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 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Date: December 5, 1956
Creator: Bielat, Ralph P; Coffee, Claude W , Jr & Petynia, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Date: October 23, 1957
Creator: Petynia, William W; Hasson, Dennis F & Spooner, Stanley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Date: December 1, 1955
Creator: Shanks, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Date: March 18, 1958
Creator: Dryer, Murray & Luidens, Roger W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method

Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method

Date: May 5, 1950
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Date: September 20, 1955
Creator: Whittle, Edward F , Jr & Mclemore, H Clyde
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at a Mach number of 1.25 of a 6-percent-thick triangular wing and 6- and 9-percent-thick triangular wings in combination with a fuselage : wing aspect ratio 2.31, biconvex airfoil sections

Aerodynamic characteristics at a Mach number of 1.25 of a 6-percent-thick triangular wing and 6- and 9-percent-thick triangular wings in combination with a fuselage : wing aspect ratio 2.31, biconvex airfoil sections

Date: May 5, 1950
Creator: Hall, Albert W & Morris, Garland J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at a Mach number of 1.38 of four wings of aspect ratio 4 having quarter-chord sweep angles of 0 degrees, 35 degrees, 45 degrees, and 60 degrees

Aerodynamic characteristics at a Mach number of 1.38 of four wings of aspect ratio 4 having quarter-chord sweep angles of 0 degrees, 35 degrees, 45 degrees, and 60 degrees

Date: October 10, 1950
Creator: Kemp, William B , Jr; Goodson, Kenneth W & Booth, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

Date: August 4, 1958
Creator: Bernot, P. T. & Robinson, R. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at a Mach number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls

Aerodynamic characteristics at a Mach number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls

Date: August 4, 1958
Creator: Robinson, Ross B & Bernot, Peter T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Date: June 5, 1953
Creator: Wilson, Homer B , Jr & Horton, Elmer A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Date: 1954?
Creator: Critzos, Chris C.
Description: An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as variations of lift, drag, and quarter-chord pitching-moment coefficients with Mach number.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: October 1, 1948
Creator: Solomon, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Date: October 26, 1948
Creator: Johnson, Peter J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics at High Speeds of Full-Scale Propellers having Different Shank Designs

Aerodynamic Characteristics at High Speeds of Full-Scale Propellers having Different Shank Designs

Date: February 13, 1947
Creator: Maynard, Julian D.
Description: Tests of two 10-foot-diameter two-blade propellers which differed only in shank design have been made in the Langley 16-foot high-speed tunnel. The propellers are designated by their blade design numbers, NACA 10-(5)(08)-03, which had aerodynamically efficient airfoil shank sections, and NACA l0-(5)(08)-03R which had thick cylindrical shank sections typical of conventiona1 blades, The propellers mere tested on a 2000-horsepower dynamometer through a range of blade-angles from 20deg to 55deg at various rotational speeds and at airspeeds up to 496 miles per hour. The resultant tip speeds obtained simulate actual flight conditions, and the variation of air-stream Mach number with advance ratio is within the range of full-scale constant-speed propeller operation. Both propellers were very efficient, the maximum envelope efficiency being approximately 0,95 for the NACA 10-(5)(08)-03 propeller and about 5 percent less for the NACA 10-(5)(08)-03R propeller. Based on constant power and rotational speed, the efficiency of the NACA 10-(05)(08)-03 propeller was from 2.8 to 12 percent higher than that of the NACA 10-(5)(08)-03R propeller over a range of airspeeds from 225 to 450 miles per hour. The loss in maximum efficiency at the design blade angle for the NACA 10-(5)(08)-03 and 10-(5)(08)-03R propellers vas about 22 and 25 percent, ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap

Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap

Date: May 29, 1953
Creator: Dunning, Robert W & Ulmann, Edward F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Date: August 30, 1954
Creator: Spearman, M Leroy & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Date: December 3, 1957
Creator: Dunning, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge

Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge

Date: August 4, 1958
Creator: Hallissy, Joseph M , Jr & Hasson, Dennis F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Date: September 2, 1955
Creator: Chapman, Rowe, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Date: September 10, 1958
Creator: Carmel, Melvin R; Kelly, Thomas C & Gregory, Donald T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers of 1.61 and 2.01 of various tip controls on the wing panel of a 0.05-scale model of a Martin XASM-N-7 (Bullpup) missile : TED No. NACA AD 3106

Aerodynamic characteristics at Mach numbers of 1.61 and 2.01 of various tip controls on the wing panel of a 0.05-scale model of a Martin XASM-N-7 (Bullpup) missile : TED No. NACA AD 3106

Date: 1956~
Creator: Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Date: November 6, 1947
Creator: Eggers, A J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord

Date: November 19, 1948
Creator: Berggren, Robert E & Summers, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department