HB-2 high-velocity correlation model at high angles of attack in supersonic wind tunnel tests
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摘要
Responding to a need for experimental data on a standard wind tunnel model at high angles of attack in the supersonic speed range, and in the absence of suitable reference data, a series of tests of two HB-2 standard models of different sizes was performed in the T-38 trisonic wind tunnel of Vojnotehnickˇi Institut(VTI), in the Mach number range 1.5–4.0, at angles of attack up to+30°. Tests were performed at relatively high Reynolds numbers of 2.2 millions to 4.5 millions(based on model forebody diameter). Results were compared with available low angle of attack data from other facilities, and, as a good agreement was found, it was assumed that, by implication, the obtained high angle of attack results were valid as well. Therefore, the results can be used as a reference database for the HB-2 model at high angles of attack in the supersonic speed range, which was not available before. The results are presented in comparison with available reference data, but also contain data for some Mach numbers not given in other publications.
Responding to a need for experimental data on a standard wind tunnel model at high angles of attack in the supersonic speed range, and in the absence of suitable reference data, a series of tests of two HB-2 standard models of different sizes was performed in the T-38 trisonic wind tunnel of Vojnotehnickˇi Institut(VTI), in the Mach number range 1.5–4.0, at angles of attack up to+30°. Tests were performed at relatively high Reynolds numbers of 2.2 millions to 4.5 millions(based on model forebody diameter). Results were compared with available low angle of attack data from other facilities, and, as a good agreement was found, it was assumed that, by implication, the obtained high angle of attack results were valid as well. Therefore, the results can be used as a reference database for the HB-2 model at high angles of attack in the supersonic speed range, which was not available before. The results are presented in comparison with available reference data, but also contain data for some Mach numbers not given in other publications.
Responding to a need for experimental data on a standard wind tunnel model at high angles of attack in the supersonic speed range, and in the absence of suitable reference data, a series of tests of two HB-2 standard models of different sizes was performed in the T-38 trisonic wind tunnel of Vojnotehnickˇi Institut(VTI), in the Mach number range 1.5–4.0, at angles of attack up to+30°. Tests were performed at relatively high Reynolds numbers of 2.2 millions to 4.5 millions(based on model forebody diameter). Results were compared with available low angle of attack data from other facilities, and, as a good agreement was found, it was assumed that, by implication, the obtained high angle of attack results were valid as well. Therefore, the results can be used as a reference database for the HB-2 model at high angles of attack in the supersonic speed range, which was not available before. The results are presented in comparison with available reference data, but also contain data for some Mach numbers not given in other publications.
引文
1.Bordano A,LeBeau G,Bryant L,Tigges M,Campbell H,Horvath T,et al.Aerodynamics and flight dynamics.In:Hale W,editor.Wings in orbit-Scientific and engineering legacies of the Space Shuttle.Washington,D.C.:NASA;2010.p.226-41.
2.Stengel RF.Strategies for control of the space shuttle transition.Journal of Spacecraft and Rockets 1973;10(1):73-84.
3.Dahlem V,Flehaerty JI,Shereda DE,Prziembel CEG.High angle of attack missile aerodynamics at Mach numbers 0.3 to 1.5.Flight Dynamics Laboratory,Wright Patterson Air Force Base;1980.Report No.:AFWAL-TR-80-3070.
4.Oberkampf WL,Nicolaides JD.Aerodynamics of finned missiles at high angles of attack.AIAA J 1971;9(12):2378-84.
5.Hadidoolabi M,Ansiaran H.Supersonic flow over a pitching delta wing using surface pressure measurements and numerical simulations.Chin J Aeronaut 2018;31(1):65-78.
6.Votta R.Advanced models for prediction of high altitude aerothermal loads of a space re-entry vehicle[dissertation].Potenza:Universita degli Studi della Basilicata;2008.
7.Cummings RM,Forsythe JR,Morton SA,Squires KD.Computational challenges in high angle of attack flow prediction.Prog Aerosp Sci 2003;39(5):369-83.
8.Mehta R.Computations of flowfield over reentry modules at high speed.Comput Simul Appl 2011.
9.Bai CY,Wu ZN.Hypersonic starting flow at high angle of attack.Chin J Aeronaut 2016;29(2):297-304.
10.Elfstrom GM,Medved B.The Yugoslav 1.5 m trisonic blowdown wind tunnel.Proceedings of the 14th AIAA aerodynamic testing conference.Reston:AIAA;1986.
11.Damljanovic′D,Isakovic′J,Rasˇuo B.T-38 Wind tunnel data quality assurance based on testing of a standard model.J Aircraft2013;50(4):1141-9.
12.Vukovic′Dj,C′urcˇic′D,Marinkovski D,Damljanovic′D,Samardzˇic′M,Vitic′A.Living with supersonic starting loads in the T-38 trisonic wind tunnel of VTI.Proceedings of the 29th congress of the international council of the aeronautical sciences(ICAS).2014.
