小型超音速飛行実験機の空力特性

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Title

小型超音速飛行実験機の空力特性

Author(s)

溝端, 一秀; 羽田, 尚太; 工藤, 摩耶; 笹山, 容資; 桑田, 耕明;

_{丸, 祐介; 湊, 亮二郎; 棚次, 亘弘; 新井, 隆景; 坪井, 伸幸}

Citation

室蘭工業大学紀要 Vol.58, pp.39-44 ,2009

Issue Date

2009-02

URL

http://hdl.handle.net/10258/428

Rights

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㧖 1 ᯏ᪾ࠪࠬ࠹ࡓᎿቇ⑼ 㧖 2 ᄢቇ㒮ඳ჻೨ᦼ⺖⒟ᯏ᪾ࠪࠬ࠹ࡓᎿቇኾ᡹㧘⃻㧔ᩣ㧕IHI 㧖 3 ᄢቇ㒮ඳ჻೨ᦼ⺖⒟ᯏ᪾ࠪࠬ࠹ࡓᎿቇኾ᡹㧘⃻ᧅᏻᏒ 㧖 4 ᄢቇ㒮ඳ჻೨ᦼ⺖⒟ᯏ᪾ࠪࠬ࠹ࡓᎿቇኾ᡹ 㧖 5 ᄢቇ㒮ඳ჻೨ᦼ⺖⒟⥶ⓨቝቮࠪࠬ࠹ࡓᎿቇኾ᡹ 㧖 6 ⥶ⓨቝቮᯏࠪࠬ࠹ࡓ⎇ⓥ࠮ࡦ࠲࡯ޔ⃻㧔⁛㧕ቝቮ⥶ⓨ⎇ ⓥ㐿⊒ᯏ᭴ቝቮ⑼ቇ⎇ⓥᧄㇱ㧖 7 ⥶ⓨቝቮᯏࠪࠬ࠹ࡓ⎇ⓥ࠮ࡦ࠲࡯ 㧖 8 ᄢ㒋ᐭ┙ᄢቇ 㧖 9 㧔⁛㧕ቝቮ⥶ⓨ⎇ⓥ㐿⊒ᯏ᭴ቝቮ⑼ቇ⎇ⓥᧄㇱ Abstract

Extensive and intensive studies are being carried out for creation of innovative fundamental technologies for realization of hypersonic aircraft and reusable space transportation systems. In the course of the studies, a small scale flight experimental vehicle is under development for validation of the technologies in real high-speed flight environments. The aerodynamic characteristics of the overall configuration of the vehicle are measured by wind tunnel tests at Mach numbers ranging from 0.3 to 2.0. The lift, drag, and pitching trim characteristics are evaluated and assessed in detail.

Keywords: Supersonic, Aerodynamics, Lift, Drag, Pitching Moment, Trim

㧝 ✜⸒ ᄢ㒽㑆ߩ㜞ㅦ⥶ⓨャㅍ߅ࠃ߮࿾⃿゠㆏߳ߩౣ૶ ↪ቝቮャㅍࠍ㕟ᣂߔࠆߎߣࠍ⋡ᜰߒߡޔቶ⯗Ꮏᬺ ᄢቇࠍਛᔃߣߒߡઁᯏ㑐ߩ⎇ⓥ⠪ߩදജࠍᓧߟߟޔ 㑐ㅪߔࠆၮ⋚ᛛⴚߩ⎇ⓥࠍㅴ߼ߡ޿ࠆ㧔㧝㧕_ޕ⎇ⓥ ߐࠇߚၮ⋚ᛛⴚࠍޔዊⷙᮨߥ߇ࠄ߽ᯏ૕ࠪࠬ࠹ࡓ ߿ࠛࡦࠫࡦࠪࠬ࠹ࡓߦ៞タߒߡޔ㜞ㅦ㘧ⴕⅣႺߦ ߅޿ߡߘߩᯏ⢻࡮ᕈ⢻ࠍታ⸽ߔࠆ⸘↹ߢ޽ࠆޕߎ ߩߚ߼ߩࡈ࡜ࠗࡦࠣ࠹ࠬ࠻ࡌ࠶࠼ߣߒߡޔో㐳 3m ⒟ᐲߩዊဳ⿥㖸ㅦ㘧ⴕታ㛎ᯏ㧔ήੱ㘧ⴕᯏ㧕ߩ㐿 ⊒⎇ⓥࠍㅴ߼ߡ޿ࠆޕ ⿥㖸ㅦ⥶ⓨᯏߩ㐿⊒ߩߚ߼ߦߪޔ੝㖸ㅦ߆ࠄㆫ 㖸ㅦࠍ⚻ߡ⿥㖸ㅦߦ⥋ࠆᐢ▸ߥ㘧ⴕㅦᐲߦߟ޿ߡޔ ✚ว⊛߆ߟ⹦⚦ߥⓨ᳇ജቇ⊛⍮⷗ࠍᔅⷐߣߔࠆޕ ߒ߆߽ޔ឴ജޔ᛫ജߛߌߢߥߊޔࡇ࠶࠴ࡦࠣ㧔❑ ំࠇ㧕ޔࡠ࡯࡝ࡦࠣ㧔ᮮំࠇ㧕ޔ߅ࠃ࡛߮࡯ࠗࡦ ࠣ㧔஍ំࠇ㧕ߦ㑐ߔࠆฦ⒳ߩ቟ቯᓸଥᢙࠍផቯߔ ࠆᔅⷐ߇޽ࠆޕ৻⥸ߦޔੑᰴర⠢ޔ⚦㐳‛૕ޔ╬ ߩන⚐ᒻ⁁‛૕ߦ㑐ߔࠆℂ⺰⊛ߥⓨജ⊛⍮⷗ߪ⦟ ߊ⍮ࠄࠇߡ޿ࠆ߇ޔⓨ᳇ജቇߩᧄ⾰⊛㕖✢ᒻᕈࠁ ߃ߦޔታ㓙⊛ߥ⥶ⓨᯏߩోᯏⓨ᳇․ᕈߪޔන⚐ᒻ

