タイトル（掲載誌）Technical Report of National Aerospace Laboratory TR-1088T
一般注記新形態航空機の一つである結合翼機の空力特性および従来型形態航空機と比較した場合の実用上の空力的メリットを,理論計算とCFD数値計算,並びに低速風洞試験で調べた。先ず拡張揚力線理論と3次元ポテンシャル流れパネル法を用いて,結合翼の各種形態について幾何学的諸元の効果,即ち立体型と平面型結合翼の空力特性の差異,前後翼のスパン比,スイープ角,面積比がそれぞれ空力特性に与える効果,およびその選定範囲を検討した。次に結合翼の前方翼に後退翼特有の翼端捩り下げをつけ,後方翼には前進翼特有の翼端振り上げと平均的捩り上げをつけた一設計形態に3次元オイラー方程式の差分計算法を適用して,亜音速,遷音速領域の揚力特性と抗力特性を調べた。低速風洞試験では,結合翼-垂直尾翼-胴体の全機形態模型を用い,広範な迎角範囲について六分力計測と流れの可視化試験を実施して,揚力特性,抗力特性,失速特性,上反角特性,方向安定性,等に関するデータを取得した。理論計算と風洞試験の両面からの検討の結果,結合翼機形態は設計上の幾何形状パラメータの選定範囲が広く,設計の自由度が大きい等のメリットがあると同時に,上反角特性や方向安定性に関連する垂直尾翼の位置,大きさの選定の設計課題があるなどの知見を得た。
Aerodynamic characteristics of a Joined-wing have been investigated by computational methods and by a low-speed wind-tunnel experiment for the purpose of understanding to aerodynamics characteristics and advantages of such a wing over conventional configurations, and to examine the feasibility of using it in a practical application. The first analysis by the extended-lifting-line-theory and the second analysis by the 3D potential-flow-panel method were done to clarify the effects of geometrical parameters on the Joined-wing aerodynamics, such as solid/planar types, span ratio, angles of sweep and area ratio of the front and rear wings. The result showed that there is a wide range of possibilities for selecting the geometrical design parameters of a Joined-wing. The third analysis by finite difference computation of 3D-Euler equation was applied to obtain the lift and drag characteristics, especially their divergence of the Joined-wing, in the high subsonic to transonic regime. The swept-back front wing was designed to have a wash-out twist distribution and the forward-swept rear wing to have a wash-in distribution and positive incidence on average against the downwash induced by the front wing. A low-speed wind-tunnel test of 6-component force measurement and flow visualization of the Joined-wing over a wide range of angles of attack up to post-stall gave lift values which agree well with the computational prediction by the Panel method for an angle of attack of up to 8deg. The test showed that he stall characteristics are mild and that the dependence of the lift and drag forces on the side-slip angle is small. Dihedral effect of the front wing and unhedral effect of the rear wing proved to almost cancel each other to make the resultant C1β very small. Further examinations on effects of the dihedral and unhedral angles and on the location and tail volume of the vertical tail are needed.
資料番号: NALTR1088000
レポート番号: NAL TR-1088T
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45347&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