DOT/FAA/AR-03/47 Low Takeoff Rotation Speed Commuter Type Aircraft Office of Aviation Research Washington, D.C. 20591 Aerodynamic Performance of Type II and Type IV Fluids August 2003 Final Report This document is available to the U.S. public through the National Technical Information Service (NTIS), Springfield, Virginia 22161. U.S. Department of Transportation Federal Aviation Administration NOTICE This document is disseminated under the sponsorship of the U.S. Department of Transportation in the interest of information exchange. The United States Government assumes no liability for the contents or use thereof. The United States Government does not endorse products or manufacturers. Trade or manufacturer's names appear herein solely because they are considered essential to the objective of this report. This document does not constitute FAA certification policy. Consult your local FAA aircraft certification office as to its use. This report is available at the Federal Aviation Administration William J. Hughes Technical Center's Full-Text Technical Reports page: actlibrary.tc.faa.gov in Adobe Acrobat portable document format (PDF). Technical Report Documentation Page 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. DOT/FAA/AR-03/47 4. Title and Subtitle 5. Report Date LOW TAKEOFF ROTATION SPEED COMMUTER TYPE AIRCRAFT August 2003 AERODYNAMIC PERFORMANCE OF TYPE II AND TYPE IV FLUIDS 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. Arlene Beisswenger and Jean-Louis Laforte 9. Performing Organization Name and Address 10. Work Unit No. (TRAIS) Anti-icing Materials International Laboratory Université du Québec à Chicoutimi 555, boulevard de l’Université 11. Contract or Grant No. Chicoutimi, Québec G7H 2B1 12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered U.S. Department of Transportation Final Report Federal Aviation Administration Office of Aviation Research 14. Sponsoring Agency Code Washington, DC 20591 AFS-200, ANM-111N 15. Supplementary Notes The FAA William J. Hughes Technical Center COTR was Charles Masters. 16. Abstract Type II and Type IV aircraft ground anti-icing fluids are currently used on commuter type aircraft, although they are being certified to AMS1428 Annex B, which corresponds to aerodynamic acceptance test for large transport type jet aircraft whose takeoff rotation speeds generally exceed 100 to 110 knots. Some aircraft manufacturers have indicated certain performance adjustments or other commuter type operational procedures to be followed for selected aircraft when operators employ these Type II and IV fluids. At the request of the Federal Aviation Administration (FAA) William J. Hughes Technical Center, the Anti-icing Materials International Laboratory conducted AMS1428D Annex C Flat Plate Elimination Tests (FPET) for commuter type aircraft to ascertain their level of performance. The aerodynamic acceptance tests were conducted at three temperature intervals for two Type II fluids and three Type IV fluids in their neat, 75/25, and 50/50 dilution forms. A deicing and anti-icing fluid is considered acceptable at a test temperature if none of the independent boundary layer displacement thickness measurements are greater than the acceptance criteria defined by the military fluid that is tested simultaneously. The results showed that all the 50/50 dilutions are acceptable for the low-speed ramp down to -10°C, the lowest temperature tested due to freeze-point restrictions. Three of the five 75/25 dilutions are acceptable for the low-speed ramp down to -10°C; below this temperature none of the fluids were acceptable. For the two other fluids, one was acceptable only at 0°C, the other was not acceptable at any temperature. For the fluids in their neat form, only one was acceptable at 0°C. For all other fluids, the neat FPET results were greater than the acceptance criteria. 17. Key Words 18. Distribution Statement Aircraft anti-icing fluids, Commuter, Takeoff, Type II fluids, This document is available to the public through the National Type IV fluids, deicing Technical Information Service (NTIS) Springfield, Virginia 22161. 