The effects of fuselage size on the low-speed longitudinal aerodynamic characteristics of a thin 60©� delta wing with and without a double slotted flap /

Transonic flight tests to determine the effect of thickness ratio and plan-form modification on the zero-lift drag of a 45©� sweptback wing /

Pepper, William B.
Hoffman, Sherwood.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"August 12, 1952."Includes bibliographical references (p. 9).Mode of access: Internet

Large-scale low-speed wind-tunnel tests of a delta winged supersonic transport model to determine aerodynamic effects of forward or reverse thrust /

Tolhurst, William H.
Aoyagi, Kiyoshi.
Ames Research Center.

January 1964

"November 1964."Includes bibliographical references (p. 9).Mode of access: Internet

Effect of wing-mounted external stores on the lift and drag of the Douglas D-558-II research airplane at transonic speeds /

Nugent, Jack.
Flight Research Center (U.S.)
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"July 17, 1957."Includes bibliographical references (p. 10).Mode of access: Internet

Effects of size of external stores on the aerodynamic characteristics of an unswept and a 45©� sweptback wing of aspect ratio 4 and a 60©� delta wing at Mach numbers of 1.41, 1.62, and 1.96 /

Jacobsen, Carl R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"January 21, 1953."Includes bibliographical references (p. 8-9).Mode of access: Internet

Effect of some section modifications and protuberances on the zero-lift drag of delta wings at transonic and supersonic speeds /

Sandahl, Carl A.
Stoney, William E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"February 18, 1954."Includes bibliographical references (p. 11).Mode of access: Internet

Effects of wing incidence on the longitudinal trim characteristics of a cambered 70° delta-wing configuration at mach numbers 3.0 to 5.0 /

Ahtye, Warren F.
Ames Research Center.

January 1960

"September 1960."Cover title.Includes bibliographical references (p. 23).Mode of access: Internet

Aerodynamic characteristics of two delta wings and two trapezoidal wings at Mach number of 4.04 /

Dunning, Robert W.
Smith, Fred M.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1959

"June 11, 1953; Declassified August 26, 1959."Includes bibliographical references (p. 6).Mode of acc...

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

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

Osborne, Robert S.
Kelly, Thomas C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"April 9, 1953."Includes bibliographical references (p. 7-9).Mode of access: Internet

Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing /

Parks, James H.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"April 11, 1952."Includes bibliographical references (p. 15-16).Mode of access: Internet

Aerodynamic characteristics over a Mach number range of 1.40 to 2.78 of a rocket-propelled airplane configuration having a low 52.2©� delta wing and an unswept horizontal tail. /

Kehlet, Alan B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"March 6, 1958."Includes bibliographical references (p. 13).Mode of access: Internet

The effect of nose radius and shape of the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack /

Gapcynski, John P.
Robins, A. Warner.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"October 22, 1953."Includes bibliographical references (p. 10-11).Mode of access: Internet

Low-speed investigation of effects of vertical tails on the static stability characteristics of a canard-bomber configuration having a very thin wing and a slender elliptical fuselage /

Gainer, Thomas G.
Langley Research Center.

January 1961

"January 1961."Caption title.Includes bibliographical references (p. 8).Mode of access: Internet

Effect of longitudinal wings position on the pressure characteristics at transonic speeds of a 45©� sweptback wing-fuselage model /

Solomon, William.
Schmeer, James W.
United States. National Advisory Committee for Aeronautics.

"March 4, 1953."Cover title.Includes bibliographical references (p. 12).Mode of access: Internet

Longitudinal aerodynamic characteristics at transonic speeds of a V/STOL airplane configuration with a fixed delta wing having auxiliary variable-sweep outboard panels /

Luoma, Arvo A.
Langley Research Center.

January 1961

"December 1961."Cover title.Includes bibliographical references (p. 11).Mode of access: Internet

Transonic flight tests to determine the effect of thickness ratio and plan-form modification on the zero-lift drag of a 45©� sweptback wing /

Pepper, William B.
Hoffman, Sherwood.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"August 12, 1952."Includes bibliographical references (p. 9).Mode of access: Internet

Large-scale low-speed wind-tunnel tests of a delta winged supersonic transport model to determine aerodynamic effects of forward or reverse thrust /

Tolhurst, William H.
Aoyagi, Kiyoshi.
Ames Research Center.

