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Force tests of three thin wings of moderately low aspect ratio at high subsonic Mach numbers

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of leading-edge shape and section profile on the aerodynamic characteristics of two thin wings of aspect ratio 4. Lift, drag, and pitching-moment data are presented for a range of angles of attack and Mach numbers. Information about a third wing with an aspect ratio of 3, a taper ratio of 0.4, and a 4.5-percent-thick modified-hexagonal section are also provided.
Date: October 17, 1952
Creator: Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Flight-determined pressure distributions over the wing of the Bell X-1 research airplane (10-percent-thick wing) at subsonic and transonic speeds

Description: Report presenting measurements of chordwise pressure distributions at four spanwise stations over a 10-percent-thick wing of the Bell X-1 airplane. Results regarding pressure distributions at the various stations and section aerodynamic characteristics are presented. The data was obtained for a range of Mach numbers from 0.30 to 11.9 and altitudes from 17,000 to 47,000 with several different types of maneuvers.
Date: June 29, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds

Description: Report presenting measurements of wing loads made on the left wing of the Bell X-1 research airplane. Data are presented within a wing-panel normal-force coefficient and Mach number range. Results regarding span load distributions, wing-panel aerodynamic characteristics, and wing-to-fuselage carry over are provided.
Date: November 4, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

The effect of a simulated propeller slipstream on the aerodynamic characteristics of an unswept wing panel with and without nacelles at Mach numbers from 0.30 to 0.86

Description: Report presenting force testing in the high-speed tunnel to determine the effect of a simulated propeller slipstream on the aerodynamic characteristics of an unswept wing panel with and without nacelles. Lift, drag, and pitching moment were measured for a range of angles of attack and Mach numbers.
Date: September 1952
Creator: Jordan, Gareth H. & Cole, Richard I.
Partner: UNT Libraries Government Documents Department

Wing pressure distributions over the lift range of the Convair XF-92A delta-wing airplane at subsonic and transonic speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
Date: November 30, 1955
Creator: Keener, Earl R. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Flight-determined pressure distributions over a section of the 35 degree swept wing of the Douglas D-558-II research airplane at Mach numbers up to 2.0

Description: From Summary: "Measurements of pressure distributions have been made over a wing midsemispan station on the 35 degree sweptback wing of the Douglas D-558-II research airplane at Mach numbers from 1.17 to 2.0. The results of the investigation indicate that, as the angle of attack increased at the higher Mach numbers, the pressure coefficient for a vacuum limited the extent to which the upper-surface pressures could expand. Consequently most of the increase in section normal-force coefficient at high angles of attack can be attributed to the increase in pressure over the lower surface."
Date: March 25, 1955
Creator: Jordan, Gareth H. & Keener, Earl R.
Partner: UNT Libraries Government Documents Department

Wing loads and load distributions throughout the lift range of the Douglas X-3 research airplane at transonic speeds

Description: Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the left wing of the Douglas X-3 to determine the effects of angle of attack and Mach number on the wing characteristics at transonic Mach numbers. The wing had an aspect ratio of 3.09 and a modified 4.5-percent-thick hexagonal section. Data covered a range of lift values and Mach numbers.
Date: November 9, 1956
Creator: Keener, Earl R. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Fuselage pressures measured on the Bell X-1 research airplane in transonic flight

Description: Report presenting pressure-distribution measurements on the fuselage of the Bell X-1 research airplane. A variety of angles of attack and Mach numbers were tested. Results regarding pressure distribution and normal load are provided.
Date: November 6, 1953
Creator: Knapp, Ronald J.; Jordan, Gareth H. & Johnson, Wallace E.
Partner: UNT Libraries Government Documents Department

Preliminary flight survey of fuselage and boundary-layer sound-pressure levels

Description: Report presenting preliminary flight surveys of noise inside fuselages and in the fuselage boundary layer, which were obtained in order to determine the magnitude of the noise and relative importance of engine noise and noise due to the boundary layer. Results indicated that the sound-pressure level continued to increase with airspeed to the highest airspeed obtained, although the rate of increase at supersonic speeds was less than at subsonic speeds. Testing occurred on the B-47A and D-558-II airplanes.
Date: May 13, 1958
Creator: McLeod, Norman J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Wing pressure distributions over the lift range of the Convair XF-92A delta-wing airplane at subsonic and transonic speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distributions, and elevon-section loads are provided.
Date: November 30, 1955
Creator: Keeener, Earl R. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Preliminary flight-determined pressure distributions over the wing of the Douglas X-3 research airplane at subsonic and transonic Mach numbers

Description: Report presenting preliminary flight-measured chordwise pressure distributions, which have been obtained at a wing midsemispan station of the Douglas X-3 research airplane through a range of angles of attack and Mach numbers. An exploration of the section aerodynamic characteristics is also provided.
Date: April 7, 1955
Creator: Jordan, Gareth H. & Hutchins, Kenneth, Jr.
Partner: UNT Libraries Government Documents Department