SIKORSKY SSC-A09 AIRFOIL (ssca09-il)
SIKORSKY SSC-A09 AIRFOIL - Sikorsky/Flemming SSC-A09 transonic rotorcraft airfoil
| Details | Dat file | Parser | |
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(ssca09-il) SIKORSKY SSC-A09 AIRFOIL Sikorsky/Flemming SSC-A09 transonic rotorcraft airfoil Max thickness 9% at 37.7% chord. Max camber 1.2% at 17.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
SIKORSKY SSC-A09 AIRFOIL 66. 66. 0.0000000 0.0000000 0.0001990 0.0020004 0.0007980 0.0039456 0.0019940 0.0064817 0.0029910 0.0080286 0.0044866 0.0098685 0.0069791 0.0123915 0.0099701 0.0149206 0.0159522 0.0190758 0.0219343 0.0224997 0.0279164 0.0254451 0.0338985 0.0280394 0.0398806 0.0303688 0.0458627 0.0324936 0.0518448 0.0344488 0.0578269 0.0362486 0.0677969 0.0389031 0.0777671 0.0411432 0.0877373 0.0430162 0.0977075 0.0445832 0.1126626 0.0465043 0.1276179 0.0480542 0.1425731 0.0493453 0.1575294 0.0504438 0.1724845 0.0513848 0.1874397 0.0521844 0.2023950 0.0528595 0.2173502 0.0534273 0.2323054 0.0539109 0.2472606 0.0543222 0.2771711 0.0549582 0.3070815 0.0553685 0.3369920 0.0555642 0.3768725 0.0554939 0.4167542 0.0550395 0.4366944 0.0546633 0.4566347 0.0541818 0.4765750 0.0535949 0.4965153 0.0528987 0.5164557 0.0520931 0.5363959 0.0511762 0.5563362 0.0501489 0.5762765 0.0490093 0.5962168 0.0477553 0.6161571 0.0463809 0.6360974 0.0448751 0.6560386 0.0432198 0.6759790 0.0413910 0.6959193 0.0393675 0.7158596 0.0371404 0.7357998 0.0347187 0.7557402 0.0321385 0.7756805 0.0294449 0.7956207 0.0266811 0.8155611 0.0238711 0.8355014 0.0210120 0.8554416 0.0180887 0.8753819 0.0150931 0.8953232 0.0120514 0.9152635 0.0090458 0.9352039 0.0062289 0.9551441 0.0038493 0.9750844 0.0022883 0.9850546 0.0019873 0.9950247 0.0021348 1.0000000 0.0024077 0.0000000 0.0000000 0.0001990 -.0014536 0.0007980 -.0028691 0.0019940 -.0045726 0.0029910 -.0054464 0.0044866 -.0064445 0.0069791 -.0077026 0.0099701 -.0088773 0.0159522 -.0107041 0.0219343 -.0121748 0.0279164 -.0134469 0.0338985 -.0145875 0.0398806 -.0156308 0.0458627 -.0165939 0.0518448 -.0174868 0.0578269 -.0183144 0.0677969 -.0195684 0.0777671 -.0206910 0.0877373 -.0217062 0.0977075 -.0226382 0.1126626 -.0239102 0.1276179 -.0250639 0.1425731 -.0261243 0.1575294 -.0271044 0.1724845 -.0280133 0.1874397 -.0288530 0.2023950 -.0296285 0.2173502 -.0303387 0.2323054 -.0309878 0.2472606 -.0315787 0.2771711 -.0325939 0.3070815 -.0334015 0.3369920 -.0340074 0.3768725 -.0345060 0.4167542 -.0346375 0.4366944 -.0345582 0.4566347 -.0343756 0.4765750 -.0340867 0.4965153 -.0336834 0.5164557 -.0331648 0.5363959 -.0325317 0.5563362 -.0317904 0.5762765 -.0309487 0.5962168 -.0300177 0.6161571 -.0290025 0.6360974 -.0279040 0.6560386 -.0267202 0.6759790 -.0254481 0.6959193 -.0240878 0.7158596 -.0226422 0.7357998 -.0211213 0.7557402 -.0195403 0.7756805 -.0179181 0.7956207 -.0162719 0.8155611 -.0146166 0.8355014 -.0129573 0.8554416 -.0112890 0.8753819 -.0095976 0.8953232 -.0078631 0.9152635 -.0060814 0.9352039 -.0042897 0.9551441 -.0026103 0.9750844 -.0013252 0.9850546 -.0009922 0.9950247 -.0008628 1.0000000 -.0008026 |
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Polars for SIKORSKY SSC-A09 AIRFOIL (ssca09-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ssca09-il | 50,000 | 9 | 28.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca09-il | 50,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca09-il | 100,000 | 9 | 38.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca09-il | 100,000 | 5 | 39.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca09-il | 200,000 | 9 | 50 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca09-il | 200,000 | 5 | 52.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca09-il | 500,000 | 9 | 72 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca09-il | 500,000 | 5 | 70.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca09-il | 1,000,000 | 9 | 87 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca09-il | 1,000,000 | 5 | 82.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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