SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 100,000 Max Cl/Cd: 39.26 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ssca09-il-100000-n5.txt Download as CSV file: xf-ssca09-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5057 0.08099 0.07665 -0.0245 1.0000 0.0636
-7.750 -0.5948 0.06847 0.06363 -0.0240 1.0000 0.0369
-7.500 -0.5963 0.06033 0.05494 -0.0265 1.0000 0.0289
-7.250 -0.5878 0.05630 0.05083 -0.0268 1.0000 0.0281
-7.000 -0.5787 0.05232 0.04666 -0.0269 1.0000 0.0274
-6.750 -0.5685 0.04841 0.04249 -0.0267 1.0000 0.0267
-6.500 -0.5576 0.04469 0.03845 -0.0258 1.0000 0.0261
-6.250 -0.5467 0.04127 0.03467 -0.0244 1.0000 0.0255
-6.000 -0.5360 0.03822 0.03127 -0.0224 1.0000 0.0251
-5.750 -0.5240 0.03546 0.02812 -0.0202 1.0000 0.0248
-5.500 -0.5099 0.03294 0.02521 -0.0182 1.0000 0.0247
-5.250 -0.4939 0.03067 0.02254 -0.0164 1.0000 0.0247
-5.000 -0.4761 0.02875 0.02028 -0.0147 1.0000 0.0253
-4.750 -0.4570 0.02721 0.01843 -0.0132 1.0000 0.0267
-4.500 -0.4336 0.02571 0.01658 -0.0124 0.9990 0.0282
-4.250 -0.4018 0.02408 0.01462 -0.0130 0.9960 0.0290
-4.000 -0.3705 0.02237 0.01271 -0.0137 0.9933 0.0298
-3.750 -0.3404 0.02088 0.01120 -0.0144 0.9903 0.0311
-3.500 -0.3089 0.01986 0.01016 -0.0153 0.9873 0.0338
-3.250 -0.2761 0.01906 0.00927 -0.0165 0.9846 0.0381
-3.000 -0.2469 0.01807 0.00823 -0.0170 0.9808 0.0415
-2.750 -0.2147 0.01741 0.00751 -0.0182 0.9773 0.0487
-2.500 -0.1806 0.01674 0.00680 -0.0197 0.9745 0.0634
-2.250 -0.1527 0.01520 0.00620 -0.0206 0.9708 0.2360
-2.000 -0.1383 0.01338 0.00654 -0.0172 0.9671 0.7430
-1.750 -0.1207 0.01380 0.00728 -0.0118 0.9635 0.8864
-1.500 -0.0794 0.01423 0.00758 -0.0122 0.9631 0.9461
-1.250 -0.0381 0.01424 0.00738 -0.0151 0.9600 0.9560
-1.000 0.0021 0.01423 0.00722 -0.0179 0.9558 0.9641
-0.750 0.0427 0.01424 0.00709 -0.0208 0.9518 0.9722
-0.500 0.0885 0.01422 0.00696 -0.0248 0.9487 0.9770
-0.250 0.1278 0.01419 0.00685 -0.0274 0.9405 0.9837
0.000 0.1703 0.01405 0.00663 -0.0300 0.9252 0.9872
0.250 0.2048 0.01378 0.00629 -0.0304 0.9028 0.9926
0.500 0.2364 0.01349 0.00595 -0.0305 0.8817 0.9994
0.750 0.2560 0.01332 0.00574 -0.0285 0.8653 1.0000
1.000 0.2753 0.01318 0.00558 -0.0267 0.8504 1.0000
1.250 0.2949 0.01305 0.00543 -0.0248 0.8349 1.0000
1.500 0.3148 0.01293 0.00528 -0.0230 0.8179 1.0000
1.750 0.3354 0.01284 0.00519 -0.0214 0.7980 1.0000
2.000 0.3560 0.01273 0.00507 -0.0196 0.7761 1.0000
2.250 0.3771 0.01265 0.00497 -0.0179 0.7476 1.0000
