Download or read book Top mounted Inlet Performance for a V STOL Fighter attack Aircraft Configuration written by and published by . This book was released on 1987 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Inlet and Airframe Compatibility for a V STOL Fighter attack Aircraft with Top mounted Inlets written by and published by . This book was released on 1982 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Top mounted Inlet System Feasibility for Transonic supersonic Fighter Aircraft written by and published by . This book was released on 1981 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Flow Field Study for Top Mounted Inlets on Fighter Aircraft Configurations written by Steven W. Prince and published by . This book was released on 1979 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flow visualization study was conducted for top mounted inlets on fighter aircraft. A generic fighter model was tested at low speed in a wind tunnel with a tuft grid mounted on the upper fuselage. Tuft patterns were photographed in four longitudinal positions from 0- to 39-deg angle of attack and from 0- to 30-deg sideslip. Various configurations were tested with a high or low delta wing, two leading edge extensions and two canards. The results indicate that the downwash from leading edge extensions or canards can produce fairly smooth and straight flow to high angles of attack and moderate angles of sideslip for an inlet mounted on the upper fuselage surface. (Author).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1979-11 with total page 1126 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Assessment of Aerodynamic Performance of V STOL and STOVL Fighter Aircraft written by and published by . This book was released on 1984 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book V STOL Concepts in the United States Past Present and Future written by and published by . This book was released on 1984 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advances in Aeronautical Sciences Proceedings written by International Council of the Aeronautical Sciences and published by . This book was released on 1982 with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical and Experimental Engine inlet Flow Fields for Fighter Forebodies written by Steven F. Yaros and published by . This book was released on 1984 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Evaluation of Engine Auxiliary Inlet Design for Supersonic V Stol Aircraft written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-08 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: A higher order panel method is used to evaluate the potential flow of a two dimensional supersonic V/STOL inlet. A non-symmetric analytical inlet model is developed to closely match a wind tunnel model. The analytical inlet is analyzed for flow characteristics around the lower cowl lip and auxiliary inlets. The results are obtained from the output of a computer program that is based on the Hess Panel Method which determines source strengths of panels distributed over a three dimensional body. The analytical model was designed for the implementation of drooped/translated cowl lip and auxiliary inlets as flow improvement concepts. A 40 or 70 degree droop lip can be incorporated on the inlet to determine if these geometry modifications result in flow improvements which may reduce the propensity for flow separation on the interior portion of the lip. Auxiliary inlets are employed to decrease the mass flow over the inlet lip. Thus, the peak flow velocity is reduced at the lip which also lessens the likelihood of flow separation on the interior portion of the lip. A 2, 4, and 6 inch translated lip can be employed to also decrease mass flow over the inlet lower lip in the same manner as the auxiliary inlet. The performance results of the flow improvement concepts show that three possible inlet configurations provide a situation where separation is less likely to occur. A 70 degree droop lip maintains flow conditions such that attached flow over the lower cowl lip may exist for the entire angle of attack range studied. A 0 degree droop and translated lip combination provides similar results for the angle of attack range. The third configuration consists of a 0 degree droop and auxiliary inlet combination. This configuration provides slightly less favorable results than the other two, but still allows for conditions favorable to attached flow within the inlet. Boles, Michael A. and Heavner, Richard L. Unspecified Center...
Download or read book Proceedings of the Congress of the International Council of the Aeronautical Sciences written by International Council of the Aeronautical Sciences. Congress and published by . This book was released on with total page 868 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Inlet Performance Characteristics of a Generalized 1 4 scale Tactical Aircraft Models at Transonic and Supersonic Mach Numbers written by R. F. Lauer (Jr.) and published by . This book was released on 1971 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP written by and published by . This book was released on 1988 with total page 520 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Special Course on Subsonic transonic Aerodynamic Interference for Aicraft written by and published by . This book was released on 1983 with total page 1204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reingestion Characteristics and Inlet Flow Distortion of V STOL Lift engine Fighter Configurations written by Jerry V. Kirk and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reingestion of exhaust gas into engine inlets during hover, and inlet flow distortion with the associated loss in total-pressure recovery during transition were studied using a largescale generalized lift-engine fighter model powered by 5-85 engines. Exhaust gas reingestion during hover was studied on a static test facility, and inlet flow distortion and total-pressure recovery loss were studied in the 40- by 80-foot wind tunnel. Two lift-engine arrangements were studied, the swiveling, retractable and the internally fixed. Both arrangements were subject to excessive thrust loss and compressor stalls due to reingestion when the engine exhaust was vectored nearly vertical. Vectoring the exhaust approximately 20' from vertical essentially eliminated reingestion problems. Vectoring the lift-engine exhaust forward and the lift-cruise engine exhaust aft tcr balance the aircraft and minimize reingestion appears to be a feasible means of allowing VTOL operation. Inlet flow distortion and total-pressure recovery were within acceptable limits for the swiveling, retractable lift-engine configuration. With the inlet guide vane installed to help turn the flow into the engine, the vertically mounted lift engines of the internally fixed configuration with an inlet radius to diameter ratio of 0.19 produced acceptable inlet flow distortion and totalpressure recovery results. Without the guide vane the nominal acceptable distortion level of 10 percent was exceeded at the higher velocity ratios.--P. i.
Download or read book Performance Study for Inlet Installations written by and published by . This book was released on 1992 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Recent Applications of Theoretical Analysis to V STOL Inlet Design written by Norbert O. Stockman and published by . This book was released on 1979 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: A brief description of the axisymmetric potential flow and boundary layer analysis methods used at the NASA Lewis Research Center, is presented. Application of this method to inlet problems arising from both tilt-nacelle and fixed-nacelle V/STOL aircraft configurations is illustrated. A three-dimensional inlet analysis computer program is described and the preliminary results presented. Finally, a suggested approach to optimum design of inlets for high angle-of-attack operation is discussed.
