S9000 (9%) (s9000-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 50,000 Max Cl/Cd: 34.71 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9000-il-50000.txt Download as CSV file: xf-s9000-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4124 0.10163 0.09488 -0.0149 1.0000 0.2395
-8.000 -0.4293 0.10080 0.09420 -0.0156 1.0000 0.2501
-7.750 -0.4199 0.09714 0.09059 -0.0143 1.0000 0.2639
-7.500 -0.4107 0.09356 0.08706 -0.0131 1.0000 0.2772
-7.250 -0.4070 0.09044 0.08402 -0.0118 1.0000 0.2909
-7.000 -0.4021 0.08725 0.08091 -0.0106 1.0000 0.3030
-6.750 -0.4020 0.08447 0.07822 -0.0091 1.0000 0.3157
-6.500 -0.4043 0.08182 0.07569 -0.0072 1.0000 0.3297
-6.250 -0.4065 0.07926 0.07324 -0.0053 1.0000 0.3439
-6.000 -0.4082 0.07669 0.07075 -0.0034 1.0000 0.3613
-5.250 -0.4103 0.05004 0.04317 -0.0423 1.0000 0.1295
-5.000 -0.3916 0.04428 0.03682 -0.0443 1.0000 0.1151
-4.750 -0.3689 0.03939 0.03104 -0.0456 1.0000 0.1065
-4.500 -0.3465 0.03586 0.02697 -0.0454 1.0000 0.1064
-4.250 -0.3244 0.03290 0.02374 -0.0450 1.0000 0.1116
-4.000 -0.2997 0.03025 0.02068 -0.0444 1.0000 0.1166
-3.750 -0.2750 0.02797 0.01804 -0.0437 1.0000 0.1283
-3.500 -0.2498 0.02590 0.01574 -0.0428 1.0000 0.1441
-3.250 -0.2255 0.02413 0.01394 -0.0417 1.0000 0.1715
-3.000 -0.2015 0.02245 0.01237 -0.0405 1.0000 0.2207
-2.750 -0.1776 0.02033 0.01107 -0.0394 1.0000 0.3441
-2.500 -0.1694 0.01809 0.01080 -0.0336 1.0000 0.6415
-2.000 -0.1235 0.01721 0.00986 -0.0276 1.0000 1.0000
-1.750 -0.1033 0.01722 0.00940 -0.0276 1.0000 1.0000
-1.500 -0.0822 0.01734 0.00912 -0.0276 1.0000 1.0000
-1.250 -0.0610 0.01753 0.00897 -0.0275 1.0000 1.0000
-1.000 -0.0399 0.01777 0.00889 -0.0274 1.0000 1.0000
-0.750 -0.0191 0.01807 0.00893 -0.0273 1.0000 1.0000
-0.500 0.0014 0.01842 0.00906 -0.0272 1.0000 1.0000
-0.250 0.0215 0.01882 0.00926 -0.0271 1.0000 1.0000
0.000 0.0412 0.01928 0.00953 -0.0270 1.0000 1.0000
0.250 0.0604 0.01980 0.00990 -0.0269 1.0000 1.0000
0.500 0.0792 0.02039 0.01035 -0.0269 1.0000 1.0000
0.750 0.0976 0.02104 0.01089 -0.0270 1.0000 1.0000
1.000 0.1155 0.02175 0.01150 -0.0271 1.0000 1.0000
1.250 0.1544 0.02287 0.01253 -0.0312 0.9895 1.0000
1.500 0.2138 0.02420 0.01379 -0.0386 0.9692 1.0000
1.750 0.2665 0.02516 0.01471 -0.0445 0.9472 1.0000
2.000 0.3191 0.02598 0.01554 -0.0499 0.9255 1.0000
2.250 0.3716 0.02661 0.01622 -0.0549 0.9035 1.0000
2.500 0.4180 0.02708 0.01675 -0.0585 0.8805 1.0000
2.750 0.4756 0.02724 0.01702 -0.0633 0.8591 1.0000
3.000 0.5197 0.02735 0.01728 -0.0656 0.8347 1.0000
3.250 0.5737 0.02708 0.01716 -0.0688 0.8122 1.0000
3.500 0.6223 0.02666 0.01689 -0.0706 0.7889 1.0000
3.750 0.6611 0.02642 0.01683 -0.0708 0.7635 1.0000
4.000 0.7000 0.02603 0.01657 -0.0706 0.7375 1.0000
4.250 0.7363 0.02563 0.01632 -0.0698 0.7101 1.0000
4.500 0.7687 0.02536 0.01613 -0.0684 0.6809 1.0000
4.750 0.7985 0.02524 0.01606 -0.0667 0.6503 1.0000
5.000 0.8271 0.02522 0.01606 -0.0650 0.6187 1.0000
5.250 0.8555 0.02527 0.01611 -0.0632 0.5867 1.0000
5.500 0.8780 0.02573 0.01659 -0.0612 0.5520 1.0000
5.750 0.9028 0.02610 0.01691 -0.0593 0.5176 1.0000
6.000 0.9256 0.02667 0.01742 -0.0573 0.4826 1.0000
6.250 0.9478 0.02735 0.01808 -0.0554 0.4475 1.0000
6.500 0.9707 0.02811 0.01872 -0.0537 0.4138 1.0000
6.750 0.9906 0.02917 0.01981 -0.0519 0.3802 1.0000
7.000 1.0114 0.03026 0.02083 -0.0502 0.3479 1.0000
7.250 1.0324 0.03146 0.02199 -0.0486 0.3172 1.0000
7.500 1.0527 0.03283 0.02330 -0.0470 0.2881 1.0000
7.750 1.0711 0.03436 0.02487 -0.0453 0.2609 1.0000
8.000 1.0892 0.03635 0.02701 -0.0438 0.2379 1.0000
8.250 1.1099 0.03804 0.02857 -0.0425 0.2156 1.0000
8.500 1.1255 0.04068 0.03154 -0.0408 0.1991 1.0000
8.750 1.1406 0.04338 0.03451 -0.0391 0.1842 1.0000
9.000 1.1536 0.04595 0.03738 -0.0374 0.1698 1.0000
9.250 1.1685 0.04911 0.04071 -0.0360 0.1591 1.0000
9.500 1.1821 0.05184 0.04354 -0.0345 0.1467 1.0000
9.750 1.1735 0.05625 0.04869 -0.0316 0.1421 1.0000
10.000 1.1882 0.05955 0.05198 -0.0305 0.1329 1.0000
10.250 1.1712 0.06436 0.05737 -0.0278 0.1312 1.0000
10.500 1.1511 0.06933 0.06273 -0.0258 0.1303 1.0000
10.750 1.1266 0.07439 0.06803 -0.0241 0.1308 1.0000
11.000 1.1008 0.07962 0.07341 -0.0232 0.1318 1.0000
11.250 1.0764 0.08556 0.07943 -0.0240 0.1328 1.0000
11.500 1.0548 0.09224 0.08617 -0.0260 0.1337 1.0000
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Polar data table (+)
Polar graphs
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