19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 241 Form DOT F1700.7 (8-72) Reproduction of completed page authorized TABLE OF CONTENTS Page EXECUTIVE SUMMARY vii 1. INTRODUCTION 1 1.1 Objective 1 1.2 Scope 1 2. TEST DESCRIPTION 1 2.1 Flat Plate Elimination Test of AMS1428 Annex C 1 2.2 Measurements 3 2.3 Calibration and Acceptance Criteria 3 3. TEST RESULTS 3 3.1 Test Fluids 3 3.2 Calculation of the Calibration and Acceptance Criteria 5 3.3 Test Results–Kilfrost ABC-3 7 3.4 Test Results–Clariant Safewing MPII 1951 10 3.5 Test Results–Octagon Process MaxFlight 14 3.6 Test Results–SPCA AD-480 17 3.7 Test Results–Dow Ultra+ 21 4. DISCUSSION 24 5. CONCLUSIONS 25 6. RECOMMENDATIONS 25 7. REFERENCES 26 APPENDICES A–Boundary Layer Displacement Thickness Measurement Principle B–Test Data Sheets iii LIST OF FIGURES Figure Page 1 Test Section Box in Wind Tunnel 2 2 Luan Phan Refrigerated Wind Tunnel 2 3 Takeoff Ground Acceleration Simulation 2 4 Acceptance Criteria for the Type II Fluid Test Series 5 5 Acceptance Criteria for the Type IV Fluid Test Series 6 6 Low-Speed Ramp Aerodynamic Test Results for Kilfrost ABC-3 9 7 Fluid Elimination for Kilfrost ABC-3 9 8 Relative Humidity for Kilfrost ABC-3 10 9 Low-Speed Ramp Aerodynamic Test Results for Clariant Safewing MPII 1951 12 10 Fluid Elimination for Clariant Safewing MPII 1951 13 11 Relative Humidity for Clariant Safewing MPII 1951 13 12 Low-Speed Ramp Aerodynamic Test Results for Octagon Process MaxFlight 16 13 Fluid Elimination for Octagon Process MaxFlight 16 14 Relative Humidity for Octagon Process MaxFlight 17 15 Low-Speed Ramp Aerodynamic Test Results for SPCA AD-480 19 16 Fluid Elimination for SPCA AD-480 20 17 Relative Humidity for SPCA AD-480 20 18 Low-Speed Ramp Aerodynamic Test Results for Dow Ultra+ 23 19 Fluid Elimination for Dow Ultra+ 23 20 Relative Humidity for Dow Ultra+ 24 21 Low-Speed Ramp Aerodynamic Acceptance Summary 24 iv LIST OF TABLES Table Page 1 Fluid Identification 4 2 Aerodynamic Performance for Kilfrost ABC-3, Neat 7 3 Aerodynamic Performance for Kilfrost ABC-3, 75/25 Dilution 8 4 Aerodynamic Performance for Kilfrost ABC-3, 50/50 Dilution 8 5 Aerodynamic Performance for Clariant Safewing MPII 1951, Neat 11 6 Aerodynamic Performance for Clariant Safewing MPII 1951, 75/25 Dilution 11 7 Aerodynamic Performance for Clariant Safewing MPII 1951, 50/50 Dilution 12 8 Aerodynamic Performance for Octagon Process MaxFlight, Neat 14 9 Aerodynamic Performance for Octagon Process MaxFlight, 75/25 Dilution 15 10 Aerodynamic Performance for Octagon Process MaxFlight, 50/50 Dilution 15 11 Aerodynamic Performance for SPCA AD-480, Neat 18 12 Aerodynamic Performance for SPCA AD-480, 75/25 Dilution 18 13 Aerodynamic Performance for SPCA AD-480, 50/50 Dilution 19 14 Aerodynamic Performance for Dow Ultra+, Neat 21 15 Aerodynamic Performance for Dow Ultra+, 75/25 Dilution 22 16 Aerodynamic Performance for Dow Ultra+, 50/50 Dilution 22 LIST OF ACRONYMS AMIL Anti-icing Materials International Laboratory FAA Federal Aviation Administration AMS Aerospace Material Specification BLDT Boundary Layer Displacement Thickness FPET Flat Plate Elimination Test W.C. Water Change (%) v/vi EXECUTIVE SUMMARY Type II and Type IV aircraft ground anti-icing fluids are currently used on commuter type aircraft, although they are being certified to AMS1428 Annex B, which corresponds to aerodynamic acceptance test for large transport type jet aircraft whose takeoff rotation speeds generally exceed 100 to 110 knots. Some aircraft manufacturers have indicated certain performance adjustments or other commuter type operational procedures to be followed for selected aircraft when operators employ these Type II and IV fluids. At the request of the Federal Aviation Administration William J. Hughes Technical Center, the Anti-icing Materials International Laboratory conducted AMS1428 Annex C Flat Plate Elimination Tests (FPET) for commuter type aircraft to ascertain their level of performance. The aerodynamic acceptance tests were conducted at three temperature intervals for two Type II fluids and three Type IV fluids in their neat, 75/25, and 50/50 dilution forms. A deicing and anti-icing fluid is considered acceptable at a test temperature if none of the independent boundary layer displacement thickness measurements are greater than the acceptance criteria defined by the military fluid that is tested simultaneously. The results showed that all the 50/50 dilutions are acceptable for the low-speed ramp down to -10°C, the lowest temperature tested due to freeze-point restrictions. Three of the five 75/25 dilutions are acceptable for the low-speed ramp down to -10°C, below this temperature none of the fluids were acceptable. For the two other fluids, one was acceptable only at 0°C, the other was not acceptable at any temperature. For the fluids in their neat form, only one was acceptable at 0°C. For other fluids tested in their neat form, results were greater than the acceptance criteria. vii/viii 1. INTRODUCTION. Type II and Type IV aircraft ground anti-icing fluids are currently used on commuter type aircraft, although they are only being certified to AMS1428D [1] Annex B, which corresponds to aerodynamic acceptance test for large transport type jet aircraft whose takeoff rotation speeds generally exceed approximately 100 to 110 knots. Some aircraft manufacturers have indicated certain performance adjustments or other commuter type operational procedures to be followed for selected aircraft when operators employ these Type II and IV fluids. A test method exists for assessing the aerodynamic acceptance of anti-icing fluids on commuter type aircraft, Annex C of AMS1428; however, no fluids are tested to this specification. At the request of the Federal Aviation Administration (FAA) William J. Hughes Technical Center, the Anti-icing Materials International Laboratory (AMIL) conducted AMS1428 Annex C Flat Plate Elimination Tests (FPET) of selected Type II and Type IV deicing and anti-icing fluids for commuter type aircraft to ascertain their level of performance. 