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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
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: February 1, 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
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 II : maximum thickness at midchord

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 II : maximum thickness at midchord

Date: December 3, 1948
Creator: Walker, Harold J & Berggren, Robert E
Description: The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit the irregular variations with Mach number at high subsonic and low supersonic Mach numbers that are characteristic of unswept wings. The lift-curve slope increased steadily with Mach number below unity and declined slowly beyond the Mach number of 1.13. A substantial rise in the minimum drag coefficient occurred between Mach numbers of 0.95 and 1.20 with an associated reduction in the maximum lift-drag ratio. The aerodynamic center shifted rearward toward the centroid of area of the wing with increasing Mach number below 0.975; whereas above 1.09 it coincided with the centroid.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Date: January 12, 1949
Creator: Lockwood, Vernard E; Vogler, Raymond D & Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 2.01 of nacelle shape and position on the aerodynamic characteristics in

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 2.01 of nacelle shape and position on the aerodynamic characteristics in

Date: July 25, 1952
Creator: Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Date: January 10, 1952
Creator: Driver, Cornelius & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the static lateral stability characteris

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the static lateral stability characteris

Date: August 1, 1952
Creator: Hamilton, Clyde V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail

Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail

Date: March 29, 1954
Creator: Kehlet, Alan B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance : transonic-bump method

Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance : transonic-bump method

Date: September 16, 1952
Creator: Wiley, Harleth G & Zontek, Leon
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance : transonic-bump method

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance : transonic-bump method

Date: February 6, 1951
Creator: Wiley, Harleth G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Date: April 5, 1954
Creator: Runckel, Jack F & Schmeer, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a full-span flap type of control with overhang balance : transonic-bump method

Aerodynamic characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a full-span flap type of control with overhang balance : transonic-bump method

Date: January 25, 1952
Creator: Lockwood, Vernard E & Hagerman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Date: January 15, 1952
Creator: Morrison, William D , Jr & Fournier, Paul G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degree sweptback, aspect-ratio-4 tail deflected about a skewed hinge axis and equipped with an inset unbalancing tab

The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degree sweptback, aspect-ratio-4 tail deflected about a skewed hinge axis and equipped with an inset unbalancing tab

Date: September 29, 1953
Creator: Watson, James M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degrees sweptback, aspect-ratio-4 tail surface deflected about a skewed hinge axis

The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degrees sweptback, aspect-ratio-4 tail surface deflected about a skewed hinge axis

Date: July 3, 1952
Creator: Hammond, Alexander D & Watson, James M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Date: November 18, 1952
Creator: Wiley, Harleth G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Date: January 1, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Description: An investigation has been made at high subsonic speeds of the aerodynamic'characteristics in pitch and sideslip of a l/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for small sideslip angles at Mach numbers above 0.8; however, the instability was eliminated by several different modifications.
Contributing Partner: UNT Libraries Government Documents Department
The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

Date: May 23, 1956
Creator: Driver, Cornelius
Description: Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined. The results indicate that for a horizontal-tail incidence of -10 deg the trim lift coefficient varied from 0.29 at a Mach number of 1.61 to 0.23 at a Mach number of 2.01 with a corresponding decrease in lift-drag trim from 3.72 to 3.15. Stick-position instability was indicated in the low-supersonic-speed range. A photographic-type nose modification resulted in slightly higher values of minimum drag coefficient but did not significantly affect the static stability or lift-curve slope. The minimum drag coefficient for the complete model with the production nose remained essentially constant at 0.047 throughout the Mach number range investigated.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Date: October 30, 1953
Creator: Spearman, M Leroy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Date: March 18, 1954
Creator: Osborne, Robert S & Wornom, Dewey E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Date: February 6, 1951
Creator: Sutton, Fred B & Martin, Andrew
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including scale effect of several wings and bodies alone and in combination at a Mach number of 1.53

Aerodynamic characteristics including scale effect of several wings and bodies alone and in combination at a Mach number of 1.53

Date: December 20, 1946
Creator: Van Dyke, Milton D
Description: None
Contributing Partner: UNT Libraries Government Documents Department