SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 200,000 Max Cl/Cd: 49.96 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca09-il-200000.txt Download as CSV file: xf-ssca09-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A09 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6047 0.09314 0.08992 -0.0120 1.0000 0.0390
-8.750 -0.6117 0.08824 0.08494 -0.0168 1.0000 0.0391
-8.500 -0.6157 0.08376 0.08033 -0.0201 1.0000 0.0391
-8.250 -0.6170 0.07579 0.07245 -0.0213 1.0000 0.0402
-8.000 -0.6074 0.07243 0.06915 -0.0211 1.0000 0.0412
-7.750 -0.5998 0.06888 0.06557 -0.0222 1.0000 0.0424
-7.500 -0.5924 0.06494 0.06154 -0.0240 1.0000 0.0439
-7.250 -0.5841 0.06077 0.05722 -0.0259 1.0000 0.0461
-7.000 -0.5743 0.05873 0.05449 -0.0273 1.0000 0.0507
-6.750 -0.5724 0.05194 0.04755 -0.0275 1.0000 0.0521
-6.500 -0.5612 0.04877 0.04453 -0.0268 1.0000 0.0539
-6.250 -0.5539 0.04684 0.04259 -0.0249 1.0000 0.0569
-5.750 -0.5448 0.04179 0.03690 -0.0199 1.0000 0.0661
-5.500 -0.5337 0.03951 0.03465 -0.0183 1.0000 0.0685
-5.250 -0.5210 0.03781 0.03276 -0.0164 1.0000 0.0737
-5.000 -0.5094 0.03522 0.02988 -0.0148 1.0000 0.0808
-4.750 -0.4934 0.03344 0.02805 -0.0135 1.0000 0.0860
-4.500 -0.4776 0.03138 0.02577 -0.0123 1.0000 0.0962
-4.250 -0.4582 0.02966 0.02384 -0.0117 0.9996 0.1095
-4.000 -0.4093 0.02345 0.01613 -0.0087 0.9984 0.0386
-3.750 -0.3762 0.02056 0.01298 -0.0096 0.9967 0.0366
-3.500 -0.3410 0.01887 0.01106 -0.0107 0.9950 0.0362
-3.250 -0.3069 0.01801 0.01005 -0.0118 0.9924 0.0384
-3.000 -0.2734 0.01663 0.00861 -0.0129 0.9900 0.0402
-2.750 -0.2393 0.01539 0.00742 -0.0143 0.9877 0.0429
-2.500 -0.2025 0.01468 0.00671 -0.0163 0.9855 0.0486
-2.250 -0.1695 0.01395 0.00599 -0.0176 0.9820 0.0600
-2.000 -0.1409 0.01066 0.00525 -0.0193 0.9809 0.6355
-1.750 -0.1189 0.01049 0.00572 -0.0165 0.9769 0.8290
-1.500 -0.0955 0.01082 0.00612 -0.0141 0.9726 0.8884
-1.250 -0.0808 0.01131 0.00662 -0.0091 0.9668 0.9448
-1.000 0.0023 0.01167 0.00681 -0.0183 0.9729 0.9776
-0.750 0.0634 0.01157 0.00659 -0.0249 0.9646 0.9784
-0.500 0.1159 0.01141 0.00632 -0.0290 0.9485 0.9791
-0.250 0.1501 0.01124 0.00608 -0.0297 0.9329 0.9854
0.000 0.1861 0.01107 0.00586 -0.0310 0.9223 0.9914
0.250 0.2223 0.01089 0.00566 -0.0327 0.9119 0.9977
0.500 0.2459 0.01074 0.00548 -0.0318 0.9009 1.0000
0.750 0.2626 0.01056 0.00528 -0.0294 0.8900 1.0000
1.000 0.2797 0.01036 0.00505 -0.0270 0.8784 1.0000
1.250 0.2978 0.01015 0.00483 -0.0249 0.8654 1.0000
1.500 0.3159 0.00993 0.00460 -0.0227 0.8518 1.0000
1.750 0.3347 0.00972 0.00437 -0.0206 0.8376 1.0000
