Static measurements of a NACA 0021 airfoil at high Reynolds numbers

Brunner, Claudia E.; Kiefer, Janik; Hansen, Martin O. L.; Hultmark, Marcus
Issue date: 4 August 2021
Cite as:
Brunner, Claudia E., Kiefer, Janik, Hansen, Martin O. L., & Hultmark, Marcus. (2021). Static measurements of a NACA 0021 airfoil at high Reynolds numbers [Data set]. Princeton University. https://doi.org/10.34770/9mv0-zd78
@electronic{brunner_claudia_e_2021,
  author      = {Brunner, Claudia E. and
                Kiefer, Janik and
                Hansen, Martin O. L. and
                Hultmark, Marcus},
  title       = {{Static measurements of a NACA 0021 airfo
                il at high Reynolds numbers}},
  publisher   = {{Princeton University}},
  year        = 2021,
  url         = {https://doi.org/10.34770/9mv0-zd78}
}
Abstract:

Reynolds number effects on the aerodynamics of the moderately thick NACA 0021 airfoil were experimentally studied by means of surface-pressure measurements. The use of a high-pressure wind tunnel allowed for variation of the chord Reynolds number over a range of 5.0 × 10^5 ≤ Re_c ≤ 7.9 × 10^6. The angle of attack was incrementally increased and decreased over a range of 0° ≤ alpha ≤ 40°, spanning both the attached and stalled regime at all Reynolds numbers. As such, attached and separated conditions, as well as the static stall and reattachment processes were studied. A fundamental change in the flow behaviour was observed around Re_c= 2.0 × 10^6. As the Reynolds number was increased beyond this value, the stall type gradually shifted from trailing-edge stall to leading-edge stall. The stall angle and the maximum lift coefficient increased with Reynolds number. Once the flow was separated, the separation point moved upstream and the suction peak decreased in magnitude with increasing Reynolds number. Two distinct types of hysteresis in reattachment were observed.

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# Filename Description Filesize
1 readMe.txt 3.31 KB
2 pressuretaps.txt 433 Bytes
3 Re7900000_decreasingAngle_corrected.txt 1.31 KB
4 Re7900000_increasingAngle_corrected.txt 1.3 KB
5 Re7000000_decreasingAngle_corrected.txt 1.29 KB
6 Re7000000_increasingAngle_corrected.txt 1.27 KB
7 Re5000000_decreasingAngle_corrected.txt 1.3 KB
8 Re5900000_decreasingAngle_corrected.txt 1.27 KB
9 Re5900000_increasingAngle_corrected.txt 1.33 KB
10 Re4000000_decreasingAngle_corrected.txt 1.3 KB
11 Re5000000_increasingAngle_corrected.txt 1.34 KB
12 Re3000000_decreasingAngle_corrected.txt 1.3 KB
13 Re3000000_increasingAngle_corrected.txt 1.35 KB
14 Re4000000_increasingAngle_corrected.txt 1.35 KB
15 Re1500000_decreasingAngle_corrected.txt 624 Bytes
16 Re2000000_decreasingAngle_corrected.txt 1.28 KB
17 Re2000000_increasingAngle_corrected.txt 1.33 KB
18 Re500000_decreasingAngle_corrected.txt 1.15 KB
19 Re1000000_decreasingAngle_corrected.txt 1.03 KB
20 Re1000000_increasingAngle_corrected.txt 1.08 KB
21 Re1500000_increasingAngle_corrected.txt 678 Bytes
22 Re500000_increasingAngle_corrected.txt 1.2 KB
23 Re7900000_decreasingAoA_raw.txt 17 KB
24 Re7000000_decreasingAoA_raw.txt 16.9 KB
25 Re7900000_increasingAoA_raw.txt 17.4 KB
26 Re5900000_decreasingAoA_raw.txt 17 KB
27 Re7000000_increasingAoA_raw.txt 17.3 KB
28 Re5000000_decreasingAoA_raw.txt 17 KB
29 Re5000000_increasingAoA_raw.txt 17.5 KB
30 Re5900000_increasingAoA_raw.txt 17.5 KB
31 Re4000000_decreasingAoA_raw.txt 17 KB
32 Re4000000_increasingAoA_raw.txt 17.6 KB
33 Re3000000_decreasingAoA_raw.txt 17.1 KB
34 Re3000000_increasingAoA_raw.txt 17.6 KB
35 Re2000000_decreasingAoA_raw.txt 17 KB
36 Re2000000_increasingAoA_raw.txt 17.6 KB
37 Re1500000_decreasingAoA_raw.txt 7.35 KB
38 Re1500000_increasingAoA_raw.txt 7.89 KB
39 Re1000000_decreasingAoA_raw.txt 13.3 KB
40 Re1000000_increasingAoA_raw.txt 13.8 KB
41 Re500000_decreasingAoA_raw.txt 15 KB
42 Re500000_increasingAoA_raw.txt 15.3 KB