Download or read book Wind Tunnel Tests of a Joined wing Missile Model written by Jennifer Corneille and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Low Speed Wind Tunnel Test on Joined Wing and Monoplane Configurations Volume 1 Analysis of Results written by J. Wolkovitch and published by . This book was released on 1982 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: The joined wing is a new airplane and missile configuration comprising two wings, a fuselage, and a fin, such that the wings form diamond shapes both in plan view and front view. Advantages claimed for the joined wing include lightness, stiffness, low induced drag, low wave drag and high trimmed maximum lift coefficient. Comparative low-speed wind tunnel tests were performed on joined wing and conventional wing configurations having similar areas and spans. The effect of adding canard surfaces to the joined wing was investigated. The joined wing developed less induced drag than the comparable conventional wing, gave a higher maximum trimmed lift coefficient, and showed generally good stability and control characteristics, except for low directional stability. Favorable canard/joined wing interactions were found, yielding further increases in maximum lift coefficient. Volume I analyses the test data which are presented in Volume II.
Download or read book Low Speed Wind Tunnel Test on Joined Wing and Monoplane Configurations Volume 2 Test Data Phase II written by J. Wolkovitch and published by . This book was released on 1982 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: The joined wing is a new airplane and missile configuration comprising two wings, a fuselage, and a fin, such that the wings form diamond shapes both in plan view and front view. Advantages claimed for the joined wing include lightness, stiffness, low induced drag, low wave drag and high trimmed maximum lift coefficient. Comparative low-speed wind tunnel tests were performed on joined wing and conventional wing configurations having similar areas and spans. Long and short fuselages were tested, and the effect of adding canard surfaces to the joined wing was investigated. Test Reynolds numbers were typically 0.22 million. The present report (Volume II) presents the test data, which are analyzed in Volume I. (Author).
Download or read book A Wind Tunnel Investigation of Joined Wing Scissor Morphing written by Christopher Dike and published by . This book was released on 2006 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Tests on a Missile Model with Canard Wings written by R. E. DE Kuyper and published by . This book was released on 1973 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were performed in an Calspan Corporation (formerly Cornell Aeronautical Laboratory) Eight-Foot Transonic Wind Tunnel on a missile model with canard wings. The tests were conducted during the end of April and the beginning of May, 1973. Two distinctly different investigations were made. The effect of canard wing positions, canard - tail angular orientation, canard size, model roll angle, and nose shape, were investigated during the Aerodynamic Test Phase. The use of canard wings for roll attitude control was also investigated during this phase. The effect of different jet plumes on the aerodynamic model loads were studied during the Thrust Effect Phase. A normal jet plume simulator was used and the effects of model tail position, planform, and orientation were investigated. The report presents details of the test program and the results in tabular form.
Download or read book Supersonic Wind Tunnel Tests of Ring wing Configurations written by Leon H. Schindel and published by . This book was released on 1958 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Tests on a Missile Model with Canard Wings written by R. E. DE Kuyper and published by . This book was released on 1973 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Volume 3 of a three volume report tabulates aerodynamic and thrust test data on a wind tunnel model of a guided missile with canard wings. Included are tail fin force and moment coefficients.
Download or read book Transonic Wind Tunnel Tests on a Missile Model with Canard Wings written by R. E. DE Kuyper and published by . This book was released on 1973 with total page 674 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report is Volume 2 of a three volume series. Tables of aerodynamic test data are given, including balance cavity and base pressure coefficients, axial force for aerodynamic and thrust phases, canard position, and force and moment coefficients for a series of runs.
Download or read book Large scale Wind tunnel Tests of an Airplane Model with an Unswept Tilt Wing of Aspect Ration 5 5 and with Four Propellers and Blowing Flaps written by James A. Weiberg and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Aerodynamic Forces and Moments at Low Speed of a Missile Model During Simulated Launching from the Midsemispan Location of a 45 Degree Sweptback Wing fuselage Combination written by William J. Alford and published by . This book was released on 1955 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made at low speed to determine the aerodynamic forces and moments of a missile model during a simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage combination, including the effects on the missile forces and moments of a pylon support.
Download or read book Transonic Wind Tunnel Tests on a Missile Model with Canard Wings Volume I written by and published by . This book was released on 1973 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were performed in an Calspan Corporation (formerly Cornell Aeronautical Laboratory) Eight-Foot Transonic Wind Tunnel on a missile model with canard wings. The tests were conducted during the end of April and the beginning of May, 1973. Two distinctly different investigations were made. The effect of canard wing positions, canard - tail angular orientation, canard size, model roll angle, and nose shape, were investigated during the Aerodynamic Test Phase. The use of canard wings for roll attitude control was also investigated during this phase. The effect of different jet plumes on the aerodynamic model loads were studied during the Thrust Effect Phase. A normal jet plume simulator was used and the effects of model tail position, planform, and orientation were investigated. The report presents details of the test program and the results in tabular form.
Download or read book A Technique for Firing Dynamically Scaled Missile Models in Wind Tunnels and for Measuring Rocket motor Sound and Pressure Fluctuations written by William J. Alford and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Large scale Wind tunnel Tests of an Airplane Model with an Unswept Tilt Wing of Aspect Ratio 5 5 and with Various Stall Control Devices written by James A. Weiberg and published by . This book was released on 1964 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Tests of a Base Drag Research Missile Model written by B. F. Gorin and published by . This book was released on 1970 with total page 583 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in order to obtain data describing the effects of various simulated rocket exhaust plumes on the model's external flow field. Data describing the flow in the nozzle exit plane and in the model boundary layer were also obtained. Model external static pressure measurements were made and Schlieren, shadowgraph and tuft photographs were taken. The tests were conducted at Mach numbers from 0.000 to 1.200 at angles of attack from -2 to +2 degrees. The report presents details of the test program, an outline of the test procedure and the results of the investigation in tabular form. (Author).
Download or read book Wind tunnel Tests on a Wingless Missile with Symmetrical Blowing Side Jets fluid Wings at Mach Numbers of 2 16 2 48 and 2 85 written by C. Carl Brindle and published by . This book was released on 1963 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind-tunnel investi gation of symmetrical blowing from the sides of a wingless missile body (Fluid Wings). The tests were conducted at Mach numbers of 2.16, 2.48, and 2.85. The effects of various slot lcations and supply pressures for the fluid wing upon the longitudinal characteristics of the missile are indicated. The increase in the operational Mach number range of winged guided missiles is seri ously affected by the limitations of the lifting and control surfaces. These conventional sur faces become a source of high wave drag and present difficult structural and aerodynamic heating problems at high speeds. Some of these high-speed problems could be minimized by the use of a wingless missile with jet blowing, in lieu of the conventional surfaces, to control the missile during flight. (Author).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Tests on an Oscillating Wing with External Stores written by H. Tijdeman and published by . This book was released on 1978 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was carried out on an oscillating model of the F-5 wing with and without an external store (AIM-9J missile). The store was mounted at the wing tip as well as at a pylon underneath the wing. Detailed steady and unsteady pressure distributions were measured over the wing, while on the store aerodynamic loads were obtained. In addition, wind-tunnel wall pressures were recorded. The tests covered the Mach numbers of 0.6, 0.8, 0.95, 1.0, 1.05, 1.1, 1.2 and 1.35 and oscillatory frequencies of 0.20, and 40 Hz.
