S9032 (9%) (s9032-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 200,000 Max Cl/Cd: 43.16 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9032-il-200000.txt Download as CSV file: xf-s9032-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S9032 (9%)
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8257 0.07565 0.07196 -0.0134 1.0000 0.0390
-11.250 -0.8556 0.06662 0.06285 -0.0202 1.0000 0.0383
-11.000 -0.8838 0.06007 0.05615 -0.0247 1.0000 0.0379
-10.750 -0.9086 0.05540 0.05131 -0.0256 1.0000 0.0375
-10.500 -0.9306 0.05134 0.04702 -0.0240 1.0000 0.0373
-10.250 -0.9431 0.04724 0.04257 -0.0227 1.0000 0.0377
-10.000 -0.9469 0.04369 0.03863 -0.0212 1.0000 0.0383
-9.750 -0.9419 0.04145 0.03597 -0.0196 1.0000 0.0392
-9.500 -0.9396 0.03725 0.03130 -0.0180 1.0000 0.0398
-9.250 -0.9319 0.03297 0.02663 -0.0167 1.0000 0.0406
-9.000 -0.9162 0.03041 0.02387 -0.0157 1.0000 0.0417
-8.750 -0.8973 0.02885 0.02218 -0.0148 1.0000 0.0434
-8.500 -0.8774 0.02745 0.02059 -0.0139 1.0000 0.0455
-8.250 -0.8569 0.02577 0.01863 -0.0128 1.0000 0.0473
-8.000 -0.8354 0.02421 0.01682 -0.0118 1.0000 0.0491
-7.750 -0.8133 0.02277 0.01513 -0.0108 1.0000 0.0508
-7.500 -0.7926 0.02079 0.01315 -0.0099 1.0000 0.0542
-7.250 -0.7698 0.01994 0.01224 -0.0091 1.0000 0.0586
-6.750 -0.7252 0.01786 0.01005 -0.0072 1.0000 0.0705
-6.500 -0.7030 0.01685 0.00902 -0.0062 1.0000 0.0786
-6.250 -0.6791 0.01633 0.00840 -0.0054 1.0000 0.0883
-6.000 -0.6567 0.01556 0.00769 -0.0045 1.0000 0.1000
-5.750 -0.6339 0.01489 0.00706 -0.0036 1.0000 0.1127
-5.500 -0.6108 0.01430 0.00648 -0.0028 1.0000 0.1280
-5.250 -0.5881 0.01368 0.00596 -0.0019 1.0000 0.1461
-5.000 -0.5652 0.01313 0.00550 -0.0010 1.0000 0.1682
-4.750 -0.5425 0.01258 0.00509 -0.0001 1.0000 0.1941
-4.500 -0.5197 0.01208 0.00470 0.0008 1.0000 0.2236
-4.250 -0.4968 0.01162 0.00436 0.0017 1.0000 0.2560
-4.000 -0.4741 0.01118 0.00409 0.0027 1.0000 0.2905
-3.750 -0.4512 0.01080 0.00385 0.0036 1.0000 0.3299
-3.500 -0.4286 0.01042 0.00364 0.0046 1.0000 0.3708
-3.250 -0.4061 0.01008 0.00347 0.0057 1.0000 0.4134
-3.000 -0.3838 0.00976 0.00334 0.0068 1.0000 0.4585
-2.750 -0.3618 0.00946 0.00324 0.0080 1.0000 0.5052
-2.500 -0.3400 0.00919 0.00316 0.0093 1.0000 0.5513
-2.250 -0.3185 0.00896 0.00312 0.0107 1.0000 0.5959
-2.000 -0.2973 0.00876 0.00310 0.0122 1.0000 0.6395
-1.750 -0.2767 0.00859 0.00311 0.0138 1.0000 0.6830
-1.500 -0.2569 0.00846 0.00316 0.0156 1.0000 0.7269
-1.250 -0.2382 0.00836 0.00326 0.0177 1.0000 0.7729
-1.000 -0.2185 0.00831 0.00341 0.0195 0.9993 0.8230
-0.750 -0.1705 0.00834 0.00358 0.0160 0.9885 0.8733
