A Description of the Ames 2- by 2-foot Transonic Wind Tunnel and Preliminary Evaluation of Wall Interference
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Spiegel, Joseph M↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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The Origin and Distribution of Supersonic Store Interference from Measurement of Individual Forces on Several Wing-fuselage-store Configurations III : Swept-wing Fighter-bomber Configuration with Large and Small Stores. Mach Number, 1.61
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Smith, Norman F↗
Interference effects at Mach 1.9 on a horizontal tail due to trailing shock waves from an axisymmetric body with an exiting jet
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Salmi, Reino J↗
The Origin and Distribution of Supersonic Store Interference from Measurement of Individual Forces on Several Wing-fuselage-store Configurations V : Swept-wing Heavy-bomber Configuration with Large Store (nacelle). Mach Number 2.01
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Carson, Harry W↗
The Origin and Distribution of Supersonic Interference from Measurement of Individual Forces on Several Wing-fuselage-store Configurations VI : Swept-wing Heavy-bomber Configuration with Stores of Different Sizes and Shapes
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Smith, Norman F↗
Experimental Investigation of Interference Effects of Lateral-support Struts on Afterbody Pressures at Mach 1.9
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Klann, John L↗
An Investigation of Wing-body Juncture Interference Effects at Transonic Speeds for Several Swept-wing and Body Combinations
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Mcdevitt, John B↗
Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (including Canopy Shape Effects)
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Mcdearmon, Russel W↗
Free-flight Investigation to Determine Some Effects of Tail Damping and Wing-tail Interference on the Rolling Effectiveness of Ailerons and a Spoiler on a Modified-delta Wing at Mach Numbers from 0.6 to 1.5
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English, Roland D↗
The Sine-cosine Method for Reducing the Interference Pressure Drag of Sweptback Wings
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Faget, Maxime A↗
Steady loads due to jet interference on wings, tails, and fuselages at transonic speeds
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Swihart, John M↗
Effects of Sting-support Interference on the Drag of an Ogive-cylinder Body with and Without a Boattail at 0.6 to 1.4 Mach Number
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Lee, George↗
An Investigation of Supersonic Store Interference in the Vicinity of a 22 Degree Swept-wing--fuselage Configuration at Mach Numbers of 1.61 and 2.01
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Geier, Douglas J↗
Theoretical analysis of the interference effects of several supersonic-tunnel walls capable of absorbing the shock caused by the nose of a model
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Matthews, Clarence W↗
The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations II : swept-wing-heavy-bomber configuration with large store (nacelle). lateral forces and pitching moment
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Smith, Norman F↗
Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0
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Kremzier, Emil J↗
Quasi-cylindrical theory of wing-body interference at supersonic speeds and comparison with experiment
A theoretical method is presented for calculating the flow field about wing-body combinations employing bodies deviating only slightly in shape from a circular cylinder. The method is applied to the calculation of the pressure field acting between a circular cylindrical body and a rectangular wing. The case of zero body angle of attack and variable wing incidence is considered as well as the case of zero wing incidence and variable body angle of attack. An experiment was performed especially for the purpose of checking the calculative examples.
Nielsen, Jack N↗
Experimental Verification of the Theory of Wind-Tunnel Boundary Interference
The results of an experimental investigation on the boundary-correction factor are presented in this report. The values of the boundary-correction factor from the theory, which at the present time is virtually completed, are given in the report for all conventional types of tunnels. With the isolation of certain disturbing effects, the experimental boundary-correction factor was found to be in satisfactory agreement with the theoretically predicted values, thus verifying the soundness and sufficiency of the theoretical analysis. The establishment of a considerable velocity distortion, in the nature of a unique blocking effect, constitutes a principal result of the investigation.
Theodorsen, Theodore↗