ዊဳ⿥㖸ㅦ㘧ⴕታ㛎ᯏߩⓨജ․ᕈ

Ḵ┵ ৻⑲*1_{㧘⠀↰ ዏᄥ*}2_{㧘Ꮏ⮮ ៺⡍*}3_{㧘╣ጊ ኈ⾗*}4_{㧘᪀↰ ⠹᣿*}5_㧘 ਣ ␭੺*6 㧘Ḋ ੫ੑ㇢*1 㧘᫜ᰴ ਗ਼ᒄ*7 㧘ᣂ੗ 㓉᥊*8 㧘ဝ੗ િᐘ*9

Aerodynamic Characteristics of a Small Scale Supersonic Flight

Experiment Vehicle

Kazuhide MIZOBATA, Syota HADA, Maya KUDO, Yousuke SASAYAMA, Koumei KUWADA, Yusuke MARU, Ryojiro MINATO, Nobuhiro TANATSUGU, Takakage ARAI

and Nobuyuki TSUBOI

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Ḵ┵ ৻⑲㧘⠀↰ ዏᄥ㧘Ꮏ⮮ ៺⡍㧘╣ጊ ኈ⾗㧘᪀↰ ⠹᣿㧘 ਣ ␭੺㧘Ḋ ੫ੑ㇢㧘᫜ᰴ ਗ਼ᒄ㧘ᣂ੗ 㓉᥊㧘ဝ੗ િᐘ ⁁‛૕ߩⓨജ․ᕈࠍ⿷ߒวࠊߖࠆߛߌߢߪផቯߒ 㔍޿ޕᓥߞߡޔℂ⺰ߦၮߠߊṶ➈⊛⎇ⓥߛߌߢߥ ߊޔታ㓙ߩ⒳ޘߩోᯏᒻ⁁ߦߟ޿ߡⓨജ․ᕈࠍ⹦ ⚦ߦ⺞ߴࠆߎߣࠍⓍߺ㊀ߨࠆᏫ⚊⊛ߥ⎇ⓥ߇ᔅ㗇 ߢ޽ࠆޕ ߒ߆ࠆߦޔߎࠇ߹ߢᚒ߇࿖ߢߪޔ㘧ⴕታ㛎ᯏߥ ࠄ߮ߦታ↪ᯏߩਔ㕙ߦ߅޿ߡ⿥㖸ㅦ⥶ⓨᯏߩ㐿⊒ ᯏળ߇߶ߣࠎߤή߆ߞߚߚ߼ޔ⥶ⓨᯏ⸳⸘ߦᔅⷐ ߥㆫ㖸ㅦ߅ࠃ߮⿥㖸ㅦߩోᯏⓨജߩ⎇ⓥ߇ᭂ߼ߡ ዋߥ޿ޕ৻ᣇޔ☨࿖߅ࠃ᰷߮Ꮊߢߪޔ╙ੑᰴ਎⇇ ᄢᚢߩ㗃߆ࠄ⎇ⓥ߇ㅴ߼ࠄࠇ⤘ᄢߥ⍮⷗߇⫾Ⓧߐ ࠇߡ޿ࠆޕߘߩ৻ㇱߪ DATCOM㧔㧞㧕_{ߣߒߡ౏⴫ߐ} ࠇߡ޿ࠆ߇ޔⓨജ․ᕈߩቯᕈ⊛௑ะࠍ⷗ࠆ⒟ᐲߩ ♖ᐲߒ߆஻߃ߡዬࠄߕޔታ㓙ߩ⥶ⓨᯏ⸳⸘ߦᔅⷐ ߥ᳓Ḱߩ⍮⷗ߪ࿖╷਄৻⽾ߒߡ⒁ඞߐࠇߡ޿ࠆޕ ᚒ߇࿖߇዁᧪ᄢ㒽㑆ߩ㜞ㅦ⥶ⓨャㅍ߅ࠃ߮࿾⃿゠ ㆏߳ߩౣ૶↪ቝቮャㅍߦ㑐ߒߡᛛⴚ⊛ߦ㊀ⷐߥ࿾ ૏ࠍᓧࠆߚ߼ߦߪޔ਄ㅀߩࠃ߁ߥታ㓙⊛ߥⓨജ⎇ ⓥࠍᣧᕆߦផㅴߔࠆߎߣ߇⢄ⷐߢ޽ࠆޕ ߘߎߢޔᧄ⎇ⓥߪޔ਄ㅀߩዊဳ⿥㖸ㅦ㘧ⴕታ㛎 ᯏࠍࠤ࡯ࠬࠬ࠲࠺ࠖߣߒߡޔታ㓙ߩ⿥㖸ㅦ⥶ⓨᯏ ߩ੝㖸ㅦ߆ࠄ⿥㖸ㅦ߹ߢߩᐢ▸ߥㅦᐲ㗔ၞߦ߅ߌ ࠆోᯏⓨജ․ᕈࠍ᣿ࠄ߆ߦߔࠆ੐ࠍ⋡⊛ߣߔࠆޕ ⿥㖸ㅦၞ߹ߢߩടㅦᕈ߇ᦼᓙߢ߈ࠆ෺⊒࡮㜞⠢ߩ ᯏ૕ᒻ⁁ࠍㆬ߮ޔࡑ࠶ࡂ 0.3㨪2.0 ߩ▸࿐ߩ㘑ᵢ⹜ 㛎㧔㘑⹜㧕ߦࠃߞߡోᯏⓨജ․ᕈࠍ⹏ଔߔࠆޕⓨ ജ․ᕈߩ㗄⋡ߣߒߡߪޔᧄⓂߢߪޔᦨ߽㊀ⷐߥ឴ ജޔ᛫ജޔ߅ࠃ߮ࡇ࠶࠴ࡦࠣࡕ࡯ࡔࡦ࠻ߩ㧟ߟࠍ ขࠅᛒ߁ޕ એਅޔ╙㧞▵ߢߪᯏ૕ߩⓨജᒻ⁁ߩ⸳⸘ౝኈࠍ ᭎⺑ߔࠆޕ╙㧟▵ߢߪ㘑ᵢ⹜㛎ߩ᭎⇛ࠍㅀߴࠆޕ ╙㧠▵ߢߪ㘑ᵢ⹜㛎ߩ⚿ᨐࠍ⹦ㅀߔࠆޕ╙㧡▵ߪ ⚿⺰ߢ޽ࠆޕ 㧞 ᯏ૕ߩⓨജ⸳⸘ 㧞㧚㧝 ోᯏⓨജᒻ⁁ߩ⸳⸘ᜰ㊎ ዊဳ⿥㖸ㅦ㘧ⴕታ㛎ᯏߦ៞タߒߡታ⸽ߐࠇࠆၮ ⋚ᛛⴚߪᄙጘߦᷰࠆߎߣ߇੍ᗐߐࠇࠆߚ߼ޔ㘧ⴕ ታ㛎ᯏߪᄙ᭽ߥ㘧ⴕࡊࡠࡈࠔࠗ࡞ߦኻᔕน⢻ߢ޽ ࠆߎߣ߇ᦸ߹ߒ޿ޕᒰ㕙ߪ Fig. 1 ߩࠃ߁ߥޔṖ⿛㔌㒽ޔ⥄ജ਄᣹࡮ടㅦޔ⿥㖸ㅦᎼ⥶ޔᷫㅦ࡮㒠ਅޔ ⌕㒽ࠕࡊࡠ࡯࠴ޔ߅ࠃ߮⌕㒽Ṗ⿛߆ࠄߥࠆ㘧ⴕࡊ ࡠࡈࠔࠗ࡞ࠍᗐቯߒߡ޿ࠆޕ ߎߩ㘧ⴕࡊࡠࡈࠔࠗ࡞ߩታ⃻ࠍ⋡ᜰߒߡ⒳ޘߩ ⓨജᒻ⁁ࠍ⠨᩺ߒޔ㘑⹜ߦࠃߞߡߘߩⓨജ․ᕈࠍ ᛠីߒߚޕߘߩ⚿ᨐޔ⿥㖸ㅦၞ߹ߢߩടㅦᕈ߇ᦼ ᓙߢ߈ࠆ෺⊒࡮㜞⠢ߩM2006ᒻ⁁ࠍᒰ㕙ߩࡌ࡯ࠬ ࡜ࠗࡦᒻ⁁ߦㆬቯߒߚ㧔㧟㧘㧠㧕_{ޕߘߩ․ᓽࠍTable 1} ߦޔ᭎ⷰࠍFig. 2ߦ␜ߔޕ߹ߚޔታᯏߣ㘑⹜ᮨဳߩ ኸᴺࠍTable 2ߦ␜ߔޕ

Fig.1. The tentative plan of the fight profile of a small-scale supersonic experimental vehicle㧚

Table 1. The design concept of the M2006 configuration.

