Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Aerodynamic loads on an isolated shrouded-propeller configuration of angles of attack from -10 degrees to 110 degrees /

Grunwald, Kalman J.
Goodson, Kenneth W.
United States. National Aeronautics and Space Administration.

Cover title."January 1962."Aerodynamics, aircraft; Aircraft; Propulsion systems, air-jet.Includes bi...

A note on the drag due to lift of delta wings at mach numbers up to 2.0 /

Osborne, Robert S.
Kelly, Thomas C.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics, aircraft; Aircraft.Includes bibliographical references.Mod...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).Mode of access: Internet

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.Mode of access: Internet

The aerodynamic characteristics of several thick delta wings at Mach numbers to 6 and angles of attack 50° /

McDevitt, John B.
Rakich, John V.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1960

"March 1960."Cover title.Includes bibliographical references (p. 26).Mode of access: Internet

Pressure measurements obtained in flight at transonic speeds for a conically cambered delta wing /

Keener, Earl R.
Flight Research Center (U.S.)

January 1959

"October 1959."Cover title.Includes bibliographical references (p. 14-15).Mode of access: Internet

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

An analysis of the delta-wing hypersonic stability and control behavior at angles of attack between 30 degrees and 90 degrees

Fetterman, David E.
Neal, Luther.
United States. National Aeronautics and Space Administration.

Cover title."March 1963."Includes bibliographical references.Mode of access: Internet

Pressure measurements on two 60° swept delta wings with blunt leading edges and dihedral angles of 0° and 45° at a Mach number of 4.95. Calvin Stainback.

Stainback, P. Calvin.
United States. National Aeronautics and Space Administration.

January 1962

Cover title."April 1962."Aerodynamics, aircraft; Aerodynamics, missiles; Fluid mechanics; Stresses a...

Preliminary base pressures obtained from the X-15 airplane at mach numbers from 1.1 to 3.2 /

Saltzman, Edwin J.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Aerodynamics, aircraft;Aerodynamics, missiles and space vehicles; Vehicle ...

Experimental determination of the pressure distribution on a rectangular wing oscillating in the first bending mode for mach numbers from 0.24 to 1.30 /

Lessing, Henry C.
Menees, Gene P.
Troutman, John L.
United States. National Aeronautics and Space Administration.

Cover title."December 1960."Aerodynamics, aircraft; Stresses and loads.Includes bibliographical refe...

Pressure distribution of a 0.0667-scale model of the X-15 airplane for an angle-of-attack range of 0° to 28° at mach numbers of 2.30, 288, and 4.65 /

Hodge, B. Leon.
Burbank, Paige B.
United States. National Aeronautics and Space Administration.

"May 1960."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

Pressure measurements on sharp and blunt 5 degreee and 15 degree-half-angle cones at mach number 3.86 and angles of attack to 100 degrees /

Amick, James L.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibl...

Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

High-subsonic-speed investigation of the static longitudinal aerodynamic characteristics of several delta-wing configurations for angles of attack from 0° to 90° /

Spencer, Bernard, 1932-
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"December 1959."Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Aerodynamic loads on an isolated shrouded-propeller configuration of angles of attack from -10 degrees to 110 degrees /

Grunwald, Kalman J.
Goodson, Kenneth W.
United States. National Aeronautics and Space Administration.

Cover title."January 1962."Aerodynamics, aircraft; Aircraft; Propulsion systems, air-jet.Includes bi...

A note on the drag due to lift of delta wings at mach numbers up to 2.0 /

Osborne, Robert S.
Kelly, Thomas C.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics, aircraft; Aircraft.Includes bibliographical references.Mod...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).Mode of access: Internet

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.Mode of access: Internet

The aerodynamic characteristics of several thick delta wings at Mach numbers to 6 and angles of attack 50° /

McDevitt, John B.
Rakich, John V.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1960

"March 1960."Cover title.Includes bibliographical references (p. 26).Mode of access: Internet

Pressure measurements obtained in flight at transonic speeds for a conically cambered delta wing /

Keener, Earl R.
Flight Research Center (U.S.)

January 1959

"October 1959."Cover title.Includes bibliographical references (p. 14-15).Mode of access: Internet

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

An analysis of the delta-wing hypersonic stability and control behavior at angles of attack between 30 degrees and 90 degrees

Fetterman, David E.
Neal, Luther.
United States. National Aeronautics and Space Administration.

Cover title."March 1963."Includes bibliographical references.Mode of access: Internet

Pressure measurements on two 60° swept delta wings with blunt leading edges and dihedral angles of 0° and 45° at a Mach number of 4.95. Calvin Stainback.

Stainback, P. Calvin.
United States. National Aeronautics and Space Administration.

January 1962

Cover title."April 1962."Aerodynamics, aircraft; Aerodynamics, missiles; Fluid mechanics; Stresses a...

Preliminary base pressures obtained from the X-15 airplane at mach numbers from 1.1 to 3.2 /

Saltzman, Edwin J.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Aerodynamics, aircraft;Aerodynamics, missiles and space vehicles; Vehicle ...

Experimental determination of the pressure distribution on a rectangular wing oscillating in the first bending mode for mach numbers from 0.24 to 1.30 /

Lessing, Henry C.
Menees, Gene P.
Troutman, John L.
United States. National Aeronautics and Space Administration.

Cover title."December 1960."Aerodynamics, aircraft; Stresses and loads.Includes bibliographical refe...

Pressure distribution of a 0.0667-scale model of the X-15 airplane for an angle-of-attack range of 0° to 28° at mach numbers of 2.30, 288, and 4.65 /

Hodge, B. Leon.
Burbank, Paige B.
United States. National Aeronautics and Space Administration.

"May 1960."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

Pressure measurements on sharp and blunt 5 degreee and 15 degree-half-angle cones at mach number 3.86 and angles of attack to 100 degrees /

Amick, James L.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibl...

Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

High-subsonic-speed investigation of the static longitudinal aerodynamic characteristics of several delta-wing configurations for angles of attack from 0° to 90° /

Spencer, Bernard, 1932-
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"December 1959."Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Aerodynamic loads on an isolated shrouded-propeller configuration of angles of attack from -10 degrees to 110 degrees /

Grunwald, Kalman J.
Goodson, Kenneth W.
United States. National Aeronautics and Space Administration.

Cover title."January 1962."Aerodynamics, aircraft; Aircraft; Propulsion systems, air-jet.Includes bi...

A note on the drag due to lift of delta wings at mach numbers up to 2.0 /

Osborne, Robert S.
Kelly, Thomas C.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics, aircraft; Aircraft.Includes bibliographical references.Mod...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).Mode of access: Internet

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Abstract

Extracted data

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Abstract

Extracted data

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