13.Gray JD.Summary report on aerodynamic characteristics of standard models HB-1 and HB-2.Arnold Engineering Development Center;1964.Report No.:AEDC-TDR-64-137.
14.Gray JD,Lindsay EE.Force tests of standard hypervelocity ballistic models HB-1 and HB-2 at Mach 1.5 to 10.Arnold Engineering Development Center;1963.Report No.:AEDC-TDR-63-137.
15.Ceresuela R.Mesure′s d‘efforts et de pressions sur la maquette balistique etalon HB-2 de Mach 2 a Mach 16,5.ONERA;1964.Report No.:Note Technique 13/1879 A.
16.Malcolm GN.Chapman GT.A computer program for systematically analyzing free-flight data to determine the aerodynamics of axisymmetric bodies.Washington,D.C.:NASA Ames Research Center;1968.Report No.:NASA TN D-4766.
17.Opalka KO.Force tests of the hypersonic ballistic standard models HB-1 and HB-2.Ballistic Research Labs,Aberdeen Proving Ground;1966.Report No.:BLR-MR-1798.
18.Wesstroem P.Lundgren S.Three-component force measurements of a heat insulated AGARD Hb-2 model at M equals 4 and Mequals 7 using an uncooled balance.Stockholm:FFA;1974.Report No.:FFA-TN-AX-805.
19.Dj Vukovic′,Damljanovic′D.Evaluation of a force balance with semiconductor strain gauges in wind tunnel tests of the HB-2standard model.Proc Inst Mech Eng Part G:J Aerospace Eng2015;229(12):2272-81.
20.Kumar RS,Das S,Kumar P,Prasad JK.Investigation of flow field around a typical reentry capsule at supersonic speeds.Proceedings of the XXVI national convention of aerospace engineers.2012.
21.Damljanovic′D,Rasˇuo B,Vukovic′DJ,Mandic′S,Isakovic′J.Hypervelocity ballistic reference models as experimental supersonic test cases.Aerosp Sci Technol 2016;52:189-97.
22.Recommended practice:Calibration and use of internal straingage balances with application to wind tunnel testing.Reston:AIAA;2003.Report No.:AIAA-0091-2003.
23.Compton WB.Effect on base drag of recessing the bases of conical afterbodies at subsonic and transonic speeds.Washington,D.C.:NACA Langley Research Center;1958.Report No.:NASA TN-D4821.
24.Wiswanath PR,Patil SR.Effectiveness of passive devices for axisymmetric base drag reduction at Mach 2.J Spacecraft 1990;27(3):234-7.
25.Adamov NP,Vasenev LG,Zvegintsev VI,Mazhul II,Nalivaichenko DG,Novikov AV,et al.Characteristics of the AT-303hypersonic wind tunnel.Part 2.Aerodynamics of the HB-2reference model.Thermophys Aeromech 2006;13(2):157-71.
26.Kharitonov AM,Zvegintsev VI,Adamov NP,Vasenev LG,Kuraeva AD,Nalivajchenko DG,et al.Calibration trials of working capabilities of the new hypersonic wind tunnel AT-303 at ITAM.Proceedings of the 1st European conference for aerospace sciences(EUCASS).2005.
27.DeSpirito J.Base pressure computations of the DERA generic missile wind tunnel model.Army Research Laboratory,Aberdeen Proving Ground;2005.Report No.:ARL-TR-3653.
28.Kuchi-Ishi S,Watanabe S,Nagai S,Tsuda S,Koyama T,Hirabayashi N,et al.Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2(Part 1:1.27 m hypersonic wind tunnel results).Tokyo:Japan Aerospace Exploration Agency;2005.Report No.:JAXA-RR-04-035E.
29.Penland JA.Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90°.Washington,D.C.:NACA Langley Aerodynamic Laboratory;1963.Report No.:NACA TN-3861.
2.Stengel RF.Strategies for control of the space shuttle transition.Journal of Spacecraft and Rockets 1973;10(1):73-84.
3.Dahlem V,Flehaerty JI,Shereda DE,Prziembel CEG.High angle of attack missile aerodynamics at Mach numbers 0.3 to 1.5.Flight Dynamics Laboratory,Wright Patterson Air Force Base;1980.Report No.:AFWAL-TR-80-3070.
4.Oberkampf WL,Nicolaides JD.Aerodynamics of finned missiles at high angles of attack.AIAA J 1971;9(12):2378-84.
5.Hadidoolabi M,Ansiaran H.Supersonic flow over a pitching delta wing using surface pressure measurements and numerical simulations.Chin J Aeronaut 2018;31(1):65-78.
6.Votta R.Advanced models for prediction of high altitude aerothermal loads of a space re-entry vehicle[dissertation].Potenza:Universita degli Studi della Basilicata;2008.