㗄⋡ ⸳⸘ౝኈ ⋡⊛࡮ലᨐ ࠛࡦࠫࡦᢙ 㧞ၮ ផജߩჇᒝޕ ࠛࡦࠫࡦߩ៞ タ૏⟎ ⢵૕ਔ⣁ Άᢱ៞タࠬࡍ࡯ࠬߩ⏕଻ޕ ⢖ᤨߩ஍ំࠇࠍૐᷫޕ ⠢ᐔ㕙ᒻ ࠢ࡜ࡦࠢ࠻࡮ ࠕࡠ࡯ ቟ቯߥ❑᷵ߦࠃࠆ೸㔌․ᕈ ߩᡷༀߣ឴ജჇᒝޕ ㅧᵄ᛫ജߩૐᷫޕ ⠢ဳ ࠳ࠗࡗࡕࡦ࠼ ⠢ဳ ㅧᵄ᛫ജߩૐᷫޕ ⠢⢵㈩⟎ 㜞⠢ᑼ ᮮំࠇ቟ቯᕈߩ⏕଻ޕ q q q q ోนേ᣹㒠⥽

Fig. 2. The overview of the M2006 configuration. Table 2. Dimensions of the M2006 configuration.

Wind tunnel test model Real configuration Scale 1/5.7 1/1 Length [m] 0.55 3.12 Wing Span [m] 0.28 1.61 Wing Area [m2] 0.03 0.96 MAC [m] 0.14 0.80 Sweep-back Angle [deg.] 66, 61

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㧞㧚㧞 ᣹㒠⥽ 㘧ⴕࡊࡠࡈࠔࠗ࡞ߩోၞߦ߅޿ߡޔࡇ࠶࠴ࡦࠣߩ ࠻࡝ࡓߣ㕒቟ቯࠍ⏕଻ߔࠆߎߣ߇ᔅⷐߢ޽ࠆޕߘߩߚ ߼ߦޔዊߐߥ⥽ⷺߢᄢ߈ߥࡇ࠶࠴ࡦࠣࡕ࡯ࡔࡦ࠻ࠍⒿ ߋߎߣߩน⢻ߥోนേᑼ᳓ᐔየ⠢ࠍណ↪ߔࠆޕߎߩ᳓ ᐔየ⠢ߩ⻉రࠍ Table 3 ߦ␜ߔޕ

Table 3. Dimensions of the all-moving horizontal tail. Area [m2] 0.26 Moment arm [m] 1.20 Volumetric coefficient 0.40 Sweep-back angle [deg.] 50 㧞㧚㧟 ᣹㒠⥽ߩᓎഀ ޽ࠆᯏ૕ߩ㊀ᔃ߹ࠊࠅߩࡇ࠶࠴ࡦࠣࡕ࡯ࡔࡦ࠻ᦛ✢ ߩ৻଀ࠍFig. 3ߦ␜ߔޕ࿑ߩࠃ߁ߦᦛ✢ߩ௑߈dCM dD ߇⽶ߢ޽ࠇ߫ࡇ࠶࠴ࡦࠣߩ㕒቟ቯᕈߪ଻ߚࠇߡ޿ࠆޕ ߐࠄߦ㧘ᯏ૕ࠍቯᏱ㘧ⴕߐߖࠆߚ߼ߦߪࡇ࠶࠴ࡦࠣࡕ ࡯ࡔࡦ࠻ଥᢙ_C_M߇ 0 ߢ޽ࠆᔅⷐ߇޽ࠆޕߎߩ଀ߢߪޔ ᣹㒠⥽ߩ⥽ⷺǬ=0qߩ႐วߪㄫⷺ 0qߢߩߺቯᏱ㘧ⴕ ߇น⢻ߢ޽ࠆޕߎߎߢ⥽ⷺࠍᄌൻߐߖࠆߣ᳓ᐔየ⠢ߩ ឴ജ߇ᄌൻߒޔࡇ࠶࠴ࡦࠣࡕ࡯ࡔࡦ࠻ᦛ✢ߪ਄߹ߚߪ ਅߦᐔⴕ⒖േߔࠆޕߎࠇߦࠃߞߡ_C_M=0 ࠍḩߚߔㄫⷺ ߇ᄌࠊࠆޕߎߩࠃ߁ߦߒߡޔ᣹㒠⥽ߩᠲ૞ߦࠃߞߡޔ ቯᏱ㘧ⴕߢ߈ࠆㄫⷺߩ▸࿐ࠍᐢߍࠆߎߣ߇ߢ߈ࠆޕㄫ ⷺߪޔ⒳ޘߩ㘧ⴕㅦᐲߦ߅޿ߡቯᏱ㘧ⴕࠍታ⃻ߔࠆߚ ߼ߦ⸳ቯߐࠇࠆ߽ߩߢ޽ࠆ߆ࠄޔ᣹㒠⥽ߩᠲ૞ߦࠃߞ ߡޔቯᏱ㘧ⴕߢ߈ࠆ㘧ⴕㅦᐲߩ▸࿐ࠍᐢߍࠆߎߣ߇ߢ ߈ࠆޕ

Angle of Attack [deg.]

P it c h in g M o m en t C o e ff ic ie n t Ǭ=0[deg.] Ǭ=5[deg.] Ǭ=10[deg.] Ǭ=-5[deg.] Ǭ=-10[deg.]