-0.500 -0.1164 0.00843 0.00373 0.0113 0.9798 0.9135
-0.250 -0.0590 0.00850 0.00383 0.0058 0.9711 0.9413
0.000 0.0000 0.00853 0.00386 0.0000 0.9595 0.9596
0.250 0.0591 0.00850 0.00383 -0.0058 0.9412 0.9711
0.500 0.1166 0.00843 0.00373 -0.0113 0.9135 0.9799
0.750 0.1705 0.00834 0.00358 -0.0160 0.8736 0.9884
1.000 0.2186 0.00832 0.00341 -0.0195 0.8232 0.9992
1.250 0.2385 0.00836 0.00326 -0.0177 0.7731 1.0000
1.500 0.2573 0.00846 0.00316 -0.0157 0.7272 1.0000
1.750 0.2770 0.00859 0.00312 -0.0139 0.6826 1.0000
2.000 0.2977 0.00876 0.00310 -0.0123 0.6393 1.0000
2.250 0.3189 0.00896 0.00312 -0.0108 0.5958 1.0000
2.500 0.3404 0.00919 0.00316 -0.0094 0.5512 1.0000
2.750 0.3622 0.00946 0.00324 -0.0081 0.5050 1.0000
3.000 0.3842 0.00976 0.00334 -0.0069 0.4584 1.0000
3.250 0.4065 0.01008 0.00347 -0.0058 0.4131 1.0000
3.500 0.4290 0.01042 0.00364 -0.0047 0.3705 1.0000
3.750 0.4516 0.01080 0.00385 -0.0037 0.3297 1.0000
4.000 0.4745 0.01118 0.00409 -0.0028 0.2903 1.0000
4.250 0.4972 0.01162 0.00437 -0.0018 0.2558 1.0000
4.500 0.5201 0.01208 0.00470 -0.0009 0.2235 1.0000
4.750 0.5429 0.01258 0.00509 0.0000 0.1939 1.0000
5.000 0.5655 0.01313 0.00551 0.0009 0.1681 1.0000
5.250 0.5884 0.01368 0.00596 0.0018 0.1460 1.0000
5.500 0.6111 0.01430 0.00648 0.0027 0.1279 1.0000
5.750 0.6341 0.01489 0.00706 0.0036 0.1127 1.0000
6.000 0.6568 0.01556 0.00769 0.0045 0.1000 1.0000
6.250 0.6791 0.01634 0.00840 0.0054 0.0883 1.0000
6.500 0.7030 0.01685 0.00901 0.0062 0.0786 1.0000
6.750 0.7251 0.01785 0.01005 0.0072 0.0705 1.0000
7.000 0.7471 0.01884 0.01099 0.0081 0.0638 1.0000
7.250 0.7696 0.01992 0.01223 0.0091 0.0586 1.0000
7.500 0.7924 0.02079 0.01315 0.0099 0.0542 1.0000
7.750 0.8131 0.02271 0.01507 0.0109 0.0509 1.0000
8.000 0.8351 0.02421 0.01681 0.0119 0.0491 1.0000
8.250 0.8566 0.02576 0.01863 0.0129 0.0474 1.0000
8.500 0.8769 0.02746 0.02058 0.0139 0.0456 1.0000
8.750 0.8968 0.02886 0.02218 0.0149 0.0434 1.0000
9.000 0.9158 0.03039 0.02384 0.0158 0.0417 1.0000
9.250 0.9313 0.03297 0.02663 0.0168 0.0405 1.0000
9.500 0.9395 0.03712 0.03116 0.0181 0.0398 1.0000
9.750 0.9412 0.04147 0.03598 0.0197 0.0392 1.0000
10.000 0.9460 0.04377 0.03869 0.0213 0.0384 1.0000
10.250 0.9428 0.04714 0.04247 0.0228 0.0377 1.0000
10.500 0.9303 0.05125 0.04692 0.0242 0.0374 1.0000
10.750 0.9084 0.05532 0.05122 0.0257 0.0376 1.0000
11.000 0.8833 0.05994 0.05602 0.0249 0.0378 1.0000
11.250 0.8559 0.06645 0.06267 0.0205 0.0384 1.0000
11.500 0.8249 0.07563 0.07194 0.0132 0.0390 1.0000
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Polar data table (+)
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