TY - JOUR
T1 - The Effects of Tailplane Ice Accretion on Flight Stability of Commuter Category Aircraft for High Terrain Remote Areas Flight Operation
AU - Hakim, A. B.
AU - Nirbito, W.
AU - Adhitya, M.
N1 - Funding Information:
The authors wish to thank Universitas Indonesia for funding this research through PITTA grant program with contract number 2553/UN2.R3.1/HKP.05.00/2018. PT. Dirgantara Indonesia (Indonesian Aerospace) have supported this research providing facilities, guidance, and opportunity to contribute in commuter category aircraft development, thus, deserves our thanks.
Publisher Copyright:
© Published under licence by IOP Publishing Ltd.
PY - 2018/11/29
Y1 - 2018/11/29
N2 - The effect of ice accretion on the surface of the horizontal tail on aerodynamic characteristics and stability of commuter category aircraft is reviewed using predicted ice shapes and polar predictions using CFD software. Ice accretion prediction is carried out in various atmospheric conditions already listed in Appendix C FAR25 within remote high terrain flight operation condition. The predicted results of ice shapes are categorized according to the main shapes which will then be simulated using XFOIL. The resulting polar data then combined with data obtained from wind tunnel test to give lift coefficient predictions and the overall moment of the aircraft at zero flap condition. The most severe impact of ice accretion on the surface of the horizontal tail is found in the decreasing values of stalling angle of attack and maximum lift coefficient due to flow separation, with stalling angle of attack and maximum lift coefficient as low as 9.54 degrees and 0.765. The most visible decrease in static longitudinal stability and the static margin point are 6.88% and 6.34% from the normal condition.
AB - The effect of ice accretion on the surface of the horizontal tail on aerodynamic characteristics and stability of commuter category aircraft is reviewed using predicted ice shapes and polar predictions using CFD software. Ice accretion prediction is carried out in various atmospheric conditions already listed in Appendix C FAR25 within remote high terrain flight operation condition. The predicted results of ice shapes are categorized according to the main shapes which will then be simulated using XFOIL. The resulting polar data then combined with data obtained from wind tunnel test to give lift coefficient predictions and the overall moment of the aircraft at zero flap condition. The most severe impact of ice accretion on the surface of the horizontal tail is found in the decreasing values of stalling angle of attack and maximum lift coefficient due to flow separation, with stalling angle of attack and maximum lift coefficient as low as 9.54 degrees and 0.765. The most visible decrease in static longitudinal stability and the static margin point are 6.88% and 6.34% from the normal condition.
UR - http://www.scopus.com/inward/record.url?scp=85057739699&partnerID=8YFLogxK
U2 - 10.1088/1757-899X/449/1/012011
DO - 10.1088/1757-899X/449/1/012011
M3 - Conference article
AN - SCOPUS:85057739699
VL - 449
JO - IOP Conference Series: Materials Science and Engineering
JF - IOP Conference Series: Materials Science and Engineering
SN - 1757-8981
IS - 1
M1 - 012011
T2 - 2018 2nd International Conference on Aerospace Technology, Communications and Energy Systems, ATCES 2018
Y2 - 15 September 2018 through 17 September 2018
ER -