Fig. 3. A typical curve of pitching moment coefficient vs. angle of attack. 㧟㘑ᵢ⹜㛎 M2006 㘑⹜ᮨဳߩ᳓ᐔየ⠢ߩขઃߌⷺࠍᄌ߃ߟ ߟޔ㘑⹜ߦࠃߞߡㄫⷺߣࡇ࠶࠴ࡦࠣࡕ࡯ࡔࡦ࠻ଥᢙߩ 㑐ଥࠍ⸘᷹ߔࠆޕ⹜㛎⸳஻ߣߒߡߪޔ㧔⁛㧕ቝቮ⥶ⓨ⎇ ⓥ㐿⊒ᯏ᭴ቝቮ⑼ቇ⎇ⓥᧄㇱ㧔JAXA/ISAS㧕ߩㆫ㖸ㅦ 㘑ᵢ߅ࠃ߮⿥㖸ㅦ㘑ᵢࠍ૶↪ߔࠆޕਔ㘑ᵢߪ็಴ߒᑼ ߢޔᵹ〝ᢿ㕙Ⓧߪ 600 mm600 mmޔᦨᄢㅢ㘑ᤨ㑆ߪ ⚂ 30 ⑽ޔㅢ㘑น⢻ࡑ࠶ࡂᢙߪߘࠇߙࠇ 0.3㨪1.3㧘1.5 㨪4.0 ߢ޽ࠆޕߘߩ᭎ⷰࠍ Fig. 4 ߦ␜ߔޕ ᮨဳߦ૞↪ߔࠆⓨ᳇ജߩ᷹ቯߦߪޔ౐ಽജౝⵝᄤ⒊ ࠍ↪޿ࠆߣߣ߽ߦޔ࿶ജᄌ឵ེߦࠃߞߡᐩ㕙࿶ജࠍ᷹ ቯߒߡᐩ㕙᛫ജ⵬ᱜࠍᣉߔޕㅢ㘑᧦ઙߪޔࡑ࠶ࡂᢙߪ 0.3㨪2.0ޔㄫⷺߪ੝㖸ㅦၞߢ-10q㨪10qޔ⿥㖸ㅦၞߢ -4q㨪4qޔᮮṖࠅⷺߪ-2q㨪2qߢ޽ࠆޕ᣹㒠⥽ߩ⥽ ⷺߪ೨✼਄ะ߈ࠍᱜߣߒߡ 0q㧘r5q㧘߅ࠃ߮r10q ߩ㧡ㅢࠅߢ޽ࠆޕ

(a) The transonic wind tunnel.

(b) The supersonic wind tunnel. Fig. 4. Wind tunnels of JAXA/ISAS.

㧠㧚⹜㛎⚿ᨐߣ⠨ኤ 㧠㧚㧝 ឴ജ߅ࠃ߮᛫ജ

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Ḵ┵ ৻⑲㧘⠀↰ ዏᄥ㧘Ꮏ⮮ ៺⡍㧘╣ጊ ኈ⾗㧘᪀↰ ⠹᣿㧘 ਣ ␭੺㧘Ḋ ੫ੑ㇢㧘᫜ᰴ ਗ਼ᒄ㧘ᣂ੗ 㓉᥊㧘ဝ੗ િᐘ ଥᢙߩࡑ࠶ࡂᢙଐሽᕈࠍޔ࿕ቯࡑ࠶ࡂᢙߩㅢ㘑ߣࡑ࠶ ࡂࠬࠗ࡯ࡊㅢ㘑ߩ⚿ᨐߦߟ޿ߡ Fig. 5(b) ߦ␜ߔޕ᛫ജ ଥᢙߪޔࡑ࠶ࡂ 1.13 ߢᦨᄢ୯ 0.081 ࠍ␜ߒߡ޿ࠆޕᦨ ᄢ୯ࠍߣߞߚᓟߪޔࡑ࠶ࡂᢙ߇Ⴧߔߦᓥߞߡ᛫ജଥᢙ ߪᷫࠅ⛯ߌޔࡑ࠶ࡂ 1.7 એ਄ߢߪࡑ࠶ࡂᢙ߇Ⴧടߒߡ ߽᛫ജଥᢙߪ߶ߣࠎߤᄌൻߒߥߊߥߞߡ޿ࠆޕ M2006 ᯏ૕ߩ឴ജ․ᕈࠍ Fig. 5(c) ߦޔ឴᛫Ყࠍ Fig. 5(d)ߦ␜ߔޕ੝㖸ㅦၞࠃࠅ߽⿥㖸ㅦၞߩ߶߁߇឴ജଥ ᢙ߇ᄢ߈޿ߎߣ߇ಽ߆ࠆޕ឴ജ௑ᢳ dCL/dǩߪㆫ㖸ㅦ ၞߦ߅޿ߡᄢ߈ߊߥߞߡ߅ࠅޔࡑ࠶ࡂ 1.1 ߢᦨᄢ୯ࠍ ขߞߡ޿ࠆޕ⿥㖸ㅦၞߢ᛫ജ߇ᄢ߈޿ߚ߼ޔ឴᛫Ყߪ ੝㖸ㅦၞࠃࠅ⿥㖸ㅦၞߩᣇ߇ዊߐߊߥࠆޕ M=0.3 M=0.7 M=0.9 M=1.1 M=1.3 M=1.5 M=1.7 M=1.9 M=2.0 C_D 0 deg. 1 deg. 2 deg. 3 deg. 4 deg. -1 deg. -2 deg. CL

(a) The drag polar curves.

fix,0deg. sweep.0deg. M=1.13,C_D=0.081 (sweep) CD Mach Number

(b) Mach number dependence of the drag coefficient.

