ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Hybrid wing design of icing wind tunnel supercooled large droplet icing test
Received date: 2022-03-21
Revised date: 2022-04-12
Accepted date: 2022-05-06
Online published: 2022-05-19
Supported by
National Science and Technology Project
An icing wind tunnel supercooled large droplet icing test was carried out to verify the design criteria of a hybrid wing. The test conditions adopt the combination of large and small water drop nozzles to achieve the “double peak” distribution characteristic. The NACA0012 airfoil with a chord length of 0.50 m is used as the original airfoil， and the hybrid wing design criteria for engineering and airworthiness are employed to design the hybrid wing. The Navier-Stokes （NS） equation is used to calculate the airfoil pressure distribution with the goal of overlapping the stagnation point position of the hybrid wing with the original airfoil and the suction peak at the leading edge as much as possible. The designed chord length of the hybrid wing was shortened by 50%. The design effect of the hybrid wing was verified by the icing wind tunnel supercooled large droplet icing test. The ice shape characteristics of the original airfoil and the hybrid airfoil model are basically the same， and the ice height of the hybrid airfoil model is slightly higher. It was verified that the design criteria of the hybrid wing are still suitable for the icing wind tunnel supercooled large droplet icing test， providing technical support for the follow-up of the supercooled large droplet icing wind tunnel test of related civil aircraft models.
Jun SHU , Dongguang XU , Zhirong HAN , Si LI , Xiong HUANG . Hybrid wing design of icing wind tunnel supercooled large droplet icing test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(1) : 627182 -627182 . DOI: 10.7527/S1000-6893.2022.27182
| 1 | Title 14 Code of federal regulations， aeronautics and space， Part 25 Airworthiness standards： Transport category airplanes， Appendix C ［S］. Washington， D.C.： Federal Aviation Administration， 1949. |
| 2 | Title 14 Code of federal regulations， aeronautics and space， Part 25 Airworthiness standards： Transport category airplanes， Appendix O ［S］. Washington， D.C.： Federal Aviation Administration， 2014. |
| 3 | ZANTE J V， IDE R， STEEN L E. NASA Glenn icing research tunnel： 2012 cloud calibration procedure and results： NASA/TM—2015-218758［R］. Washington， D.C.： NASA， 2012. |
| 4 | VAN ZANTE J， IDE R， STEEN L C. NASA Glenn icing research tunnel： 2012 cloud calibration procedure and results［C］∥ 4th AIAA Atmospheric and Space Environments Conference. Reston： AIAA， 2012： 2012-2933. |
| 5 | POTAPCZUK M G， TSAO J C， KING-STEEN L C. Bimodal SLD ice accretion on a NACA 0012 airfoil model［C］∥ 9th AIAA Atmospheric and Space Environments Conference. Reston： AIAA， 2017： 2017-4478. |
| 6 | KING-STEEN L C， IDE R F. Creating a bimodal drop-size distribution in the NASA Glenn icing research tunnel［C］∥ 9th AIAA Atmospheric and Space Environments Conference. Reston： AIAA， 2017： 2017-4477. |
| 7 | POTAPCZUK M G， TSAO J C. Further examinations of bimodal SLD ice accretion in the NASA icing research tunnel［C］∥ 2018 Atmospheric and Space Environments Conference. Reston： AIAA， 2018： 2018-3182. |
| 8 | POTAPCZUK M G， TSAO J C. Bimodal SLD ice accretion on swept NACA 0012 airfoil models［C］∥ AIAA AVIATION 2020 FORUM. Reston： AIAA， 2020： 2020-2814. |
| 9 | ESPOSITO B M， BROWN K J， BACHALO W D. Application of optical methods for icing wind tunnel cloud simulation extension to supercooled large droplets［C］∥ 23rd Annual Conference on Liquid Atomization and Spray System. Ventura： ILASS， 2011. |
| 10 | BIAGIO M E. SLD calibration at CIRA icing wind tunnel cloud generation & measurements［R］. ［S.l.］： CIRA， 2012. |
| 11 | ORCHARD D M， CLARK C， OLESKIW M. Development of a supercooled large droplet environment within the NRC altitude icing wind tunnel［C］∥ SAE Technical Paper Series. Warrendale： SAE International， 2015： 2015-01-2092. |
| 12 | SAEED F， SELIG M S， BRAGG M B. Hybrid airfoil design method to simulate full-scale ice accretion throughout a given a range［J］. Journal of Aircraft， 1998， 35（2）： 233-239. |
| 13 | SAEED F， SELIG M S， BRAGG M B. Hybrid airfoil design procedure validation for full-scale ice accretion simulation［J］. Journal of Aircraft， 1999， 36（5）： 769-776. |
| 14 | FUJIWARA G E C， WIBERG B D， WOODARD B， et al. 3D swept hybrid wing design method for icing wind tunnel tests［C］∥ 6th AIAA Atmospheric and Space Environments Conference. Reston： AIAA， 2014： 2014-2616. |
| 15 | SAEED F， SELIG M S， BRAGG M B. Design of subscale airfoils with full-scale leading edges for ice accretion testing［J］. Journal of Aircraft， 1997， 34（1）： 94-100. |
| 16 | SAEE D F. Hybrid airfoil design methods for full-scale ice accretion simulation［D］. Chicago： University of Illinois， 1999. |
| 17 | MORTONSON A J. Use of hybrid airfoil design in icing wind tunnel tests of large scale swept wings［D］. Chicago： University of Illinois， 2012. |
| 18 | FUJIWARA G E C， BRAGG M B. Method for designing hybrid airfoils for icing wind-tunnel tests［J］. Journal of Aircraft， 2019， 56（1）： 137-149. |
| 19 | GUO T， ZHU C X， ZHU C L. Hybrid airfoil design for full-scale ice accretion test［J］. Transactions of Nanjing University of Aeronautics & Astronautics， 2013， 30（2）： 139-144. |
| 20 | 韩志熔， 赵克良， 颜巍. 格尼襟翼在冰风洞混合翼设计中的应用［J］. 航空学报， 2019， 40（2）： 522387. |
| HAN Z R， ZHAO K L， YAN W. Application of Gurney flap in hybrid-wing design for icing wind tunnel［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（2）： 522387 （in Chinese）. |
/
| 〈 |
|
〉 |
CJA