Two matrix methods for calculating forcing functions from known responses
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MATHEMATICS - MATRICES↗
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Results for “CALCULATION METHODS”
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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Method of calculating the lateral motions of aircraft based on the Laplace transform
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EQUATIONS - MOTION↗
An Approximate Method of Calculating Pressures in the Tip Region of a Rectangular Wing of Circular-Arc Section at Supersonic Speeds
No abstract available
PRESSURE DISTRIBUTION - WING TIPS↗
An improved approximate method for calculating lift distributions due to twist
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LIFT DISTRIBUTION - WINGS, SWEPTBACK↗
A method for calculating stresses in torsion-box covers with cutouts
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BOXES - STRESSES EFFECT OF CUT-OUTS↗
Method for calculating downwash field due to lifting surfaces at subsonic and supersonic speeds
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FLOW, SUPERSONIC↗
A biharmonic relaxation method for calculating thermal stress in cooled irregular cylinders
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Holms, Arthur G↗
Practical methods of calculation involved in the experimental study of an autopilot and the autopilot-aircraft combination
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CONTROLS - FREQUENCY RESPONSE↗
Method for Calculation of Ram-jet Performance
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CHARTS - PERFORMANCE - ENGINES, RAM-JET↗
Approximate methods for calculating the flow about nonlifting bodies of revolution at high supersonic airspeeds
Explicit expressions are developed which yield the Mach number and pressure distributions on the surfaces of pointed nonlifting bodies of revolution operating at high supersonic airspeeds and at values of the hypersonic similarity parameter (ratio of free-stream Mach number to slenderness ratio) greater than 1. Very simple explicit expressions are obtained for these distributions in the special case of slender bodies. In the case of cones, the analytic solutions accurately define the entire flow field over a wide range of free-stream Mach numbers and apex angles.
Eggers, A J , Jr↗
Simplified method for calculation of compressible laminar boundary with arbitrary free-stream pressure gradient
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Low, George M↗
Method for Calculation of Heat Transfer in Laminar Region of Air Flow Around Cylinders of Arbitrary Cross Section (including Large Temperature Differences and Transpiration Cooling)
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Eckert, E R G↗
Method for calculation of compressible laminar boundary-layer characteristics in axial pressure gradient with zero heat transfer
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Morduchow, Morris↗
A simple approximate method for calculating spanwise lift distributions and aerodynamic influence coefficients
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WINGS, COMPLETE - ASPECT RATIO↗
An Approximate Method of Calculating the Deformations of Wings Having Swept, M or W, ? and Swept-tip Plan Forms
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Zender, George W↗
A Method for Calculating the Subsonic Steady-state Loading on an Airplane with a Wing of Arbitrary Plan Form and Stiffness
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Gray, W L↗
Method for calculation of compressible laminar boundary layer with axial pressure gradient and heat transfer
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Libby, Paul A↗
A Method for Calculating the Contour of Bodies of Revolution with a Prescribed Pressure Gradient at Supersonic Speed with Experimental Verification
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Burbank, Paige B↗