SIKORSKY SSC-A07 AIRFOIL (ssca07-il)
SIKORSKY SSC-A07 AIRFOIL - Sikorsky/Flemming SSC-A07 transonic rotorcraft airfoil
| Details | Dat file | Parser | |
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(ssca07-il) SIKORSKY SSC-A07 AIRFOIL Sikorsky/Flemming SSC-A07 transonic rotorcraft airfoil Max thickness 7% at 37.7% chord. Max camber 0.9% at 17.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
SIKORSKY SSC-A07 AIRFOIL
66. 66.
0.0000000 0.0000000
0.0001990 0.0015559
0.0007980 0.0030688
0.0019940 0.0050413
0.0029910 0.0062445
0.0044866 0.0076755
0.0069791 0.0096378
0.0099701 0.0116049
0.0159522 0.0148367
0.0219343 0.0174998
0.0279164 0.0197906
0.0338985 0.0218084
0.0398806 0.0236202
0.0458627 0.0252728
0.0518448 0.0267935
0.0578269 0.0281934
0.0677969 0.0302580
0.0777671 0.0320003
0.0877373 0.0334570
0.0977075 0.0346758
0.1126626 0.0361700
0.1276179 0.0373755
0.1425731 0.0383797
0.1575294 0.0392341
0.1724845 0.0399660
0.1874397 0.0405879
0.2023950 0.0411130
0.2173502 0.0415546
0.2323054 0.0419307
0.2472606 0.0422506
0.2771711 0.0427453
0.3070815 0.0430644
0.3369920 0.0432166
0.3768725 0.0431619
0.4167542 0.0428085
0.4366944 0.0425159
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0.9551441 0.0029939
0.9750844 0.0017798
0.9850546 0.0015457
0.9950247 0.0016604
1.0000000 0.0018727
0.0000000 0.0000000
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0.8355014 -.0100779
0.8554416 -.0087803
0.8753819 -.0074648
0.8953232 -.0061157
0.9152635 -.0047300
0.9352039 -.0033364
0.9551441 -.0020302
0.9750844 -.0010307
0.9850546 -.0007717
0.9950247 -.0006711
1.0000000 -.0006242
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Polars for SIKORSKY SSC-A07 AIRFOIL (ssca07-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ssca07-il | 50,000 | 9 | 29.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 50,000 | 5 | 28.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 100,000 | 9 | 39.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 100,000 | 5 | 37.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 200,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 200,000 | 5 | 48.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 500,000 | 9 | 64.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 500,000 | 5 | 61.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 1,000,000 | 9 | 76 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 1,000,000 | 5 | 74.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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