1.1 OBJECTIVE. The objective was to determine the aerodynamic acceptance of Type II and IV fluids when tested according to Annex C of AMS1428 for commuter type aircraft. 1.2 SCOPE. Flat Plate Elimination Testing according to Annex C of AMS1428D [1] were conducted at three temperature intervals for two Type II fluids and three Type IV fluids in their neat, 75/25, and 50/50 dilution forms. 2. TEST DESCRIPTION. 2.1 FLAT PLATE ELIMINATION TEST OF AMS1428 ANNEX C. This test is designed to measure the boundary layer displacement thickness (BLDT), which is related to lift loss on commuter type aircraft when no compensating measures are taken into aircraft takeoff procedures and takeoff rotation speeds generally exceed approximately 60 knots [2]. The flat plate setup consists of a duct (figure 1) inserted in the test section of AMIL‘s cold wind tunnel (figure 2). In this tunnel, the airflow and the fluid can be maintained at a constant temperature, between 5°±1°C and -45°±2°C. The FPET procedure consists of submitting a 2-mm-thick layer of anti-icing fluid covering the test duct floor to an accelerating air flow of 2.1 m/s×, simulating an aircraft takeoff (figure 3). This test is commonly referred to as the low-speed ramp as opposed to the high-speed ramp test of AMS1428 Annex B concerning FPET for large jet transport type aircraft. The BLDT on the flat plate is measured at pressure tap location P3 (figure 1) 20 seconds after the beginning of the simulated takeoff. A detailed description of this test is presented in Annex C of AMS1428D [1]. 1 P1 Divergent cone Insulation Convergent cone Test section 1.5 meter P2 P3 Ta Tf Tunnel wall P1,P2,P3 - Static pressure gauges Ta- Air temperature thermocouple Tf- Fluid temperature thermocouple FIGURE 1. TEST SECTION BOX IN WIND TUNNEL FIGURE 2. LUAN PHAN REFRIGERATED WIND TUNNEL 50 Low Speed Ramp 45 40 35 m/s ± 3 35 30 25 20 15 17 s ± 1 10 5 0 0 5 10 15 20 25 30 TIME (s) FIGURE 3. TAKEOFF GROUND ACCELERATION SIMULATION 2 2.2 MEASUREMENTS. In an FPET, the fluid performance is evaluated from BLDT measurements. The BLDT value used for the fluid evaluation is the average of the BLDT measured between the 19th and the 21st second following the beginning of the test. The starting time (t = 0) is evaluated by extrapolating the straight line of the acceleration ramp to the point where V = 0 m/s. In addition, the following parameters are measured: • refractive index of the fluid, which is used to determine the water change (percent). • fluid film thickness (µm) at the beginning and at the end of the FPET to compute fluid elimination (percent). 2.3 CALIBRATION AND ACCEPTANCE CRITERIA. The calibration is obtained from dry tests, performed without fluid, and reference fluid tests using a 75/25 dilution of the reference military deicing fluid, MIL-A-8243D, for which BLDT results are well documented. The BLDT values obtained from a dry, without fluid, test should be 2.8 ±0.4 mm. For dry and calibration tests, the BLDT values are recorded at four temperature intervals: 0°, -10°, -20°, and -25°C. Reference fluid BLDT values and dry BLDT values are used to calculate the acceptance criteria required for certification. A candidate fluid is acceptable at a test temperature if none of the independent BLDT measurements are greater than the acceptance criteria. 3. TEST RESULTS. 3.1 TEST FLUIDS. The fluids evaluated in this study are presented in table 1. For this study, two Type II and three Type IV representative certified fluids were selected. They are the same fluids used in the aerodynamic flow-off performance study conducted concurrently by AMIL for the FAA under contract DTFA-0302-P10157. Tests were conducted at three temperature intervals for each dilution, as per AMS1428 Annex C [1]. For the neat fluid, the intervals were 0°, -10°, and -20°C. The dilutions, however, were tested at warmer temperatures due to freeze-point restrictions and the undesirability of running tests near the fluid‘s freezing point. Therefore, the 75/25 dilutions were tested at 0°, -10°, and -15°C (or -20°C where freeze-point restrictions allowed for it), and the 50/50 dilutions were tested at 0°, -5°, and -10°C. 3