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in creator/contributor: "Crabill, Norman L"  
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Summary of the Lift, Drag, and Stability of 1/10-Scale Rocket-Boosted Models of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.6 to 1.4 as Affected by the Operation of Extensible Rocket Racks

Description: Report discussing an investigation of the McDonnell XF3H-1 with models to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Information about the flutter, static longitudinal stability, dynamic longitudinal stability, static directional stability, trim, drag, and effect of rocket racks on aerodynamic characteristics of the model is provided.
Date: January 26, 1954
Creator: Crabill, Norman L. & McFall, John C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Some Transonic Aerodynamic Characteristics of a Model Similar to the McDonnell F3H-2N Airplane

Description: Report discussing testing of a model of the McDonnell F3H-2N to determine its pitch-up and buffet boundaries and its longitudinal stability and control data obtainable with the pulse-tail technique. Stability was found to be less at low trim angles of attack than at high trim angles of attack up to a point. The buffet boundary was not obtainable through this testing.
Date: May 15, 1956
Creator: Crabill, Norman L. & Jackson, Bruce G.
Partner: UNT Libraries Government Documents Department
open access

The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10 Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34

Description: Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.
Date: June 16, 1953
Creator: Crabill, Norman L.
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Drag and Longitudinal Stability and Control Characteristics of a Rocket-Powered Model of a 60 Degrees Delta-Wing Airplane From Mach Numbers 0.75 to 1.70

Description: Report discussing an investigation to determine the aerodynamic characteristics of a model of a tailless delta-wing airplane configuration with a leading edge swept back 60 degrees at a range of Mach numbers. Information about lift-curve slope, buffeting, drag rise, hinge-moment coefficients, transonic trim, and stability is provided.
Date: November 29, 1951
Creator: Mitcham, Grady L.; Crabill, Norman L. & Stevens, Joseph E.
Partner: UNT Libraries Government Documents Department
open access

Summary of the lift, drag, and stability of 1/10-scale rocket-boosted models of the McDonnell XF3H-1 airplane for a Mach number range of 0.6 to 1.4 as affected by the operation of extensible rocket racks : TED No. NACA DE 351

Description: Report presenting a flight investigation using two rocket-boosted scale models of the McDonnell XF3H-1 airplane to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Operation of the racks generally had only a small effect on the aerodynamic characteristics with the exception of drag.
Date: January 26, 1954
Creator: Crabill, Norman L. & McFall, John C., Jr.
Partner: UNT Libraries Government Documents Department
open access

The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10-Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34 : TED No. NACA DE 31

Description: Memorandum presenting the results of a test on the transonic longitudinal characteristics of a scale rocket model of the McDonnell XF3H-1 airplane. The model, flown with a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane, was equipped with extensible rocket racks. Results regarding the Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional … more
Date: June 16, 1953
Creator: Crabill, Norman L.
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation of jet effects at low supersonic Mach numbers on a fighter-type configuration employing a tail-boom assembly: longitudinal stability and trim

Description: Report presenting flight tests over a range of Mach numbers to study the effects of a simulated afterburning turbojet engine on the gross longitudinal flight characteristics of two geometrically identical models of a swept-wing fighter-type configuration. Results regarding the trim characteristics, lift, pitching moment, dynamic stability, and drag are provided.
Date: August 30, 1957
Creator: Jackson, Bruce G. & Crabill, Norman L.
Partner: UNT Libraries Government Documents Department
open access

Lift, Drag, Static Stability, and Buffet Boundaries of a Model of the McDonnell F3H-1N Airplane at Mach Numbers from 0.40 to 1.27, TED No. NACA DE 351

Description: "The National Advisory Committee for Aeronautics has conducted a flight test of a model approximating the McDonnell F3H-1N airplane configuration to determine its pitch-up and buffet boundaries, as well as the usual longitudinal stability derivatives obtainable from the pulsed- tail technique. The test was conducted by the freely flying rocket-boosted model technique developed at the Langley Laboratory; results were obtained at Mach numbers from 0.40 to 1.27 at corresponding Reynolds numbers of… more
Date: January 31, 1956
Creator: Crabill, Norman L.
Partner: UNT Libraries Government Documents Department
open access

Low-Lift Drag and Duct Pressure Recovery of a 1/8.25-Scale Model of the Consolidated Vultee XF-92 Airplane at Mach Numbers from 0.7 to 1.4

Description: "A flight investigation has been made to determine the external drag and pressure recovery of a 1/8.25 - scale flight model of the Consolidated Vultee XF-92 from Mach numbers 0.7 to 1.4 and Reynolds numbers from 8.5 x 10(exp 6) to 19.2 x 10(exp 6) at or near zero lift. Relative mass flow, average pressure recovery, total drag, internal drag, and external drag are presented as functions of Mach number. Between Mach numbers of 0.90 and 0.975, the external drag of the configuration (including base… more
Date: 1951
Creator: Mitcham, Grady L.; Stevens, Joseph E.; Crabill, Norman L. & Hinners, Arthur H., Jr.
Partner: UNT Libraries Government Documents Department
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