SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 200,000 Max Cl/Cd: 52.74 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ssca09-il-200000-n5.txt Download as CSV file: xf-ssca09-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4645 0.11499 0.11181 0.0029 1.0000 0.0246
-10.500 -0.4646 0.11094 0.10777 0.0015 1.0000 0.0250
-10.000 -0.6069 0.11187 0.10856 0.0131 1.0000 0.0230
-9.000 -0.4888 0.07942 0.07633 -0.0118 1.0000 0.0205
-8.750 -0.4944 0.07410 0.07103 -0.0142 1.0000 0.0197
-8.250 -0.6288 0.06555 0.06207 -0.0223 1.0000 0.0164
-8.000 -0.6215 0.06225 0.05869 -0.0234 1.0000 0.0157
-7.750 -0.6169 0.05774 0.05402 -0.0248 1.0000 0.0155
-7.500 -0.6101 0.05298 0.04904 -0.0259 1.0000 0.0153
-7.250 -0.6014 0.04679 0.04231 -0.0261 1.0000 0.0161
-6.750 -0.5738 0.03884 0.03370 -0.0261 0.9917 0.0160
-6.500 -0.5518 0.03500 0.02951 -0.0271 0.9864 0.0157
-6.250 -0.5287 0.03157 0.02568 -0.0276 0.9812 0.0155
-6.000 -0.5042 0.02854 0.02223 -0.0278 0.9766 0.0154
-5.750 -0.4783 0.02593 0.01919 -0.0278 0.9726 0.0153
-5.500 -0.4528 0.02376 0.01664 -0.0275 0.9676 0.0154
-5.250 -0.4259 0.02195 0.01448 -0.0273 0.9635 0.0156
-5.000 -0.3992 0.02049 0.01274 -0.0270 0.9596 0.0159
-4.750 -0.3733 0.01913 0.01119 -0.0266 0.9551 0.0163
-4.500 -0.3476 0.01796 0.00996 -0.0263 0.9510 0.0170
-4.250 -0.3218 0.01719 0.00914 -0.0261 0.9471 0.0179
-4.000 -0.2959 0.01661 0.00851 -0.0258 0.9426 0.0198
-3.750 -0.2702 0.01600 0.00782 -0.0253 0.9384 0.0213
-3.500 -0.2458 0.01518 0.00697 -0.0246 0.9347 0.0224
-3.250 -0.2202 0.01453 0.00631 -0.0244 0.9299 0.0243
-3.000 -0.1944 0.01410 0.00584 -0.0240 0.9255 0.0273
-2.750 -0.1693 0.01366 0.00535 -0.0234 0.9217 0.0322
-2.500 -0.1424 0.01328 0.00492 -0.0233 0.9170 0.0388
-2.250 -0.1165 0.01274 0.00453 -0.0230 0.9123 0.0700
-2.000 -0.0950 0.01136 0.00415 -0.0227 0.9082 0.3172
-1.750 -0.0764 0.00996 0.00411 -0.0212 0.9035 0.6510
-1.500 -0.0583 0.00970 0.00437 -0.0181 0.8983 0.7930
-1.250 -0.0431 0.00977 0.00462 -0.0138 0.8937 0.8628
-1.000 -0.0213 0.00985 0.00468 -0.0118 0.8884 0.8901
-0.750 0.0024 0.00980 0.00456 -0.0104 0.8809 0.9026
-0.500 0.0251 0.00968 0.00437 -0.0087 0.8693 0.9131
-0.250 0.0467 0.00948 0.00407 -0.0065 0.8533 0.9228
0.000 0.0696 0.00930 0.00379 -0.0047 0.8365 0.9330
0.250 0.0955 0.00919 0.00360 -0.0039 0.8222 0.9429
0.500 0.1246 0.00911 0.00347 -0.0038 0.8104 0.9510
0.750 0.1535 0.00904 0.00334 -0.0038 0.7979 0.9601
1.000 0.1851 0.00898 0.00323 -0.0044 0.7834 0.9673
1.250 0.2172 0.00892 0.00312 -0.0052 0.7660 0.9744
1.500 0.2503 0.00887 0.00300 -0.0061 0.7420 0.9808
1.750 0.2835 0.00883 0.00286 -0.0071 0.7039 0.9866
2.000 0.3158 0.00890 0.00266 -0.0078 0.6408 0.9923
2.250 0.3483 0.00927 0.00258 -0.0088 0.5487 0.9973
