@techreport{oai:jaxa.repo.nii.ac.jp:00044654,
 author = {森, 幹彦 and 真柳, 光美 and 名越, 孝行 and 後藤, 芳夫 and 照井, 祐之 and MORI, Mikihiko and MAYANAGI, Mitsuyoshi and NAGOSHI, Takayuki and GOTO, Yoshio and TERUI, Yushi},
 month = {Feb},
 note = {The longitudinal stability and control derivatives of the Beechcraft Queen Air-Model 65-were determined from the flight data for landing and cruising flight configurations. The result will be used for designing an automatic landing system for the airplane. To analyze the flight data, the least square method of conventional derivative type was adopted, which brought the raw estimate of derivatives with considerable variations depending upon the sampling intervals. The final value of each derivatives was determined by a simulated computation and was compared with the wind tunnel test data. The accuracy of the derivatives is estimated to be of about 50 percent error for stability derivatives and less than 30 percent for control derivatives. Of noticed is a large discrepancy which exists in the two values of Mα derived from the flight test and the wind tunnel test. Since Mα is one of the most important derivatives, a detailed simulation was made to confirm the appropriateness of the flight test result, and it was concluded that the discrepancy is apparent because the reference points of the pitching moment were different for the flight test and the wind tunnel test. Also regarding the role of Mα in the motion of an airplane, the generally used two degree of freedom approximation to a long period motion was examined, and another expressions for ωnph and ζph were obtained. These expressions are suitably applicable to approximate the long period dynamics of an airplane with small |Mα|., 資料番号: NALTR0406000, レポート番号: NAL TR-406},
 title = {クインエア機の縦の安定操縦微係数の推定},
 year = {1975}
}