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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body -- NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body -- NACA model 84 series

Date: January 1, 1943
Creator: Parkinson, John B; Olson, Roland E; Draley, Eugene C & Luoma, Arvo A
Description: A series of related forms of flying-boat hulls representing various degrees of compromise between aerodynamic and hydrodynamic requirements was tested in Langley Tank No. 1 and in the Langley 8-foot high-speed tunnel. The purpose of the investigation was to provide information regarding the penalties in water performance resulting from further aerodynamic refinement and, as a corollary, to provide information regarding the penalties in range or payload resulting from the retention of certain desirable hydrodynamic characteristics. The information should form a basis for over-all improvements in hull form.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil

Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil

Date: January 1, 1943
Creator: Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Date: October 1, 1942
Creator: Liddell, Robert B
Description: None
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 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 for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane

Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane

Date: October 1, 1942
Creator: Underwood, William J
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 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Date: October 1, 1949
Creator: Loftin, Laurence K , Jr & Smith, Hamilton A
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 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Date: October 12, 1945
Creator: Schnurbusch, Alfred W.
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 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 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 number of modified NACA four-digit-series airfoil sections

Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections

Date: June 1, 1948
Creator: Loftin, Laurence K , Jr & Cohen, Kenneth S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Date: November 14, 1947
Creator: Loftin, Laurence K., Jr. & Cohen, Kenneth G.
Description: Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Description: A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in various conditions of surface deformation are presented in this report.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Date: April 1, 1941
Creator: Rogallo, F M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller

Date: September 2, 1948
Creator: Evans, Albert J & Salters, Leland B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department