2.500 0.3767 0.00987 0.00268 -0.0094 0.4448 1.0000
2.750 0.4003 0.01044 0.00284 -0.0092 0.3659 1.0000
3.000 0.4242 0.01088 0.00302 -0.0089 0.3145 1.0000
3.250 0.4487 0.01124 0.00322 -0.0086 0.2810 1.0000
3.500 0.4738 0.01157 0.00343 -0.0084 0.2570 1.0000
3.750 0.4995 0.01188 0.00365 -0.0083 0.2381 1.0000
4.000 0.5254 0.01220 0.00390 -0.0083 0.2226 1.0000
4.250 0.5516 0.01250 0.00416 -0.0083 0.2096 1.0000
4.500 0.5780 0.01282 0.00444 -0.0083 0.1994 1.0000
4.750 0.6044 0.01316 0.00475 -0.0083 0.1911 1.0000
5.000 0.6310 0.01347 0.00509 -0.0083 0.1834 1.0000
5.250 0.6572 0.01384 0.00542 -0.0083 0.1751 1.0000
5.500 0.6840 0.01413 0.00575 -0.0083 0.1662 1.0000
5.750 0.7103 0.01449 0.00610 -0.0083 0.1584 1.0000
6.000 0.7368 0.01482 0.00649 -0.0083 0.1510 1.0000
6.250 0.7630 0.01519 0.00688 -0.0083 0.1443 1.0000
6.500 0.7895 0.01552 0.00727 -0.0083 0.1363 1.0000
6.750 0.8157 0.01587 0.00769 -0.0083 0.1284 1.0000
7.000 0.8416 0.01625 0.00808 -0.0083 0.1191 1.0000
7.250 0.8680 0.01657 0.00849 -0.0083 0.1083 1.0000
7.500 0.8939 0.01695 0.00891 -0.0083 0.0954 1.0000
7.750 0.9191 0.01744 0.00939 -0.0083 0.0807 1.0000
8.000 0.9436 0.01805 0.00999 -0.0081 0.0663 1.0000
8.250 0.9673 0.01881 0.01074 -0.0079 0.0554 1.0000
8.500 0.9901 0.01970 0.01163 -0.0076 0.0469 1.0000
8.750 1.0135 0.02047 0.01252 -0.0073 0.0413 1.0000
9.000 1.0350 0.02149 0.01360 -0.0069 0.0363 1.0000
9.250 1.0575 0.02231 0.01457 -0.0065 0.0325 1.0000
9.500 1.0782 0.02333 0.01567 -0.0060 0.0295 1.0000
9.750 1.0970 0.02455 0.01701 -0.0052 0.0275 1.0000
10.000 1.1164 0.02565 0.01829 -0.0045 0.0258 1.0000
10.250 1.1346 0.02684 0.01966 -0.0037 0.0243 1.0000
10.500 1.1516 0.02808 0.02103 -0.0029 0.0230 1.0000
10.750 1.1659 0.02952 0.02257 -0.0019 0.0218 1.0000
11.000 1.1777 0.03122 0.02441 -0.0006 0.0208 1.0000
11.250 1.1908 0.03269 0.02610 0.0005 0.0199 1.0000
11.500 1.2006 0.03439 0.02801 0.0019 0.0193 1.0000
11.750 1.2061 0.03616 0.02998 0.0037 0.0187 1.0000
12.000 1.2098 0.03812 0.03213 0.0054 0.0182 1.0000
12.250 1.2118 0.04027 0.03446 0.0068 0.0177 1.0000
12.500 1.2119 0.04265 0.03705 0.0079 0.0174 1.0000
12.750 1.2101 0.04531 0.03990 0.0086 0.0170 1.0000
13.000 1.2067 0.04828 0.04303 0.0089 0.0167 1.0000
13.250 1.2012 0.05168 0.04659 0.0086 0.0164 1.0000
13.500 1.1928 0.05572 0.05079 0.0076 0.0162 1.0000
13.750 1.1813 0.06061 0.05587 0.0057 0.0159 1.0000
14.000 1.1671 0.06647 0.06192 0.0026 0.0158 1.0000
15.000 1.0919 0.09926 0.09549 -0.0187 0.0159 1.0000
15.250 1.0535 0.11310 0.10956 -0.0273 0.0164 1.0000
15.500 0.8791 0.16823 0.16482 -0.0554 0.0184 1.0000
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Polar data table (+)
Polar graphs
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