Abstract
Investigations were made on performance of scram jet nozzles under a Mach 8 flight condition, using high temperature gas made from burning monomethyl-hydrazine and nitrogen tetraoxide. The test items included nozzle thrust, nozzle wall pressure distribution, pitot pressure, and static pressure distribution. A nozzle visualization experiment was also carried out. The analytic method used was the one JANNAF has applied for rocket nozzles. The following findings were obtained: This nozzle has a small thrust increment, but it corresponds to 1100 seconds as converted to a flow rate; nozzle flow fields were calculated using non-viscosity two-dimensional codes to verify the accuracy by comparing the results with experimental values; energy efficiency, non-equilibrium loss, and two-dimensional loss were identified from these calculations; core flow performance using these codes can be predicted with an accuracy of 4% or higher; the boundary layer in the case of using this combustion gas suggested a possibility of a laminar flow; and effect of radical activity loss reaction on the performance was investigated, by which the reaction mechanisms of nozzle flows were clarified. 73 refs., 40 figs., 5 tabs.
Miyajima, H;
Mitani, T;
Sato, S;
Ueda, S;
Tani, K;
Hiraiwa, T;
Ito, K;
Kusaka, K;
Izumikawa, M;
Kisara, K;
Kumagai, T;
Saito, T;
Sakuranaka, N;
Takahashi, M;
[1]
Tanaka, A;
Yasu, S;
Higashino, K;
Sayama, M;
Yamamoto, M;
Matsumoto, M;
Sawaguchi, S;
Utagawa, Y;
Tokunaga, K
[2]
- National Aerospace Laboratory, Tokyo (Japan)
- Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo (Japan)
Citation Formats
Miyajima, H, Mitani, T, Sato, S, Ueda, S, Tani, K, Hiraiwa, T, Ito, K, Kusaka, K, Izumikawa, M, Kisara, K, Kumagai, T, Saito, T, Sakuranaka, N, Takahashi, M, Tanaka, A, Yasu, S, Higashino, K, Sayama, M, Yamamoto, M, Matsumoto, M, Sawaguchi, S, Utagawa, Y, and Tokunaga, K.
Studies on scramjet nozzles. 1. Performance of two dimensional nozzles; Scramjet nozzle no kenkyu. 1. Nijigen nozzle no seino.
Japan: N. p.,
1992.
Web.
Miyajima, H, Mitani, T, Sato, S, Ueda, S, Tani, K, Hiraiwa, T, Ito, K, Kusaka, K, Izumikawa, M, Kisara, K, Kumagai, T, Saito, T, Sakuranaka, N, Takahashi, M, Tanaka, A, Yasu, S, Higashino, K, Sayama, M, Yamamoto, M, Matsumoto, M, Sawaguchi, S, Utagawa, Y, & Tokunaga, K.
Studies on scramjet nozzles. 1. Performance of two dimensional nozzles; Scramjet nozzle no kenkyu. 1. Nijigen nozzle no seino.
Japan.
Miyajima, H, Mitani, T, Sato, S, Ueda, S, Tani, K, Hiraiwa, T, Ito, K, Kusaka, K, Izumikawa, M, Kisara, K, Kumagai, T, Saito, T, Sakuranaka, N, Takahashi, M, Tanaka, A, Yasu, S, Higashino, K, Sayama, M, Yamamoto, M, Matsumoto, M, Sawaguchi, S, Utagawa, Y, and Tokunaga, K.
1992.
"Studies on scramjet nozzles. 1. Performance of two dimensional nozzles; Scramjet nozzle no kenkyu. 1. Nijigen nozzle no seino."
Japan.
@misc{etde_10156065,
title = {Studies on scramjet nozzles. 1. Performance of two dimensional nozzles; Scramjet nozzle no kenkyu. 1. Nijigen nozzle no seino}
author = {Miyajima, H, Mitani, T, Sato, S, Ueda, S, Tani, K, Hiraiwa, T, Ito, K, Kusaka, K, Izumikawa, M, Kisara, K, Kumagai, T, Saito, T, Sakuranaka, N, Takahashi, M, Tanaka, A, Yasu, S, Higashino, K, Sayama, M, Yamamoto, M, Matsumoto, M, Sawaguchi, S, Utagawa, Y, and Tokunaga, K}
abstractNote = {Investigations were made on performance of scram jet nozzles under a Mach 8 flight condition, using high temperature gas made from burning monomethyl-hydrazine and nitrogen tetraoxide. The test items included nozzle thrust, nozzle wall pressure distribution, pitot pressure, and static pressure distribution. A nozzle visualization experiment was also carried out. The analytic method used was the one JANNAF has applied for rocket nozzles. The following findings were obtained: This nozzle has a small thrust increment, but it corresponds to 1100 seconds as converted to a flow rate; nozzle flow fields were calculated using non-viscosity two-dimensional codes to verify the accuracy by comparing the results with experimental values; energy efficiency, non-equilibrium loss, and two-dimensional loss were identified from these calculations; core flow performance using these codes can be predicted with an accuracy of 4% or higher; the boundary layer in the case of using this combustion gas suggested a possibility of a laminar flow; and effect of radical activity loss reaction on the performance was investigated, by which the reaction mechanisms of nozzle flows were clarified. 73 refs., 40 figs., 5 tabs.}
place = {Japan}
year = {1992}
month = {Apr}
}
title = {Studies on scramjet nozzles. 1. Performance of two dimensional nozzles; Scramjet nozzle no kenkyu. 1. Nijigen nozzle no seino}
author = {Miyajima, H, Mitani, T, Sato, S, Ueda, S, Tani, K, Hiraiwa, T, Ito, K, Kusaka, K, Izumikawa, M, Kisara, K, Kumagai, T, Saito, T, Sakuranaka, N, Takahashi, M, Tanaka, A, Yasu, S, Higashino, K, Sayama, M, Yamamoto, M, Matsumoto, M, Sawaguchi, S, Utagawa, Y, and Tokunaga, K}
abstractNote = {Investigations were made on performance of scram jet nozzles under a Mach 8 flight condition, using high temperature gas made from burning monomethyl-hydrazine and nitrogen tetraoxide. The test items included nozzle thrust, nozzle wall pressure distribution, pitot pressure, and static pressure distribution. A nozzle visualization experiment was also carried out. The analytic method used was the one JANNAF has applied for rocket nozzles. The following findings were obtained: This nozzle has a small thrust increment, but it corresponds to 1100 seconds as converted to a flow rate; nozzle flow fields were calculated using non-viscosity two-dimensional codes to verify the accuracy by comparing the results with experimental values; energy efficiency, non-equilibrium loss, and two-dimensional loss were identified from these calculations; core flow performance using these codes can be predicted with an accuracy of 4% or higher; the boundary layer in the case of using this combustion gas suggested a possibility of a laminar flow; and effect of radical activity loss reaction on the performance was investigated, by which the reaction mechanisms of nozzle flows were clarified. 73 refs., 40 figs., 5 tabs.}
place = {Japan}
year = {1992}
month = {Apr}
}