7.Cummings RM,Forsythe JR,Morton SA,Squires KD.Computational challenges in high angle of attack flow prediction.Prog Aerosp Sci 2003;39(5):369-83.
8.Mehta R.Computations of flowfield over reentry modules at high speed.Comput Simul Appl 2011.
9.Bai CY,Wu ZN.Hypersonic starting flow at high angle of attack.Chin J Aeronaut 2016;29(2):297-304.
10.Elfstrom GM,Medved B.The Yugoslav 1.5 m trisonic blowdown wind tunnel.Proceedings of the 14th AIAA aerodynamic testing conference.Reston:AIAA;1986.
11.Damljanovic′D,Isakovic′J,Rasˇuo B.T-38 Wind tunnel data quality assurance based on testing of a standard model.J Aircraft2013;50(4):1141-9.
12.Vukovic′Dj,C′urcˇic′D,Marinkovski D,Damljanovic′D,Samardzˇic′M,Vitic′A.Living with supersonic starting loads in the T-38 trisonic wind tunnel of VTI.Proceedings of the 29th congress of the international council of the aeronautical sciences(ICAS).2014.
13.Gray JD.Summary report on aerodynamic characteristics of standard models HB-1 and HB-2.Arnold Engineering Development Center;1964.Report No.:AEDC-TDR-64-137.
14.Gray JD,Lindsay EE.Force tests of standard hypervelocity ballistic models HB-1 and HB-2 at Mach 1.5 to 10.Arnold Engineering Development Center;1963.Report No.:AEDC-TDR-63-137.
15.Ceresuela R.Mesure′s d‘efforts et de pressions sur la maquette balistique etalon HB-2 de Mach 2 a Mach 16,5.ONERA;1964.Report No.:Note Technique 13/1879 A.
16.Malcolm GN.Chapman GT.A computer program for systematically analyzing free-flight data to determine the aerodynamics of axisymmetric bodies.Washington,D.C.:NASA Ames Research Center;1968.Report No.:NASA TN D-4766.
17.Opalka KO.Force tests of the hypersonic ballistic standard models HB-1 and HB-2.Ballistic Research Labs,Aberdeen Proving Ground;1966.Report No.:BLR-MR-1798.
18.Wesstroem P.Lundgren S.Three-component force measurements of a heat insulated AGARD Hb-2 model at M equals 4 and Mequals 7 using an uncooled balance.Stockholm:FFA;1974.Report No.:FFA-TN-AX-805.
19.Dj Vukovic′,Damljanovic′D.Evaluation of a force balance with semiconductor strain gauges in wind tunnel tests of the HB-2standard model.Proc Inst Mech Eng Part G:J Aerospace Eng2015;229(12):2272-81.
20.Kumar RS,Das S,Kumar P,Prasad JK.Investigation of flow field around a typical reentry capsule at supersonic speeds.Proceedings of the XXVI national convention of aerospace engineers.2012.
21.Damljanovic′D,Rasˇuo B,Vukovic′DJ,Mandic′S,Isakovic′J.Hypervelocity ballistic reference models as experimental supersonic test cases.Aerosp Sci Technol 2016;52:189-97.
22.Recommended practice:Calibration and use of internal straingage balances with application to wind tunnel testing.Reston:AIAA;2003.Report No.:AIAA-0091-2003.
23.Compton WB.Effect on base drag of recessing the bases of conical afterbodies at subsonic and transonic speeds.Washington,D.C.:NACA Langley Research Center;1958.Report No.:NASA TN-D4821.
24.Wiswanath PR,Patil SR.Effectiveness of passive devices for axisymmetric base drag reduction at Mach 2.J Spacecraft 1990;27(3):234-7.
25.Adamov NP,Vasenev LG,Zvegintsev VI,Mazhul II,Nalivaichenko DG,Novikov AV,et al.Characteristics of the AT-303hypersonic wind tunnel.Part 2.Aerodynamics of the HB-2reference model.Thermophys Aeromech 2006;13(2):157-71.
26.Kharitonov AM,Zvegintsev VI,Adamov NP,Vasenev LG,Kuraeva AD,Nalivajchenko DG,et al.Calibration trials of working capabilities of the new hypersonic wind tunnel AT-303 at ITAM.Proceedings of the 1st European conference for aerospace sciences(EUCASS).2005.
27.DeSpirito J.Base pressure computations of the DERA generic missile wind tunnel model.Army Research Laboratory,Aberdeen Proving Ground;2005.Report No.:ARL-TR-3653.
28.Kuchi-Ishi S,Watanabe S,Nagai S,Tsuda S,Koyama T,Hirabayashi N,et al.Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2(Part 1:1.27 m hypersonic wind tunnel results).Tokyo:Japan Aerospace Exploration Agency;2005.Report No.:JAXA-RR-04-035E.
29.Penland JA.Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90°.Washington,D.C.:NACA Langley Aerodynamic Laboratory;1963.Report No.:NACA TN-3861.