M=0.3 M=0.7 M=0.9 M=1.1 M=1.3 M=1.5 M=1.7 M=1.9 M=2.0 ALPHA [deg.] CL

(c) The lift coefficient.

M=0.3 M=0.7 M=0.9 M=1.1 M=1.3 M=1.5 M=1.7 M=1.9 M=2.0 ALPHA [deg.] L/D

(d) The lift to drag ratio.

Fig. 5. Obtained aerodynamic data for the M2006 configuration. 㧠㧚㧞 ࡇ࠶࠴ࡦࠣߩ࠻࡝ࡓߣ㕒቟ቯᕈ Fig. 6 ߅ࠃ߮ Fig. 7 ߦޔࡑ࠶ࡂᢙ 0.3 ߅ࠃ߮ 0.7 ߩ႐ วߩ㊀ᔃ߹ࠊࠅߩࡇ࠶࠴ࡦࠣࡕ࡯ࡔࡦ࠻ᦛ✢ࠍ␜ߔޕ ㊀ᔃߪᐔဋⓨജ⠢ᒏߩ 30%૏⟎ߦ઒ቯߒߡ޿ࠆޕ⥽ⷺ Ǭ=0qߩ႐วߩᦛ✢ߩ௑߈ߪ⽶ߢ޽ࠅޔࡇ࠶࠴ࡦࠣߩ 㕒቟ቯߪ଻ߚࠇߡ޿ࠆߎߣ߇ࠊ߆ࠆޕࡑ࠶ࡂᢙ 0.3 ߩ ႐วޔฦ⥽ⷺߦߟ޿ߡߩᦛ✢ߪ⋧੕ߦᐔⴕߢ޽ࠆޕ⥽ ⷺ▸࿐ࠍr5qߣߔࠆߣቯᏱ㘧ⴕน⢻ߥㄫⷺ▸࿐ߪ -6q㨪8qߢ޽ࠆޕ߹ߚ⥽ⷺ▸࿐ࠍr10qߣߔࠆߣޔᦛ ✢ࠍ⵬ᄖߔࠆߎߣߦࠃࠅቯᏱ㘧ⴕน⢻ߥㄫⷺ▸࿐ߪ -13q㨪15qߣ੍᷹ߐࠇࠆޕࡑ࠶ࡂᢙ 0.7 ߩ႐วߪޔ⥽

(6)

ⷺ▸࿐ࠍr5qߣߔࠆߣޔᦛ✢ࠍ⵬ᄖߔࠆߎߣߦࠃࠅ ቯᏱ㘧ⴕน⢻ߥㄫⷺ▸࿐ߪ-6q㨪6qߣ੍᷹ߐࠇࠆޕߒ ߆ߒޔ⥽ⷺ-10q߅ࠃ߮ 10qߢߪᦛ✢ߩ௑߈߇㕖Ᏹߦ ዊߐߊޔ቟ቯਛ┙ߦㄭ޿⁁ᘒߢ޽ࠆޕࡑ࠶ࡂᢙ 0.7 એ ਄ߩㆫ㖸ㅦၞߦ߅޿ߡห᭽ߩ௑ะ߇⷗ࠄࠇࠆޕ

Pi tc hi ng M om ent C oe ff ic ient delta = -10[deg.] delta = -5[deg.] delta = 0 [deg.] delta = 5 [deg.] delta = 10[deg.] M2006 Mach0.3, C_M(MAC30%)

Fig. 6. The pitching moment coefficient vs. the angle of attack at Mach 0.3.

P it ch ing M o m en t C o ef fi ci en t delta = -10[deg.] delta = -5[deg.] delta = 0 [deg.] delta = 5 [deg.] delta = 10[deg.] M2006 Mach0.7, C_M(MAC30%)

