

January 1989

Also publ. as RAE-TM-P--1151Available from British Library Document Supply Centre- DSC:2265.63F(BR--...

Inviscid compressible flow past multi-element aerofoils

Suddhoo, A

January 1985

2 volsSIGLEAvailable from British Library Document Supply Centre- DSC:D67423/86 / BLDSC - British Li...

The experimental and theoretical aerodynamic characteristics of aerofoil sections suitable for remotely piloted vehicles

Render, P.M
Cranfield Inst. of Technology (United Kingdom)

January 1984

SIGLEAvailable from British Library Lending Division - LD:D54086/85 / BLDSC - British Library Docume...

Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies /

Fischetti, Thomas L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...

Research data supporting "Design Study for a Laminar-Flying-Wing Aircraft": Surface Pressures - LFW aerofoil surface pressure coefficients in the form used for the suction calculation

Saeed, T. I.
Graham, W. R.

April 2015

These files provide the LFW aerofoil surface pressure coefficients in the form used for the suction ...

Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel /

Johnson, William G. (William Garland), 1944-
Eichmann, Otto.
Hill, Acquilla S.
Langley Research Center.

January 1985

Prepared at Langley Research Center.Bibliography: p. 390.Mode of access: Internet

Drag-rise Mach number of aerofoils having a specified form of upper-surface pressure distribution Charts and comments on design

Engineering Sciences Data Unit, London (UK)

January 1971

SIGLELD:3769.95V(ESDU--71019) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

Calculation and measurement of transonic flows over aerofoils with novel rear sections

Ashill, P.R
Royal Aerospace Establishment, Farnborough (United Kingdom)

January 1988

SIGLEAvailable from British Library Document Supply Centre- DSC:8670.19(RAE-TM-AERO--2145) / BLDSC -...

Pressure distribution on wing-body-flap configurations at subsonic speed

Bitomsky, U

January 1993

In 2 volsSIGLEAvailable from British Library Document Supply Centre- DSC:DX178237 / BLDSC - British ...

Transonic data memorandum Axial pressure coefficient distributions for spherically blunted secant ogive forebodies of fineness ratio 1.0, 1.5 and 2.0 at zero incidence in transonic flow

Engineering Sciences Data Unit, London (United Kingdom)

January 1983

SIGLEAvailable from British Library Lending Division - LD:3769.95v(ESDU--83018) / BLDSC - British Li...

A summary of experimental data on wing characteristics at transonic speeds

Nonweiler, T.
Royal Aircraft Establishment, Farnborough (UK)

January 1948

SIGLELD:8678.3(RAE-TM--AERO--1953) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

Hypersonic aerodynamics on flat plates and thin aerofoils

Khorrami, A.F

January 1991

SIGLEAvailable from British Library Document Supply Centre- DSC:D79662 / BLDSC - British Library Doc...

A comparison of two new methods for the design of aerofoils with specific pressure distributions

Vezza, M.
Galbraith, R.A.McD
Glasgow Univ. (United Kingdom). Dept. of Aeronautics and Fluid Mechanics

January 1983

SIGLEAvailable from British Library Lending Division - LD:7620.935(GU-AERO--8303) / BLDSC - British ...

Pressure distributions on some delta wings at M=4

Moore, K.C.
Squire, L.C.
Royal Aircraft Establishment, Farnborough (UK)

January 1980

SIGLELD:8717.806(RAE-TR--80068) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

The vibation analysis of aerofoil section blading

Grigg, R

January 1981

SIGLEAvailable from British Library Document Supply Centre- DSC:D41961/81 / BLDSC - British Library ...

Aerodynamic and heat transfer measurements on blading for a high rim-speed transonic turbine

Wedlake, E.T
Leversuch, N.P.
Harasgama, S.P.
Kingcombe, R.C.
Royal Aircraft Establishment (RAE), Farnborough (United Kingdom)

January 1989

Also publ. as RAE-TM-P--1151Available from British Library Document Supply Centre- DSC:2265.63F(BR--...

Inviscid compressible flow past multi-element aerofoils

Suddhoo, A

January 1985

2 volsSIGLEAvailable from British Library Document Supply Centre- DSC:D67423/86 / BLDSC - British Li...

The experimental and theoretical aerodynamic characteristics of aerofoil sections suitable for remotely piloted vehicles

Render, P.M
Cranfield Inst. of Technology (United Kingdom)

January 1984

SIGLEAvailable from British Library Lending Division - LD:D54086/85 / BLDSC - British Library Docume...

Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies /

Fischetti, Thomas L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...

Research data supporting "Design Study for a Laminar-Flying-Wing Aircraft": Surface Pressures - LFW aerofoil surface pressure coefficients in the form used for the suction calculation

Saeed, T. I.
Graham, W. R.

April 2015

These files provide the LFW aerofoil surface pressure coefficients in the form used for the suction ...

Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel /

Johnson, William G. (William Garland), 1944-
Eichmann, Otto.
Hill, Acquilla S.
Langley Research Center.

January 1985

Prepared at Langley Research Center.Bibliography: p. 390.Mode of access: Internet

Transonic data memorandum: Aerofoils having a specified form of upper-surface pressure and distribution Details and comments on design

Abstract

Extracted data

Transonic data memorandum: Aerofoils having a specified form of upper-surface pressure and distribution Details and comments on design

Abstract

Extracted data

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