Print Email Facebook Twitter Free-flight tests of vortex generator configurations at transonic speeds Title Free-flight tests of vortex generator configurations at transonic speeds Author Edwards, J.B.W. Institution Royal Aircraft Establishment RAE Date 1962-12-31 Abstract Tests have been made to investigate the effectiveness of vortex generators in alleviating the adverse effects of shock-induced boundarylaer separation. The variation in effectiveness of a flap control on an unswept wing in the transonic speed range was taken as a representative example of such effects since it lends itself easily to simple and reliable measurements by the free-night technique. Most of the configurations were successful in improving the transonic effectiveness, although one made matters worse. Three configurations maintained the improvement through to supersonic speeds where generators were not expected to have a beneficial effect. The results bear out previous findings remarkably well particularly those of small scale tests at N.P.L. This applies to both successful and unsuccessful configurations. To reference this document use: http://resolver.tudelft.nl/uuid:eed5534c-441d-46aa-b0a8-2de1c2c5ab8b Publisher Ministry of Aviation, Royal Aircraft Establishment, RAE Farnborough Access restriction Campus only Source RAE Technical Note No. Aero 2862 Part of collection Aerospace Engineering Reports Document type report Rights © 1962 Ministry of Aviation, Royal Aircraft Establishment Files PDF Tech_Note_Aero_2862.pdf 14 MB Close viewer /islandora/object/uuid:eed5534c-441d-46aa-b0a8-2de1c2c5ab8b/datastream/OBJ/view