2.500 0.3983 0.01258 0.00485 -0.0162 0.7076 1.0000
2.750 0.4183 0.01251 0.00457 -0.0138 0.6446 1.0000
3.000 0.4376 0.01273 0.00434 -0.0114 0.5499 1.0000
3.250 0.4580 0.01336 0.00442 -0.0099 0.4476 1.0000
3.500 0.4800 0.01405 0.00468 -0.0092 0.3721 1.0000
3.750 0.5032 0.01466 0.00500 -0.0087 0.3238 1.0000
4.000 0.5272 0.01520 0.00537 -0.0083 0.2918 1.0000
4.250 0.5518 0.01568 0.00574 -0.0080 0.2692 1.0000
4.500 0.5767 0.01616 0.00615 -0.0077 0.2528 1.0000
4.750 0.6017 0.01664 0.00658 -0.0074 0.2390 1.0000
5.000 0.6268 0.01713 0.00707 -0.0071 0.2271 1.0000
5.250 0.6517 0.01766 0.00755 -0.0068 0.2174 1.0000
5.500 0.6772 0.01815 0.00809 -0.0066 0.2081 1.0000
5.750 0.7025 0.01868 0.00865 -0.0064 0.1992 1.0000
6.250 0.7528 0.01971 0.00978 -0.0060 0.1795 1.0000
6.500 0.7779 0.02025 0.01039 -0.0058 0.1698 1.0000
6.750 0.8025 0.02082 0.01096 -0.0056 0.1608 1.0000
7.000 0.8275 0.02132 0.01165 -0.0054 0.1504 1.0000
7.250 0.8521 0.02187 0.01234 -0.0052 0.1398 1.0000
7.500 0.8763 0.02241 0.01299 -0.0050 0.1284 1.0000
7.750 0.9002 0.02295 0.01365 -0.0047 0.1159 1.0000
8.000 0.9238 0.02353 0.01438 -0.0044 0.1023 1.0000
8.250 0.9470 0.02421 0.01516 -0.0041 0.0883 1.0000
8.500 0.9691 0.02506 0.01608 -0.0037 0.0763 1.0000
8.750 0.9900 0.02610 0.01715 -0.0032 0.0663 1.0000
9.000 1.0096 0.02732 0.01843 -0.0026 0.0587 1.0000
9.250 1.0285 0.02873 0.02004 -0.0018 0.0526 1.0000
9.500 1.0455 0.03017 0.02155 -0.0011 0.0476 1.0000
9.750 1.0620 0.03188 0.02348 -0.0001 0.0442 1.0000
10.000 1.0778 0.03360 0.02544 0.0009 0.0411 1.0000
10.250 1.0917 0.03526 0.02724 0.0019 0.0384 1.0000
10.500 1.1026 0.03735 0.02943 0.0030 0.0362 1.0000
10.750 1.1136 0.03946 0.03195 0.0043 0.0343 1.0000
11.000 1.1214 0.04184 0.03464 0.0056 0.0330 1.0000
11.250 1.1257 0.04434 0.03742 0.0071 0.0319 1.0000
11.500 1.1253 0.04688 0.04020 0.0088 0.0311 1.0000
11.750 1.1224 0.04967 0.04321 0.0102 0.0304 1.0000
12.000 1.1171 0.05275 0.04652 0.0112 0.0298 1.0000
12.250 1.1097 0.05617 0.05013 0.0115 0.0294 1.0000
12.500 1.0999 0.06006 0.05420 0.0111 0.0289 1.0000
12.750 1.0868 0.06474 0.05907 0.0098 0.0287 1.0000
13.000 1.0694 0.07056 0.06512 0.0070 0.0285 1.0000
13.250 1.0427 0.07910 0.07396 0.0011 0.0288 1.0000
13.500 0.9105 0.11773 0.11301 -0.0262 0.0327 1.0000
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Polar data table (+)
Polar graphs
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