Development of a multi-component internal strain-gauge balance for model tests in a cryogenic wind tunnel

A three-component internal strain-gauge balance for use in a cryogenic wind tunnel has been developed by NLR. With this balance model tests were performed in the NASA 0.3-m Transonic Cryogenic Tunnel. The results are discussed with a view to the development of strain-gauge balances for the ETW.

The international vortex flow experiment: A test case for compressible Euler codes

As part of the joint International Vortex Flow Experiment, force and pressure measurements have been carried out on a 65 deg delta wing configuration in the transonic and supersonic wind tunnels of NLR. Out of these data three test cases were selected by the organizing committee of the GAMM WORKSHOP on the "Numerical Simulation of Compressible...

Description and validation of the two-dimensional test setup for multiple airfoils in the pressurized wind tunnel HST

A description is given of the two-dimensional test setup in the pressurized wind tunnel HST of the NLR, for the testing of multiple airfoils at high Reynolds numbers. Results of the first tests with this setup are validated. For this validation a number of additional tests were performed in the HST as well as in the atmospheric wind tunnel HST 3...

Evaluation of Thing's method for the calculation of the lift discription on a wing in propulsive jets

The calculation method presented by Ting, Liu and Kleinstein in reference 3 has been subjected to an evaluation study, principally on the basis of experimental data obtained from special experiments on a half wing immersed in two jets. Very satisfactory results were found for the unflapped wing lying centrally within the jets. Both flap...

Evaluation of Levinsky's method for the calculation of the lift distribution on a wing in propulsive jets

Based on comparison with results from special experiments, an evaluation has been performed of the method of Levinsky, Thommen, Yager and Holland, which is intended to calcxilate the spanwise lift distribution on wings immersed in propulsive jets. Various modifications of the original method have been investigated. It was found that the method,...

Wind-tunnel measurements on the interference between a jet and a wing, located outside the jet. Part I: text, tables and figures

This report describes a wind-tunnel investigation on the interference between a jet and a wing half model, located outside the jet. Pressure distributions on the wing, and lift coefficients calculated from those have been used for evaluation of a method developed at NLR for the prediction of interference effects between jets and parts of...

Evaluation of a method for the prediction of jet-airframe interference

A brief description is given of a method, developed at NLR for the prediction of interference effects between (propulsion) jets and parts of airframes. The jet flow region is described by a model for a jet in a nonuniform mainflow, accounting for the presence of the airframe. The potential flow field around the airframe-jet combination is...

Evaluation of a potential theoretical model of the wake behind a wing via comparison of measurements and calculations

The present report considers the validity of the representation of the wake by discrete trailing vortices as is common practice in potential theoretical calcualtions. Theoretical results, obtained with a method developed at NLR, are compared with experimental results obtained at NLR for a 30° swept back wing. The shape of the vortex sheet as...