| 1. | Numerical simulation of thrust reversal - ONERA's Science Pictures |
| | At the request of the companies Snecma and Teuchos of the Safran group, Andheo, a partner of Onera, has just carried out a Cedre evaluation of configurations of nacelles with thrust reversers deployed.... The calculation was carried out on a configuration proposed by Teuchos : one nacelle in the rear position on a generic wings-fuselage-rudder configuration.... |
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| 2. | ONERA's SAR radar imagery presented at the Salon-de-Provence Onera Center |
| | The Sethi concept is based on the installation of two nacelles - or pods - which can hold four radar sensors and two optical sensors, under the wings of a Falcon 20. It is a new, compact, quickly operational and thoroughly original means of observing the Earth : it brings together all the benefits of SAR imagery and facilitates the testing of new sensors with its plug and play adaptability.... |
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| 3. | Aerodynamics of Helicopters - Tilt-Rotor Aircraft - ONERA / DAAP-EN |
| | H2T's activities, in the framework of these projects, concern aerodynamic and aeroacoustic optimization studies (in collaboration with the DSNA) of the rotor, along with the analysis of the interactions between the rotor, the nacelle and the wings for the different phases of flight of the tilt-rotor aircraft.... |
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| 4. | Test on the Elfin2 Nacelle - ONERA's Science Pictures |
| | Test on the Elfin2 Nacelle - ONERA's Science PicturesWho are we ?Science Pictures... Test on the Elfin2 Nacelle copyright © ONERA 1996-2006. Tests on the ELFIN 2 hybrid laminarity nacelle in the Modane-Avrieux wind-tunnel (). Pictures. |
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| 5. | Surface Measurement Techniques : Pressure Sensitive Paints (PSP) - ONERA's Science Pictures |
| | PSP global pressures on a commercial airliner model equipped with an engine nacelle. ()... |
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| 6. | RHILP [ Handling Qualities ] |
| | First, the rotor-borne mode with the nacelles tilted around 90 degrees (w. r. t. the longitudinal body axis), which is more or less like a helicopter flight and is mainly used to achieve vertical take-offs and landings.... Second, the wing-borne mode with the nacelles tilted at its most forward position.... |
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| 7. | RHILP [ tbd ] |
| | The download model for the tilt-rotor in hover and in helicopter mode (nacelle at 90 °) is based on two curves representing the evolution of : - the download with rotor thrust at a given wing flap angle, - the download with the flap angle.... Influence of the forward speed and nacelle angle... The model used in hover has been extended to take into account both the forward speed and the nacelle tilt angle.... |
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| 8. | RHILP [ tbd ] |
| | They mainly concern the aerodynamic interactions between rotors and wing, in helicopter mode, in hover and low speed conditions (nacelle angle between 80 ° and 100 ° and forward speeds up to 90 kts).... The tests have been conducted, using a powered model for three different configurations : an isolated rotor, used to measure performance characteristics with zero and non-zero forward speeds ; a half-span model (starboard side) with one rotor, a nacelle, a half-span wing and a half-fuselage set on an image plane : this configuration has been used for hover and forward flight tests ; a rotor + wing model with one rotor, a nacelle and a half-span wing, used to investigate the effect of the fountain flow phenomena on rotor performance and on wing download (through comparison with half-span tests).... |
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| 9. | RHILP [ tbd ] |
| | With nacelle angle set to 90 ° degrees (helicopter mode) following effects have been investigated at different wing flap settings and rotor thrust levels : - ground effect, - fountain flow effect, - rotor to wing distance, - lateral flapping of rotor disc.... |
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| 10. | No title |
| | 2 = wing drag coefficient at - 90 ° angle of attack CF = flap chord, m Ct = rotor thrust coefficient, / [ 2 ] CW = wing chord, m DL = wing download, N Dnac = nacelle tilt angle, ° Fx-cel = fuselage + wing force along x aircraft axis, DaN Fz-cel = fuselage + wing force along z aircraft axis, DaN PW-RD = rotor power for the right rotor, kW PW-RG = rotor power for the left rotor, kW S = wing surface, m²... |
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