Download or read book Wind Tunnel Results from a Nozzle Afterbody Test of a 0 2 Scale Fighter Aircraft in the Mach Number Regime of 0 6 to 1 5 Volume 1 Test Technique Evaluation written by Ernest J. Lucas and published by . This book was released on 1979 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Propulsion Wind Tunnel (16T) to determine the effect of throttle-dependent parameters (nozzle closure and nozzle pressure ratio) on the aft end surface pressures of a 0.2-scale model of a twin-engine fighter prototype (YF-17). The data are part of a data base to be used in a wind tunnel/flight correlation to define the validity of current wind tunnel test techniques to provide data for full-scale flight performance predictions. Surface pressure data were obtained on several model configurations, using a wingtip support system, to define the effects of nozzle closure and jet exhaust flow on the test article nacelle and nozzle surfaces. Two additional test entries were conducted on sting support systems to evaluate support system interference produced by the wingtip support system and to evaluate the annular-jet test technique.
Download or read book Wind Tunnel Results from a Nozzle Afterbody Test of a 0 2 Scale Fighter Aircraft in the Mach Number Regime of 0 6 to 1 5 Volume II Model Configuration and Environment Effects written by Ernest J. Lucas and published by . This book was released on 1979 with total page 349 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Propulsion Wind Tunnel (16T) to document the effect of throttle-dependent parameters (nozzle closure and nozzle pressure ratio) on the aft end surface pressures of a 0.2-scale model of a twin-engine fighter prototype (YF-17). The data are part of a data base to be used in a future analysis effort to define the validity of current wind tunnel test techniques to provide data for full-scale flight performance predictions.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1978 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1975 with total page 978 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Wind Tunnel Nozzle Afterbody Test Techniques Utilizing a Modern Twin Engine Fighter Geometry at Mach Numbers from 0 6 to 1 2 written by Ernest J. Lucas and published by . This book was released on 1980 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analyses of surface pressure data from wind tunnel tests conducted in the Propulsion Wind Tunnel (16T) on the 0.1- and 0.2-scale models of the YF-17 aircraft and flight tests conducted at the NASA Dryden Flight Research Center with the prototype YF-17 were conducted to substantiate the effectiveness of the subscale wind tunnel test techniques currently used at AEDC to provide data to evaluate throttle-dependent effects. The data were obtained at Mach numbers 0.6, 0.9, and 1.2 at characteristic Reynold numbers based on fuselage length from 14 million to 250 million. The data obtained at Mach numbers 0.6 and 0.9 indicate that valid techniques are available to obtain subscale wind tunnel data that are directly applicable to aft-end throttle-dependent flight performance prediction. The wind tunnel plume simulation techniques, however, do not provide data for directly predicting the flight vehicle, aft-end, calculated loads at Mach number 1.2. Additional corrections must be applied to the data to compensate for temperature effects associated with afterburning operations, such as that encountered at Mach 1.2.
Download or read book An Evaluation of Wind Tunnel Test Techniques for Aircraft Nozzle Afterbody Testing at Transonic Mach Numbers written by and published by . This book was released on 1980 with total page 183 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of many experiments to develop and verify wind tunnel test techniques for determining engine exhaust effects on aircraft performance at transonic Mach numbers are summarized. The influence of model support interference, exhaust jet simulation techniques, wind tunnel calibration-flow quality and operating conditions, model geometric effects, and measurement techniques n afterbody aerodynamic forces are discussed. Recommendations are given for reducing or eliminating adverse interference effects on wind tunnel test data.
Download or read book Wind Tunnel Tests of a 0 06 scale B 1 Model at Mach Numbers from 0 60 to 1 60 written by C. J. Spurlin and published by . This book was released on 1973 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1995 with total page 470 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel flight Data Correlation u written by James A. Behal and published by . This book was released on 1971 with total page 1104 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Download or read book Wind Tunnel flight Data Correlation u written by James A. Behal and published by . This book was released on 1971 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1981 with total page 1070 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tests of Submerged Duct Installation on a Modified Fighter Airplane in the Ames 40 by 80 foot Wind Tunnel written by Norman J. Martin and published by . This book was released on 1947 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flow Generation Properties of Five Transonic Wind Tunnel Test Section Wall Configurations written by R. L. Parker (Jr.) and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Simulator Study of Stall post stall Characteristics of a Fighter Airplane with Relaxed Longitudinal Static Stability written by and published by . This book was released on 1979 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NOL Hypervelocity Wind Tunnel written by Naval Ordnance Laboratory (White Oak, Md.). and published by . This book was released on 1971 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive cylinder Model at Mach Numbers 1 75 to 4 50 written by Neil Arthur Zarin and published by . This book was released on 1964 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Description and Preliminary Calibration Tests of a Small Arc heated Hypersonic Wind Tunnel written by William B. Boatright and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
