NACA Research Memorandums

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1960

"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...

Investigation of spoiler ailerons for use as speed brakes or glide-path controls on two NACA 65-series wings equipped with full-span slotted flaps /

Fischel, Jack.
Watson, James M.
United States. National Advisory Committee for Aeronautics.

January 1949

Analysis indicates that this use of spoiler ailerons is feasible and desirable for normal emergency ...

Experimental pressure distributions over wing tips at Mach number 1.9.

Mirels, Harold.
Jagger, James M., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...

NACA Research Memorandums

Hill, W. A., Jr.
Kaattari, G. E.

July 1956

Force and pressure distribution studies to high angles of attack on all-movable triangular and recta...

PRESSURE DISTRIBUTIONS AND AERODYNAMIC CHARACTERISTICS OF SEVERAL SPOILER-TYPE CONTROLS ON A TRAPEZOIDAL WING AT MACH NUMBERS OF 1.61 AND 2.01

Lord, D. R.
Czarnecki, K. R.

July 1956

Pressure distributions and aerodynamic characteristics of spoiler-type controls on trapezoidal wing ...

NACA Technical Memorandums

Ernst, G.
Kramer, M.

March 1949

The present report deals with the aerodynamic, constructive, and instrumental development of a spoil...

Aerodynamic characteristics of a spoiler-slot-deflector control on a 45©� sweptback wing at Mach numbers of 1.61 and 2.01 /

Lord, Douglas R.
Moring, Robert.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach number...

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1960

"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...

Investigation of spoiler ailerons for use as speed brakes or glide-path controls on two NACA 65-series wings equipped with full-span slotted flaps /

Fischel, Jack.
Watson, James M.
United States. National Advisory Committee for Aeronautics.

January 1949

Analysis indicates that this use of spoiler ailerons is feasible and desirable for normal emergency ...

Experimental pressure distributions over wing tips at Mach number 1.9.

Mirels, Harold.
Jagger, James M., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...

NACA Research Memorandums

Hill, W. A., Jr.
Kaattari, G. E.

July 1956

Force and pressure distribution studies to high angles of attack on all-movable triangular and recta...

PRESSURE DISTRIBUTIONS AND AERODYNAMIC CHARACTERISTICS OF SEVERAL SPOILER-TYPE CONTROLS ON A TRAPEZOIDAL WING AT MACH NUMBERS OF 1.61 AND 2.01

Lord, D. R.
Czarnecki, K. R.

July 1956

Pressure distributions and aerodynamic characteristics of spoiler-type controls on trapezoidal wing ...

NACA Technical Memorandums

Ernst, G.
Kramer, M.

March 1949

The present report deals with the aerodynamic, constructive, and instrumental development of a spoil...

Aerodynamic characteristics of a spoiler-slot-deflector control on a 45©� sweptback wing at Mach numbers of 1.61 and 2.01 /

Lord, Douglas R.
Moring, Robert.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach number...

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1960

"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...

Investigation of spoiler ailerons for use as speed brakes or glide-path controls on two NACA 65-series wings equipped with full-span slotted flaps /

Fischel, Jack.
Watson, James M.
United States. National Advisory Committee for Aeronautics.

January 1949

Analysis indicates that this use of spoiler ailerons is feasible and desirable for normal emergency ...

Experimental pressure distributions over wing tips at Mach number 1.9.

Mirels, Harold.
Jagger, James M., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...

NACA Research Memorandums

Abstract

Extracted data

NACA Research Memorandums

Abstract

Extracted data

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