Fig. 7. The pitching moment coefficient vs. the angle of attack at Mach 0.7. 㧠㧚㧟 ᣹㒠⥽ᠲ⥽ߦࠃࠆ឴ജଥᢙߩᄌൻ Fig. 8 ߅ࠃ߮ Fig. 9 ߦࡑ࠶ࡂᢙ 0.3 ߅ࠃ߮ 0.7 ߩ᣹㒠 ⥽ᠲ⥽ߦࠃࠆ឴ജଥᢙ_C_Lߩᄌൻߩ᭽ሶࠍ␜ߔޕࡑ࠶ࡂ ᢙ 0.3 ߢߪޔߔߴߡߩㄫⷺߦ߅޿ߡޔ⥽ⷺߦኻߒߡ⋥ ✢⊛ߦ឴ജଥᢙ߇ᄌൻߒߡ޿ࠆޕࡑ࠶ࡂᢙ 0.7 ߢߪ⥽ ⷺߦኻߔࠆ឴ജଥᢙߩᄌൻ߇⋥✢⊛ߢߥߊޔ⥽ⷺ▸࿐ -10q㨪-5q߅ࠃ߮ 5q㨪10qߢ឴ജଥᢙߩᄌൻ߇㊰ߞ ߡ޿ࠆޕߎࠇߪޔᄢ߈ߥ⥽ⷺߦࠃߞߡ᳓ᐔየ⠢߇ᄬㅦ ߒߡ޿ࠆߚ߼ߣ⠨߃ࠄࠇࠆޕ 㧠㧚㧠㔌⌕㒽ᕈ⢻ߩ੍᷹ 㔌㒽ㅦᐲࠍࡑ࠶ࡂᢙ0.3߅ࠃ߮0.5ߣ઒ቯߒߚ႐วߩ 㔌㒽ᤨߩ឴ജࠍ Fig. 10 ߦ␜ߔޕᮮゲߪㄫⷺ[deg.]㧘❑ ゲߪ឴ജ[kgf]ߢ޽ࠆޕM2006 ᯏ૕ߩో஻㊀㊂ߪ 155 kgf ߣផ▚ߐࠇߡ߅ࠅޔߎࠇࠍ࿑ਛߦ⿒✢ߢ␜ߔޕ㔌⌕㒽 ࡑ࠶ࡂᢙࠍ 0.3㧔㘧ⴕㅦᐲ 102 m/sec㧕ߣߔࠆ႐วߪㄫ ⷺ 5q⒟ᐲ㧔᳓ᐔየ⠢⥽ⷺ-3q⒟ᐲ㧕ߢ឴ജ߇㊀㊂ࠍ ਄࿁ߞߡ㔌⌕㒽น⢻ߢ޽ࠆޕߎߩ୯߆ࠄ឵▚ߔࠆߣޔ ㄫⷺࠍ 8q㧔᳓ᐔየ⠢⥽ⷺ-5q㧕ߣߔࠆߥࠄ߫ޔ㘧ⴕ ࡑ࠶ࡂᢙ 0.24㧔㘧ⴕㅦᐲ 82 m/sec㧕⒟ᐲߢ㔌⌕㒽น⢻ ߢ޽ࠆޕߥ߅ޔㆫ㖸ㅦ㨪⿥㖸ㅦၞߦߟ޿ߡߪޔ2q⒟ ᐲએਅߩዊߐߥㄫⷺߢ㘧ⴕߔࠆߣ޿߁੐߽⋧଼ߞߡޔ ࡇ࠶࠴ࡦࠣ࠻࡝ࡓᕈ⢻ߪචಽߢ޽ࠆߎߣ߇ಽ߆ߞߡ޿ ࠆޕ 㧡㧚⚿⸒ ᄢ㒽㑆ߩ㜞ㅦ⥶ⓨャㅍ߅ࠃ߮࿾⃿゠㆏߳ߩౣ૶↪ቝ ቮャㅍࠍ㕟ᣂߔࠆߚ߼ߩၮ⋚ᛛⴚࠍ㘧ⴕታ⸽ߔࠆߎߣ ࠍ⋡ᮡߣߒߡޔࡈ࡜ࠗࡦࠣ࠹ࠬ࠻ࡌ࠶࠼ߣߒߡߩዊဳ ⿥㖸ㅦ㘧ⴕታ㛎ᯏߩ㐿⊒⎇ⓥࠍㅴ߼ߡ޿ࠆޕ⿥㖸ㅦၞ ߹ߢߩടㅦᕈߩᦼᓙߢ߈ࠆ෺⊒࡮㜞⠢ᒻ⁁ࠍᒰ㕙ߩࡌ ࡯ࠬ࡜ࠗࡦᒻ⁁ߣߒߡㆬቯߒߚޕࡑ࠶ࡂᢙ 0.3㨪2.0 ߩ ▸࿐ߢ㘑ᵢ⹜㛎ࠍታᣉߒޔ឴ജޔ᛫ജޔ߅ࠃ߮ࡇ࠶࠴ ࡦࠣࡕ࡯ࡔࡦ࠻ࠍ⸘᷹ߒߚޕߘߩ⚿ᨐޔM2006 ᒻ⁁ߩ 㘧ⴕታ㛎ᯏߪޔ㔌⌕㒽߆ࠄ⿥㖸ㅦᎼ⥶߹ߢߩోㅦᐲ㗔 ၞߦ߅ߌࠆࡇ࠶࠴ࡦࠣ࠻࡝ࡓᕈ⢻߅ࠃ߮⦟ᅢߥ㔌⌕㒽 ᕈ⢻ࠍ᦭ߔࠆߎߣ߇੍᷹ߐࠇߚޕ ߥ߅ޔ੝㖸ㅦၞߦᲧߴߡㆫ㖸ㅦ࡮⿥㖸ㅦၞߢߪޔࡇ ࠶࠴ࡦࠣ㕒቟ቯᕈ߇⧯ᐓૐᷫߔࠆߎߣߣޔ᳓ᐔየ⠢߇ ᄬㅦߔࠆ௑ะ߇ᝒ߃ࠄࠇߚޕ೨⠪ߦߟ޿ߡߪ㊀ᔃ૏⟎ ࠍ߽ߞߣ೨ᣇߦ⸳ቯߔࠆߎߣ߇ലᨐ⊛ߢ޽ࠅޔᓟ⠪ߦ ߟ޿ߡߪ᳓ᐔየ⠢ߩᓟㅌⷺࠍዊߐߊߒߚࠅޔࡏ࡞࠹࠶ ࠢࠬࠫࠚࡀ࡟࡯࠲ޔ࠼࠶ࠣ࠷࡯ࠬޔ╬ߩᄬㅦᛥ೙╷ࠍ ⻠ߓࠆߎߣ߇ലᨐ⊛ߣ⠨߃ࠄࠇࠆޕ ߎߩࠃ߁ߥታ㓙ߩ⥶ⓨᯏߩోᯏⓨജ․ᕈߦ㑐ߔࠆ⎇ ⓥ߇⚥Ⓧߐࠇޔ⿥㖸ㅦ⥶ⓨᯏߩ⸳⸘ߦ⾗ߔࠆ⍮⷗߇⫾ Ⓧߐࠇࠆߎߣߦࠃߞߡޔᄢ㒽㑆ߩ㜞ㅦ⥶ⓨャㅍ߅ࠃ߮ ࿾⃿゠㆏߳ߩౣ૶↪ቝቮャㅍߦ㑐ߔࠆᚒ߇࿖ߩᛛⴚ⊛ ࿾૏߇⏕┙ߔࠆߎߣ߇ᦼᓙߐࠇࠆޕ

