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Preliminary Free-Flight Investigation of the Effect of Airfoil Section on Aileron Rolling Effectiveness at Transonic and Supersonic Speeds
"Results have been obtained by means of a free-flight technique utilizing rocket propulsion which indicate that aileron-rolling-effectiveness characteristics are affected adversely by variations in airfoil section which procedure large increases in the trailing-edge angle" (p. 1).
Date:
June 25, 1948
Creator:
Sandahl, Carl A.
System:
The UNT Digital Library
Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a 42.7 Degree Sweptback Wing Having Partial-Span Ailerons
An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.
Date:
October 25, 1948
Creator:
Sandahl, Carl A.
System:
The UNT Digital Library
NACA Transonic Wing-Tunnel Test Sections
Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date:
October 25, 1948
Creator:
Wright, Ray H. & Ward, Vernon G.
System:
The UNT Digital Library
Preliminary Investigation at a Mach Number of 1.9 and a Reynolds Number of 2,200,000 of Three Ailerons Applicable to the Bell XS-2 Airplane Design
Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.
Date:
May 25, 1948
Creator:
Sivells, James C. & Conner, D. William
System:
The UNT Digital Library
Performance of J33-A-23 Turbojet-Engine Compressor, II, Over-All Performance Characteristics of Compressor with 34-Blade Impeller at Equivalent Impeller Speeds from 6000 to 11,750 RPM
"The J33-A-23 compressor with a 34-blade impeller was operated at ambient inlet temperature and an inlet pressure of 14 inches mercury absolute over a range of equivalent impeller speeds from 6000 to 11,750 rpm. Additional runs at equivalent speeds of 7,000, 10,000, and 11,750 rpm and ambient inlet temperature were made at inlet pressures of 5 and 10 inches mercury absolute. The results of this investigation are compared with those of the J33-A-23 compressor with a 17-blade impeller" (p. 1).
Date:
August 25, 1948
Creator:
Beede, William L. & Kovach, Karl
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Low-Speed Stability and Control Characteristics of a Model With a Sweptback Vee Tail and a Sweptback Wing
Report presenting testing in the 300 mph tunnel of a model with a sweptback vee tail and a sweptback wing to determine its low-speed stability and control characteristics. The results are compared to testing with the same tail panel with zero dihedral on the same wing-fuselage combination. The longitudinal stability characteristics, downwash at the tail, longitudinal control characteristics, lateral stability characteristics, and rudder control characteristics are provided.
Date:
May 25, 1948
Creator:
Polhamus, Edward C.
System:
The UNT Digital Library