Abstract
The Quiet Short Take-Off and Landing (QSTOL) Experimental Aircraft `ASKA` has been researched and developed by the National Aerospace Laboratory (NAL). The `ASKA` was based upon the airframe of the home produced C-1 tactical transport which was modified into the Upper Surface Blowing (USB) -powered high- lift STOL aircraft. The wing configuration, however, was not changed. Therefore, this Experimental Aircraft does not always have the optimum configuration of a USB-type aircraft. So the authors tried to improve the aerodynamic characteristics of the STOL Aircraft. This paper describes the investigations which have been conducted to improve the aerodynamic characteristics of a subsonic jet transport semi-span model with an Upper Surface Blown Flap system which has been newly designed using the NAL STOL-CAD program. The model had an 8.2{degree} swept wing of aspect ratio 10.0 and four turbofan engines with short USB nozzles. The tests were conducted in the NAL 2{times}2m Gust Wind Tunnel with closed section and results were obtained for several flap and slat deflections at jet momentum coefficients from 0 to 1.85. Compared with the aerodynamic characteristics of the `ASKA` model, we determined that the airframe weight can be reduced and the aerodynamic characteristics can be improved significantly. 14
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Takahashi, H;
Okuyama, M;
Fujieda, H;
Fujita, T;
Iwasaki, A
[1]
- National Aerospace Laboratory, Tokyo (Japan)
Citation Formats
Takahashi, H, Okuyama, M, Fujieda, H, Fujita, T, and Iwasaki, A.
Wind tunnel investigation of a USB-STOL transport semi-span model. 2; CAD sekkei ni yoru USB-STOL ki hansai mokei no fudo shiken. 2.
Japan: N. p.,
1994.
Web.
Takahashi, H, Okuyama, M, Fujieda, H, Fujita, T, & Iwasaki, A.
Wind tunnel investigation of a USB-STOL transport semi-span model. 2; CAD sekkei ni yoru USB-STOL ki hansai mokei no fudo shiken. 2.
Japan.
Takahashi, H, Okuyama, M, Fujieda, H, Fujita, T, and Iwasaki, A.
1994.
"Wind tunnel investigation of a USB-STOL transport semi-span model. 2; CAD sekkei ni yoru USB-STOL ki hansai mokei no fudo shiken. 2."
Japan.
@misc{etde_155005,
title = {Wind tunnel investigation of a USB-STOL transport semi-span model. 2; CAD sekkei ni yoru USB-STOL ki hansai mokei no fudo shiken. 2}
author = {Takahashi, H, Okuyama, M, Fujieda, H, Fujita, T, and Iwasaki, A}
abstractNote = {The Quiet Short Take-Off and Landing (QSTOL) Experimental Aircraft `ASKA` has been researched and developed by the National Aerospace Laboratory (NAL). The `ASKA` was based upon the airframe of the home produced C-1 tactical transport which was modified into the Upper Surface Blowing (USB) -powered high- lift STOL aircraft. The wing configuration, however, was not changed. Therefore, this Experimental Aircraft does not always have the optimum configuration of a USB-type aircraft. So the authors tried to improve the aerodynamic characteristics of the STOL Aircraft. This paper describes the investigations which have been conducted to improve the aerodynamic characteristics of a subsonic jet transport semi-span model with an Upper Surface Blown Flap system which has been newly designed using the NAL STOL-CAD program. The model had an 8.2{degree} swept wing of aspect ratio 10.0 and four turbofan engines with short USB nozzles. The tests were conducted in the NAL 2{times}2m Gust Wind Tunnel with closed section and results were obtained for several flap and slat deflections at jet momentum coefficients from 0 to 1.85. Compared with the aerodynamic characteristics of the `ASKA` model, we determined that the airframe weight can be reduced and the aerodynamic characteristics can be improved significantly. 14 refs., 44 figs.}
place = {Japan}
year = {1994}
month = {Nov}
}
title = {Wind tunnel investigation of a USB-STOL transport semi-span model. 2; CAD sekkei ni yoru USB-STOL ki hansai mokei no fudo shiken. 2}
author = {Takahashi, H, Okuyama, M, Fujieda, H, Fujita, T, and Iwasaki, A}
abstractNote = {The Quiet Short Take-Off and Landing (QSTOL) Experimental Aircraft `ASKA` has been researched and developed by the National Aerospace Laboratory (NAL). The `ASKA` was based upon the airframe of the home produced C-1 tactical transport which was modified into the Upper Surface Blowing (USB) -powered high- lift STOL aircraft. The wing configuration, however, was not changed. Therefore, this Experimental Aircraft does not always have the optimum configuration of a USB-type aircraft. So the authors tried to improve the aerodynamic characteristics of the STOL Aircraft. This paper describes the investigations which have been conducted to improve the aerodynamic characteristics of a subsonic jet transport semi-span model with an Upper Surface Blown Flap system which has been newly designed using the NAL STOL-CAD program. The model had an 8.2{degree} swept wing of aspect ratio 10.0 and four turbofan engines with short USB nozzles. The tests were conducted in the NAL 2{times}2m Gust Wind Tunnel with closed section and results were obtained for several flap and slat deflections at jet momentum coefficients from 0 to 1.85. Compared with the aerodynamic characteristics of the `ASKA` model, we determined that the airframe weight can be reduced and the aerodynamic characteristics can be improved significantly. 14 refs., 44 figs.}
place = {Japan}
year = {1994}
month = {Nov}
}