(7)

Ḵ┵ ৻⑲㧘⠀↰ ዏᄥ㧘Ꮏ⮮ ៺⡍㧘╣ጊ ኈ⾗㧘᪀↰ ⠹᣿㧘 ਣ ␭੺㧘Ḋ ੫ੑ㇢㧘᫜ᰴ ਗ਼ᒄ㧘ᣂ੗ 㓉᥊㧘ဝ੗ િᐘ ᢥ₂ 㧔㧝㧕Ḵ┵ ৻⑲㧘᫜ᰴ ਗ਼ᒄ㧘᧲㊁ ๺ᐘ㧘Ḋ ੫ੑ㇢㧘 ਣ ␭੺㧘ᣂ੗ 㓉᥊㧘ޟFTB ߣߒߡߩዊဳ⿥㖸ㅦ㘧 ⴕታ㛎ᯏߩ᭴ᗐߣ੝㖸ㅦ㘧ⴕታ⸽ޠ㧘ᐔᚑ 19 ᐕᐲቝ ቮャㅍࠪࡦࡐࠫ࠙ࡓ㧘⋧ᮨේ㧔2008ᐕ1᦬28-29ᣣ㧕㧚㧔㧞㧕USAF Stability and Control DATCOM, McDonnell Douglas Corporation and Air Force Flight Dynamics Laboratory, 1978. 㧔㧟㧕⠀↰ ዏᄥ㧘᫜ᰴ ਗ਼ᒄ㧘Ḵ┵ ৻⑲㧘Ḋ ੫ੑ㇢㧘 ᧁ᧛ ඳᐘ㧘Ꮏ⮮ ៺⡍㧘㤗↢ ⨃㧘⼱ ᵏኡ㧘ᣂ੗ 㓉 ᥊㧘ޟዊဳ⿥㖸ㅦ㘧ⴕታ㛎ߩߚ߼ߩ᦭⠢ᯏ૕ߩⓨജ⸳ ⸘ߣ㘑⹜⚿ᨐޠ㧘ᐔᚑ 18 ᐕᐲቝቮャㅍࠪࡦࡐࠫ࠙ࡓ㧘 ⋧ᮨේ㧔2007 ᐕ 1 ᦬ 18-19 ᣣ㧕㧚㧔㧠㧕Ꮏ⮮ ៺⡍㧘᫜ᰴ ਗ਼ᒄ㧘Ḵ┵ ৻⑲㧘ਣ ␭੺㧘 ╣ጊ ኈ⾗㧘᪀↰ ⠹᣿㧘ᣂ੗ 㓉᥊㧘ᬮ੉ ᜏ਽㧘ਭ ଻ ⦟੺㧘ဝ੗ િᐘ㧘ޟዊဳ⿥㖸ㅦ㘧ⴕታ㛎ᯏߩⓨജ ⸳⸘ߣⓨജᕈ⢻⹏ଔޠ㧘ᐔᚑ 19 ᐕᐲቝቮャㅍࠪࡦࡐ ࠫ࠙ࡓ㧘⋧ᮨේ㧔2008 ᐕ 1 ᦬ 28-29 ᣣ㧕㧚 L if t C o ef fi ci en t Elevator angle[deg.] ǩ= -4[deg.] ǩ= -2[deg.] ǩ= 0[deg.] ǩ= 2[deg.] ǩ= 4[deg.] M2006 C_L , M = 0.3

Fig. 8. The lift coefficient vs. the elevator angle at Mach 0.3.

L if t C o ef fi ci en t Elevator angle[deg.] ǩ= -4[deg.] ǩ= -2[deg.] ǩ= 0[deg.] ǩ= 2[deg.] ǩ= 4[deg.] M2006 C_L , M = 0.7

Fig. 9. The lift coefficient vs. the elevator angle at Mach 0.7.

L if t [k g f] M = 0.3 M = 0.5 M = 0.3 (d = -10[deg.]) M = 0.3 (d = -5[deg.]) M = 0.5 (d = -5[deg.]) Weight = 155 [kgf]

Fig. 10. The predicted lift of the experimental vehicle of the M2006 configuration.