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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
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
Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Description: An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale moue1 of the Fairchild Lark missile, The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses. The wind-tunnel-test data indicate that rolling the missile 22.5 deg. had no serious effect on the static longitudinal stability. The desired maneuvering acceleration could not be attained with any of the horizontal wings tested, even with the horizontal wing flaps deflected 50 deg. The flaps on the 64A-209 wing (with small trailing-edge angles and flat sides) were effective at all flap deflections, while the flaps on the 16-series wings (with large trailing-edge angles) lost effectiveness at small flap deflections. The data showed that rolling moment existed when the vertical wing flaps were deflected with the model at other than zero angle of attack. A similar rolling moment probably would be found . with the horizontal wing flaps deflected and the model yawed.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102A airplane at Mach numbers of 1.41, 1.61, and 2.01

Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102A airplane at Mach numbers of 1.41, 1.61, and 2.01

Date: September 30, 1955
Creator: Spearman, M. Leroy & 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 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated. In addition, the effects of a revised vertical tail and two different ventral fins were determined. The results indicated that the use of cambered wings resulted in lower drag in the lift-coefficient range above 0.2. This range, however, is above that which would generally be required for level flight; hence, the usefulness of camber might be confined to increased maneuverability at the higher lifts while its use may be detrimental to the high-speed (low-lift) capabilities.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Date: March 28, 1955
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
Description: Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 . In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution. Fuselage modifications employed on the F-102A were responsible for a 25.percent reduction in the minimum drag-coefficient rise between the Mach numbers of 0.85 and 1.075 when compared with that for the earlier versions of the F-102. Although the wing modifications increased the F-102A subsonic minimum drag-coefficient level approximately 0.0020, they produced large decreases in drag at lifting conditions over that for the original (plane-wing) F-102. The F-102A had 15 to 25 percent higher maximum lift-drag ratios than did the original F-102. The F-102A had about 15 percent lower maximum lift-drag ratios at Mach numbers below 0.95 and slightly higher maximum lift-drag ratios at supersonic speeds when compared with those ratios for sn earlier modified-wing version ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102B airplane at Mach numbers of 1.41, 1.61, and 2.01 : COORD No. AF-231

Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102B airplane at Mach numbers of 1.41, 1.61, and 2.01 : COORD No. AF-231

Date: February 27, 1956
Creator: Driver, Cornelius & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Date: January 1, 1957
Creator: Osborne, Robert S.
Description: The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested. An increase in lift-curve slope from 0.045 to 0.059 and an 11-percent rearward shift in aerodynamic-center location occurred with increases in Mach number from 0.60 to approximately 1.05. The zero-lift drag coefficient for the TF-102A airplane increased 145 percent between the Mach numbers of 0.85 and 1.075; the maximum lift-drag ratio decreased from 9.5 at a Mach number of 0.60 to 5.0 at Mach numbers above 1.025. There was little difference in the lift and pitching-moment characteristics and drag due to life between the TF-102A and F-102A configurations. However, as compared with the F-102A airplane, the zero-lift drag-rise Mach number for the TF-102A was reduced by at least 0.06, the zero-lift peak wave drag was increased 50 percent, and the maximum lift-drag ratio was ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 1/4-scale model of the duct system for the General Electric P-1 nuclear powerplant for aircraft

Aerodynamic characteristics of a 1/4-scale model of the duct system for the General Electric P-1 nuclear powerplant for aircraft

Date: July 29, 1955
Creator: Wood, Charles C. & Henry, John R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 6-percent-thick symmetrical circular-arc airfoil having a 30-percent-chord trailing-edge flap at a Mach number of 6.9

Aerodynamic characteristics of a 6-percent-thick symmetrical circular-arc airfoil having a 30-percent-chord trailing-edge flap at a Mach number of 6.9

Date: May 5, 1956
Creator: Ridyard, Herbert W & Fetterman, David E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Date: March 4, 1949
Creator: Lina, Lindsay J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Date: May 23, 1947
Creator: Neely, Robert H & Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 45 deg swept wing fighter airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Aerodynamic characteristics of a 45 deg swept wing fighter airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Date: June 24, 1958
Creator: Oehman, W. I. & Turner, K. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Date: August 4, 1947
Creator: Proterra, Anthony J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Date: June 24, 1958
Creator: Oehman, Waldo I & Turner, Kenneth L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Date: April 25, 1955
Creator: Ulmann, Edward F & Smith, Fred M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range

Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range

Date: November 2, 1953
Creator: Hatch, John E , Jr & Gallagher, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01

The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01

Date: July 2, 1957
Creator: Gapcynski, John P & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Date: March 24, 1958
Creator: Spearman, M Leroy & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a circular cylinder at Mach number of  6.86 and angles of attack up to 90 degrees

Aerodynamic Characteristics of a circular cylinder at Mach number of 6.86 and angles of attack up to 90 degrees

Date: March 11, 1954
Creator: Penland, Jim A
Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristics but that the modified Newtonian theory gives a more accurate prediction of the pressure distribution. The calculated crossflow drag coefficients plotted as a function of crossflow Mach number were found to be in reasonable agreement with similar results obtained from other investigations at lower supersonic Mach numbers. Comparison of the results of this investigation with data obtained at a lower Mach number indicates that the drag coefficient of a cylinder normal to the flow is relatively constant for Mach numbers above about 4.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Date: April 12, 1954
Creator: Spearman, M Leroy & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Date: February 11, 1949
Creator: Macleod, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206

Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206

Date: January 23, 1951
Creator: Riebe, John M. & Naeseth, Rodger L.
Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam ratios indicated a reduction in minimum drag coefficients of 0.0006 (10 peroent)with fixed transition when the length-beam ratio was extended from 12 to 15. As with the hulls of lower length-beam ratio, the drag reduction with a length-beam ratio of 15 occurred throughout the range of angle of attack tested and the angle of attack for minimum drag was in the range from 2deg to 3deg. Increasing the length-beam ratio from 12 to 15 reduced the hull longitudinal instability by an mount corresponding to an aerodynamic-center shift of about 1/2 percent of the mean aerodynamic chord of the hypothetical flying boat. At an angle of attack of 2deg, the value of the variation of yawing-moment coefficient with angle of yaw for ...
Contributing Partner: UNT Libraries Government Documents Department