Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry /

Some factors affecting the variation of pitching moment with sideslip of aircraft configurations /

Polhamus, Edward C.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 115. ...

Control hinge-movement and effectiveness characteristics of several interchangeable tip controls on a 60©� delta wing at Mach numbers of 1.41, 1.62, and 1.96 /

Morris, Odell A.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel /

Hasel, Lowell E.
Sinclair, Archibald R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

January 1950

"April 7, 1950; Declassified May 29, 1959."Includes bibliographical references (p. 14).Mode of acces...

Calculated effects of the lateral acceleration derivatives on the dynamic lateral stability of a delta-wing airplane /

Campbell, John P.
Woodling, Carroll H.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

"Classification changed to unclassified ..."--Stamped on cover."Confidential.""January 25, 1955."Cov...

An experimental and theoretical investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic characteristics in sideslip of an unswept, untapered tail assembly /

Wiley, Harleth G.
Riley, Donald R.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Wind-tunnel investigation at high subsonic speeds of the effect of spoiler profile on the lateral control characteristics of a wing-fuselage combination winter quarter-chord line swept back 32.6©� and NACA 65A006 airfoil section /

Johnson, Harold S.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Comparison of full-scale lift and drag characteristics of the x-15 airplane with wind-tunnel results and theory /

Hopkins, Edward J.
Saltzman, Edwin J.
Fetterman, David E.
Flight Research Center (U.S.)
Langley Research Center.
Ames Research Center.

January 1962

"Classification changed to unclassified by authority of NASA CCN number 14, dated April 21, 1965."Ma...

Wind-tunnel investigation at low speed of the effect of varying the ratio of body diameter to wing span from 0.1 to 0.8 on the aerodynamic characteristics in pitch of the 45©� sweptback-wing--body combination /

Johnson, Harold S.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Jet effects on longitudinal trim of an airplane configuration measured at Mach numbers between 1.2 and 1.8 /

Peck, Robert F.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 121. ...

Investigation at transonic speeds of the hinge-moment characteristics of a 1/8-scale model of the X-1E aileron /

Moseley, William C., Jr.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Effects of an inset tab on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60©� delta wing at Mach numbers from 0.75 to 1.96 /

Guy, Lawrence D. (Lawrence Duncan), 1921-
Brown, Hoyt V.
United States. National Advisory Committee for Aeronautics.

"Classification changed to unclassified, authority: NASA publication annoucement no. 3, effective da...

Aerodynamic load measurements and opening characteristics of automatic leading-edge slats on a 45©� sweptback wing at transonic speeds /

Arabian, Donald D.
Reid, Charles F., Jr.
Runckel, Jack F.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on a tapered sweptback wing at Mach numbers between 0.6 and 1.4 /

Schult, Eugene D.
Fields, E. M.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 111. ...

The twisting effect at transonic speeds of spoiler ailerons on a 45©� sweptback, aspect-ratio-4, tapered wing /

Hammond, Alexander D.
Graven, Jean C., Jr.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a diamond-plan-form wing aspect ration 3.08 and a low, swept horizontal tail /

Kehlet, Alan B.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 129. ...

Some factors affecting the variation of pitching moment with sideslip of aircraft configurations /

Polhamus, Edward C.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 115. ...

Control hinge-movement and effectiveness characteristics of several interchangeable tip controls on a 60©� delta wing at Mach numbers of 1.41, 1.62, and 1.96 /

Morris, Odell A.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel /

Hasel, Lowell E.
Sinclair, Archibald R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

January 1950

"April 7, 1950; Declassified May 29, 1959."Includes bibliographical references (p. 14).Mode of acces...

Calculated effects of the lateral acceleration derivatives on the dynamic lateral stability of a delta-wing airplane /

Campbell, John P.
Woodling, Carroll H.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

"Classification changed to unclassified ..."--Stamped on cover."Confidential.""January 25, 1955."Cov...

An experimental and theoretical investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic characteristics in sideslip of an unswept, untapered tail assembly /

Wiley, Harleth G.
Riley, Donald R.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Wind-tunnel investigation at high subsonic speeds of the effect of spoiler profile on the lateral control characteristics of a wing-fuselage combination winter quarter-chord line swept back 32.6©� and NACA 65A006 airfoil section /

Johnson, Harold S.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Comparison of full-scale lift and drag characteristics of the x-15 airplane with wind-tunnel results and theory /

Hopkins, Edward J.
Saltzman, Edwin J.
Fetterman, David E.
Flight Research Center (U.S.)
Langley Research Center.
Ames Research Center.

January 1962

"Classification changed to unclassified by authority of NASA CCN number 14, dated April 21, 1965."Ma...

Wind-tunnel investigation at low speed of the effect of varying the ratio of body diameter to wing span from 0.1 to 0.8 on the aerodynamic characteristics in pitch of the 45©� sweptback-wing--body combination /

Johnson, Harold S.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Jet effects on longitudinal trim of an airplane configuration measured at Mach numbers between 1.2 and 1.8 /

Peck, Robert F.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 121. ...

Investigation at transonic speeds of the hinge-moment characteristics of a 1/8-scale model of the X-1E aileron /

Moseley, William C., Jr.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Effects of an inset tab on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60©� delta wing at Mach numbers from 0.75 to 1.96 /

Guy, Lawrence D. (Lawrence Duncan), 1921-
Brown, Hoyt V.
United States. National Advisory Committee for Aeronautics.

"Classification changed to unclassified, authority: NASA publication annoucement no. 3, effective da...

Aerodynamic load measurements and opening characteristics of automatic leading-edge slats on a 45©� sweptback wing at transonic speeds /

Arabian, Donald D.
Reid, Charles F., Jr.
Runckel, Jack F.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on a tapered sweptback wing at Mach numbers between 0.6 and 1.4 /

Schult, Eugene D.
Fields, E. M.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 111. ...

Hammond, Alexander D.
Graven, Jean C., Jr.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a diamond-plan-form wing aspect ration 3.08 and a low, swept horizontal tail /

Kehlet, Alan B.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 129. ...

Some factors affecting the variation of pitching moment with sideslip of aircraft configurations /

Polhamus, Edward C.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 115. ...

Control hinge-movement and effectiveness characteristics of several interchangeable tip controls on a 60©� delta wing at Mach numbers of 1.41, 1.62, and 1.96 /

Morris, Odell A.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

On front cover: "Classification Changed to Unclassified, Authority: NASA Technical Publications Anno...

A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel /

Hasel, Lowell E.
Sinclair, Archibald R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

January 1950

"April 7, 1950; Declassified May 29, 1959."Includes bibliographical references (p. 14).Mode of acces...

Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry /

Abstract

Extracted data

Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry /

Abstract

Extracted data

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