Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests
This report presents the results of experimental investigations into the interaction between the propellers (Ps) and the airframe of a twin-engine, twin-boom light transport aircraft with a Π-shaped tail. An analysis was performed of the forces and moments acting on the aircraft with rotating Ps. Th...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
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CTU Central Library
2004-01-01
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| Series: | Acta Polytechnica |
| Subjects: | |
| Online Access: | https://ojs.cvut.cz/ojs/index.php/ap/article/view/530 |
| _version_ | 1818021832369897472 |
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| author | A. V. Petrov Y. G. Stepanov M. V. Shmakov |
| author_facet | A. V. Petrov Y. G. Stepanov M. V. Shmakov |
| author_sort | A. V. Petrov |
| collection | DOAJ |
| description | This report presents the results of experimental investigations into the interaction between the propellers (Ps) and the airframe of a twin-engine, twin-boom light transport aircraft with a Π-shaped tail. An analysis was performed of the forces and moments acting on the aircraft with rotating Ps. The main features of the methodology for windtunnel testing of an aircraft model with running Ps in TsAGI’s T-102 wind tunnel are outlined.<br />The effect of 6-blade Ps slipstreams on the longitudinal and lateral aerodynamic characteristics as well as the effectiveness of the control surfaces was studied on the aircraft model in cruise and takeoff/landing configurations. The tests were conducted at flow velocities of <em>V</em><em>∞ =</em> 20 to 50 m/s in the ranges of angles of attack α = -6 to 20 deg, sideslip angles of β = -16 to 16 deg and blade loading coefficient of B 0 to 2.8. For the aircraft of unusual layout studied, an increase in blowing intensity is shown to result in decreasing longitudinal static stability and significant asymmetry of the directional stability characteristics associated with the interaction between the Ps slipstreams of the same (left-hand) rotation and the empennage. |
| first_indexed | 2024-04-14T08:23:22Z |
| format | Article |
| id | doaj.art-9b8627e775d04622b30e4a0c071009d8 |
| institution | Directory Open Access Journal |
| issn | 1210-2709 1805-2363 |
| language | English |
| last_indexed | 2024-04-14T08:23:22Z |
| publishDate | 2004-01-01 |
| publisher | CTU Central Library |
| record_format | Article |
| series | Acta Polytechnica |
| spelling | doaj.art-9b8627e775d04622b30e4a0c071009d82022-12-22T02:04:09ZengCTU Central LibraryActa Polytechnica1210-27091805-23632004-01-01442530Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of TestsA. V. PetrovY. G. StepanovM. V. ShmakovThis report presents the results of experimental investigations into the interaction between the propellers (Ps) and the airframe of a twin-engine, twin-boom light transport aircraft with a Π-shaped tail. An analysis was performed of the forces and moments acting on the aircraft with rotating Ps. The main features of the methodology for windtunnel testing of an aircraft model with running Ps in TsAGI’s T-102 wind tunnel are outlined.<br />The effect of 6-blade Ps slipstreams on the longitudinal and lateral aerodynamic characteristics as well as the effectiveness of the control surfaces was studied on the aircraft model in cruise and takeoff/landing configurations. The tests were conducted at flow velocities of <em>V</em><em>∞ =</em> 20 to 50 m/s in the ranges of angles of attack α = -6 to 20 deg, sideslip angles of β = -16 to 16 deg and blade loading coefficient of B 0 to 2.8. For the aircraft of unusual layout studied, an increase in blowing intensity is shown to result in decreasing longitudinal static stability and significant asymmetry of the directional stability characteristics associated with the interaction between the Ps slipstreams of the same (left-hand) rotation and the empennage.https://ojs.cvut.cz/ojs/index.php/ap/article/view/530windtunnel testingpropeller slipstreamengine failuretest methodology |
| spellingShingle | A. V. Petrov Y. G. Stepanov M. V. Shmakov Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests Acta Polytechnica windtunnel testing propeller slipstream engine failure test methodology |
| title | Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests |
| title_full | Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests |
| title_fullStr | Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests |
| title_full_unstemmed | Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests |
| title_short | Development of a Technique and Method of Testing Aircraft Models with Turboprop Engine Simulators in a Small-scale Wind Tunnel - Results of Tests |
| title_sort | development of a technique and method of testing aircraft models with turboprop engine simulators in a small scale wind tunnel results of tests |
| topic | windtunnel testing propeller slipstream engine failure test methodology |
| url | https://ojs.cvut.cz/ojs/index.php/ap/article/view/530 |
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