January 1964

"November 1964."Includes bibliographical references (p. 9).Mode of access: Internet

Effect of wing-mounted external stores on the lift and drag of the Douglas D-558-II research airplane at transonic speeds /

Nugent, Jack.
Flight Research Center (U.S.)
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"July 17, 1957."Includes bibliographical references (p. 10).Mode of access: Internet

Effects of size of external stores on the aerodynamic characteristics of an unswept and a 45©� sweptback wing of aspect ratio 4 and a 60©� delta wing at Mach numbers of 1.41, 1.62, and 1.96 /

Jacobsen, Carl R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"January 21, 1953."Includes bibliographical references (p. 8-9).Mode of access: Internet

Effect of some section modifications and protuberances on the zero-lift drag of delta wings at transonic and supersonic speeds /

Sandahl, Carl A.
Stoney, William E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"February 18, 1954."Includes bibliographical references (p. 11).Mode of access: Internet

Effects of wing incidence on the longitudinal trim characteristics of a cambered 70° delta-wing configuration at mach numbers 3.0 to 5.0 /

Ahtye, Warren F.
Ames Research Center.

January 1960

"September 1960."Cover title.Includes bibliographical references (p. 23).Mode of access: Internet

Aerodynamic characteristics of two delta wings and two trapezoidal wings at Mach number of 4.04 /

Dunning, Robert W.
Smith, Fred M.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1959

"June 11, 1953; Declassified August 26, 1959."Includes bibliographical references (p. 6).Mode of acc...

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

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

Osborne, Robert S.
Kelly, Thomas C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"April 9, 1953."Includes bibliographical references (p. 7-9).Mode of access: Internet

Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing /

Parks, James H.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"April 11, 1952."Includes bibliographical references (p. 15-16).Mode of access: Internet

Aerodynamic characteristics over a Mach number range of 1.40 to 2.78 of a rocket-propelled airplane configuration having a low 52.2©� delta wing and an unswept horizontal tail. /

Kehlet, Alan B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"March 6, 1958."Includes bibliographical references (p. 13).Mode of access: Internet

The effect of nose radius and shape of the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack /

Gapcynski, John P.
Robins, A. Warner.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"October 22, 1953."Includes bibliographical references (p. 10-11).Mode of access: Internet

Low-speed investigation of effects of vertical tails on the static stability characteristics of a canard-bomber configuration having a very thin wing and a slender elliptical fuselage /

Gainer, Thomas G.
Langley Research Center.

January 1961

"January 1961."Caption title.Includes bibliographical references (p. 8).Mode of access: Internet

Effect of longitudinal wings position on the pressure characteristics at transonic speeds of a 45©� sweptback wing-fuselage model /

Solomon, William.
Schmeer, James W.
United States. National Advisory Committee for Aeronautics.

"March 4, 1953."Cover title.Includes bibliographical references (p. 12).Mode of access: Internet

Longitudinal aerodynamic characteristics at transonic speeds of a V/STOL airplane configuration with a fixed delta wing having auxiliary variable-sweep outboard panels /

Luoma, Arvo A.
Langley Research Center.

January 1961

"December 1961."Cover title.Includes bibliographical references (p. 11).Mode of access: Internet

Transonic flight tests to determine the effect of thickness ratio and plan-form modification on the zero-lift drag of a 45©� sweptback wing /

Pepper, William B.
Hoffman, Sherwood.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"August 12, 1952."Includes bibliographical references (p. 9).Mode of access: Internet

Large-scale low-speed wind-tunnel tests of a delta winged supersonic transport model to determine aerodynamic effects of forward or reverse thrust /

Tolhurst, William H.
Aoyagi, Kiyoshi.
Ames Research Center.

January 1964

"November 1964."Includes bibliographical references (p. 9).Mode of access: Internet

Effect of wing-mounted external stores on the lift and drag of the Douglas D-558-II research airplane at transonic speeds /

Nugent, Jack.
Flight Research Center (U.S.)
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"July 17, 1957."Includes bibliographical references (p. 10).Mode of access: Internet

The effects of fuselage size on the low-speed longitudinal aerodynamic characteristics of a thin 60©� delta wing with and without a double slotted flap /

Abstract

Extracted data

The effects of fuselage size on the low-speed longitudinal aerodynamic characteristics of a thin 60©� delta wing with and without a double slotted flap /

Abstract

Extracted data

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