Aeronautical Research Councilhttps://reports.aerade.cranfield.ac.uk/handle/1826.2/12023-09-22T17:47:50Z2023-09-22T17:47:50ZNote on Wind-Tunnel Measurements of Yawing Moment, Rudder Fixed and Free, on Models of Three AircraftAdamson, J EBrown, E CAllen, R Hhttps://reports.aerade.cranfield.ac.uk/handle/1826.2/48712023-06-01T14:49:11Z1941-07-01T00:00:00ZNote on Wind-Tunnel Measurements of Yawing Moment, Rudder Fixed and Free, on Models of Three Aircraft
Adamson, J E; Brown, E C; Allen, R H
1941-07-01T00:00:00ZThe Equations of Hydrodynamics in a Very General FormCope, W Fhttps://reports.aerade.cranfield.ac.uk/handle/1826.2/48702023-02-28T11:30:22Z1942-11-01T00:00:00ZThe Equations of Hydrodynamics in a Very General Form
Cope, W F
1942-11-01T00:00:00ZThe design of wind tunnel fans.Collar, A. R.https://reports.aerade.cranfield.ac.uk/handle/1826.2/48692022-11-04T00:17:34Z1940-08-10T00:00:00ZThe design of wind tunnel fans.
Collar, A. R.
Summary.—The present report is one of a series dealing with N.P.L. methods for the design of return flow wind tunnels. Reports already issued deal with the design of the Compressed Air Tunnel¹ and Open Jet Tunnels,² with the design of corner cascades³ and fan straighteners, ⁴ and with the improvement of velocity distribution by means of windmills⁵ and gauzes.⁶
An explanation is now given of the method usually adopted in the design of fans for return flow tunnels ; as an example of the method, the design of the fan for the N.P.L. non-turbulent tunnel is considered in detail. It is shown that for a wind tunnel a fan with blades of constant chord is advisable ; and a formula is given by means of which a rapid estimate can be made of the variation in rotational speed of the fan corresponding to a variation in power factor at constant power.
1940-08-10T00:00:00ZStrip theory method of calculation for airscrews on high-speed aeroplanesLock, C. N. H.Pankhurst, R. C.https://reports.aerade.cranfield.ac.uk/handle/1826.2/41122020-11-15T15:26:45Z1945-10-01T00:00:00ZStrip theory method of calculation for airscrews on high-speed aeroplanes
Lock, C. N. H.; Pankhurst, R. C.
The report describes a simplified 8-point strip theory method of calculating the free-air performance of a propeller up to tip Mach numbers near the velocity of sound. It is based on the assumptions of R. & M. 1674 and 1849 together with the further simplifying assumption that the curve is straight (valid below the stall) and that the curve also is straight (valid for J > 1.0). The report includes tables of parameters which are required in the calculations as functions of J, r, and N for eight standard radii (r, = 0.3, 0.45, 0.6, 0.7, 0.8, 0.9, 0.95, 0.975) for the range of values of J from 1.0 t o 7.0; these are of universal application. In addition, tables of section data for various section shapes are required; these are given for Clark Y sections over a range of thickness in R. & M. 2036; they were derived, by methods described in R. & M. 2020, from overall measurements of thrust and torque on full scale propellers at low values of J in the Royal Aircraft Establishment 24-ft. tunnel and are subject to revision in the light of subsequent experimental research.
1945-10-01T00:00:00Z