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Wind-tunnel investigation of a 1/60-scale model of the Republic MX-1554 airplane at a Mach number of 2.85

Description: Report presenting the results of an investigation to determine the static longitudinal and lateral stability and control characteristics of a model of the Republic MX-1554 airplane at a specified Mach and Reynolds number. No analysis was provided in the paper in order to expedite publication.
Date: March 18, 1953
Creator: Dickey, Robert R. & Spahr, J. Richard
Partner: UNT Libraries Government Documents Department

External-store drag reduction at transonic and low supersonic Mach numbers by application of Baldwin's moment-of-area rule

Description: Report presenting an investigation to evaluate the external-store drag reductions obtainable by application of Baldwin's moment-of-area rule. Several wing-body combinations were investigated with and without four typical air-to-air missiles. Results regarding the total-drag measurements, wave-drag components, and effectiveness of moment-of-area rule for reducing the drag of the external-store installations are provided.
Date: March 5, 1956
Creator: Levy, Lionel L., Jr. & Dickey, Robert R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds

Description: Report presenting an investigation of the flow field behind triangular wings alone and in combination with a pointed cylindrical body at Mach numbers of 1.5 and 2.0 through an angle-of-attack range of 0 to 24 degrees. Results regarding the geometric characteristics of the vortex system and downwash characteristics are provided.
Date: June 25, 1953
Creator: Spahr, J. Richard & Dickey, Robert R.
Partner: UNT Libraries Government Documents Department

Effect of tail surfaces on the base drag of a body of revolution at Mach numbers of 1.5 and 2.0

Description: "Wind-tunnel tests were performed at Mach numbers of 1.5 and 2.0 to investigate the influence of tail surfaces on the base drag of a body of revolution without boattailing and having a turbulent boundary layer. The tail surfaces were of rectangular plan form of aspect ratio 2.33 and has symmetrical, circular-arc airfoil section. The results of the investigation showed that the addition of these tail surfaces with the trailing edges at or near the body base incurred a large increase in the base-drag coefficient. For a cruciform tail having a 10-percent-thick airfoil section, this increase was about 70 percent at a Mach number of 1.5 and 35 percent at a Mach number of 2.0" (p. 1).
Date: April 1951
Creator: Spahr, J. Richard & Dickey, Robert R.
Partner: UNT Libraries Government Documents Department