Author: Mary L. MasonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 224
Book Description
Static Investigation of Several Yaw Vectoring Concepts on Nonaxisymmetric Nozzles
Author: Mary L. MasonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 224
Book Description
Static Investigation of Several Yaw Vectoring Concepts on Nonaxisymmetric Nozzles
Author: Mary L. MasonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 216
Book Description
Static Investigation of Several Yaw Vectoring Concepts on Nonaxisymmetric Nozzles
Author: Mary L. MasonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 224
Book Description
Static Performance of Nonaxisymmetric Nozzles with Yaw Thrust-Vectoring Vanes
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722772338
Category :
Languages : en
Pages : 76
Book Description
A static test was conducted in the static test facility of the Langley 16 ft Transonic Tunnel to evaluate the effects of post exit vane vectoring on nonaxisymmetric nozzles. Three baseline nozzles were tested: an unvectored two dimensional convergent nozzle, an unvectored two dimensional convergent-divergent nozzle, and a pitch vectored two dimensional convergent-divergent nozzle. Each nozzle geometry was tested with 3 exit aspect ratios (exit width divided by exit height) of 1.5, 2.5 and 4.0. Two post exit yaw vanes were externally mounted on the nozzle sidewalls at the nozzle exit to generate yaw thrust vectoring. Vane deflection angle (0, -20 and -30 deg), vane planform and vane curvature were varied during the test. Results indicate that the post exit vane concept produced resultant yaw vector angles which were always smaller than the geometric yaw vector angle. Losses in resultant thrust ratio increased with the magnitude of resultant yaw vector angle. The widest post exit vane produced the largest degree of flow turning, but vane curvature had little effect on thrust vectoring. Pitch vectoring was independent of yaw vectoring, indicating that multiaxis thrust vectoring is feasible for the nozzle concepts tested. Mason, Mary L. and Berrier, Bobby L. Langley Research Center...
NASA Technical Paper
Author: Static Thrust-vectoring Performance of Nonaxisymmetric Convergent-divergent Nozzles with Post-exit Yaw Vanes
Author: Robert J. FoleyPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 88
Book Description
Effects of Internal Yaw-Vectoring Devices on the Static Performance of a Pitch-Vectoring Nonaxisymmetric Convergent-Divergent Nozzle
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781723039362
Category :
Languages : en
Pages : 116
Book Description
An investigation was conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to evaluate the internal performance of a nonaxisymmetric convergent divergent nozzle designed to have simultaneous pitch and yaw thrust vectoring capability. This concept utilized divergent flap deflection for thrust vectoring in the pitch plane and flow-turning deflectors installed within the divergent flaps for yaw thrust vectoring. Modifications consisting of reducing the sidewall length and deflecting the sidewall outboard were investigated as means to increase yaw-vectoring performance. This investigation studied the effects of multiaxis (pitch and yaw) thrust vectoring on nozzle internal performance characteristics. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 13.0. The results indicate that this nozzle concept can successfully generate multiaxis thrust vectoring. Deflection of the divergent flaps produced resultant pitch vector angles that, although dependent on nozzle pressure ratio, were nearly equal to the geometric pitch vector angle. Losses in resultant thrust due to pitch vectoring were small or negligible. The yaw deflectors produced resultant yaw vector angles up to 21 degrees that were controllable by varying yaw deflector rotation. However, yaw deflector rotation resulted in significant losses in thrust ratios and, in some cases, nozzle discharge coefficient. Either of the sidewall modifications generally reduced these losses and increased maximum resultant yaw vector angle. During multiaxis (simultaneous pitch and yaw) thrust vectoring, little or no cross coupling between the thrust vectoring processes was observed. Asbury, Scott C. Langley Research Center CONVERGENT-DIVERGENT NOZZLES; DEFLECTORS; FLAPS (CONTROL SURFACES); NOZZLE FLOW; PITCH (INCLINATION); PROPULSION SYSTEM PERFORMANCE; STATIC TESTS; THRUST VECTOR CONTROL; WIND TUNNEL TESTS; YAW; DISCHARGE COEFFICIENT; NOZZLE INSERTS; ...
Static Investigation of Two STOL Nozzle Concepts with Pitch Thrust-vectoring Capability
Author: Mary L. MasonStatic Performance Investigation of a Skewed-throat Multiaxis Thrust-vectoring Nozzle Concept
Author: David J. WingNASA Technical Paper
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 432
Book Description