2.000 0.3541 0.00953 0.00417 -0.0185 0.8222 1.0000
2.250 0.3737 0.00933 0.00394 -0.0164 0.8047 1.0000
2.500 0.3953 0.00918 0.00378 -0.0148 0.7798 1.0000
2.750 0.4166 0.00904 0.00358 -0.0130 0.7468 1.0000
3.000 0.4379 0.00896 0.00336 -0.0111 0.6869 1.0000
3.250 0.4574 0.00935 0.00312 -0.0090 0.5589 1.0000
3.500 0.4789 0.01048 0.00338 -0.0083 0.3970 1.0000
4.000 0.5275 0.01195 0.00415 -0.0081 0.2862 1.0000
4.250 0.5529 0.01250 0.00452 -0.0080 0.2643 1.0000
4.500 0.5786 0.01301 0.00492 -0.0079 0.2491 1.0000
4.750 0.6048 0.01345 0.00532 -0.0078 0.2367 1.0000
5.000 0.6311 0.01390 0.00577 -0.0077 0.2259 1.0000
5.250 0.6572 0.01439 0.00620 -0.0077 0.2159 1.0000
5.500 0.6835 0.01482 0.00660 -0.0077 0.2058 1.0000
5.750 0.7101 0.01522 0.00705 -0.0076 0.1967 1.0000
6.000 0.7361 0.01576 0.00756 -0.0076 0.1886 1.0000
6.250 0.7626 0.01611 0.00800 -0.0076 0.1798 1.0000
6.500 0.7887 0.01659 0.00852 -0.0076 0.1710 1.0000
6.750 0.8144 0.01710 0.00900 -0.0075 0.1616 1.0000
7.000 0.8406 0.01734 0.00940 -0.0075 0.1508 1.0000
7.250 0.8662 0.01772 0.00986 -0.0075 0.1390 1.0000
7.500 0.8916 0.01804 0.01025 -0.0074 0.1253 1.0000
7.750 0.9168 0.01835 0.01063 -0.0073 0.1096 1.0000
8.000 0.9409 0.01891 0.01114 -0.0072 0.0932 1.0000
8.250 0.9652 0.01954 0.01183 -0.0069 0.0777 1.0000
8.500 0.9876 0.02055 0.01283 -0.0064 0.0661 1.0000
8.750 1.0076 0.02196 0.01418 -0.0057 0.0574 1.0000
9.000 1.0300 0.02293 0.01535 -0.0052 0.0513 1.0000
9.250 1.0478 0.02496 0.01735 -0.0043 0.0465 1.0000
9.500 1.0693 0.02624 0.01888 -0.0035 0.0438 1.0000
9.750 1.0894 0.02778 0.02058 -0.0027 0.0411 1.0000
10.000 1.1084 0.02942 0.02232 -0.0020 0.0389 1.0000
10.250 1.1224 0.03298 0.02604 -0.0010 0.0367 1.0000
10.500 1.1387 0.03439 0.02781 0.0001 0.0355 1.0000
10.750 1.1516 0.03668 0.03046 0.0014 0.0344 1.0000
11.000 1.1607 0.03935 0.03348 0.0028 0.0336 1.0000
11.250 1.1654 0.04230 0.03679 0.0045 0.0329 1.0000
11.500 1.1645 0.04551 0.04034 0.0063 0.0325 1.0000
11.750 1.1557 0.04880 0.04395 0.0086 0.0322 1.0000
12.000 1.1418 0.05237 0.04781 0.0105 0.0321 1.0000
12.250 1.1236 0.05657 0.05229 0.0113 0.0320 1.0000
12.500 1.1002 0.06182 0.05782 0.0105 0.0322 1.0000
12.750 1.0707 0.06883 0.06510 0.0072 0.0326 1.0000
13.000 1.0355 0.07858 0.07511 0.0002 0.0333 1.0000
13.250 0.9897 0.09383 0.09056 -0.0122 0.0344 1.0000
13.500 0.9301 0.11410 0.11083 -0.0252 0.0360 1.0000
13.750 0.8398 0.14830 0.14484 -0.0415 0.0453 1.0000
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Polar data table (+)
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