S9032 (9%) (s9032-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 100,000 Max Cl/Cd: 34.21 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9032-il-100000-n5.txt Download as CSV file: xf-s9032-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8009 0.08345 0.07836 -0.0040 1.0000 0.0359
-11.250 -0.8901 0.06185 0.05644 -0.0222 1.0000 0.0324
-11.000 -0.9174 0.05612 0.05047 -0.0249 1.0000 0.0323
-10.750 -0.9352 0.05238 0.04650 -0.0243 1.0000 0.0324
-10.500 -0.9415 0.04956 0.04348 -0.0232 1.0000 0.0332
-10.250 -0.9432 0.04669 0.04033 -0.0221 1.0000 0.0342
-10.000 -0.9418 0.04367 0.03698 -0.0210 1.0000 0.0353
-9.750 -0.9368 0.04060 0.03352 -0.0197 1.0000 0.0364
-9.500 -0.9277 0.03769 0.03018 -0.0185 1.0000 0.0374
-9.250 -0.9148 0.03514 0.02721 -0.0173 1.0000 0.0386
-9.000 -0.8991 0.03284 0.02459 -0.0162 1.0000 0.0397
-8.750 -0.8820 0.03109 0.02278 -0.0153 1.0000 0.0416
-8.500 -0.8631 0.02983 0.02138 -0.0145 1.0000 0.0443
-8.250 -0.8433 0.02838 0.01971 -0.0136 1.0000 0.0473
-8.000 -0.8226 0.02689 0.01792 -0.0126 1.0000 0.0500
-7.750 -0.8031 0.02539 0.01640 -0.0116 1.0000 0.0529
-7.500 -0.7822 0.02428 0.01522 -0.0107 1.0000 0.0569
-7.250 -0.7602 0.02329 0.01404 -0.0098 1.0000 0.0627
-7.000 -0.7394 0.02229 0.01304 -0.0090 1.0000 0.0690
-6.750 -0.7172 0.02137 0.01200 -0.0081 1.0000 0.0762
-6.500 -0.6951 0.02058 0.01119 -0.0073 1.0000 0.0854
-6.250 -0.6730 0.01977 0.01038 -0.0065 1.0000 0.0950
-6.000 -0.6504 0.01904 0.00964 -0.0056 1.0000 0.1069
-5.750 -0.6278 0.01835 0.00893 -0.0048 1.0000 0.1203
-5.500 -0.6049 0.01771 0.00831 -0.0040 1.0000 0.1361
-5.250 -0.5819 0.01710 0.00772 -0.0032 1.0000 0.1537
-5.000 -0.5588 0.01653 0.00718 -0.0024 1.0000 0.1724
-4.750 -0.5359 0.01598 0.00671 -0.0016 1.0000 0.1953
-4.500 -0.5129 0.01547 0.00627 -0.0008 1.0000 0.2213
-4.250 -0.4899 0.01499 0.00589 0.0001 1.0000 0.2503
-4.000 -0.4669 0.01455 0.00556 0.0010 1.0000 0.2824
-3.750 -0.4442 0.01412 0.00527 0.0019 1.0000 0.3182
-3.500 -0.4215 0.01372 0.00499 0.0029 1.0000 0.3556
-3.250 -0.3990 0.01334 0.00477 0.0039 1.0000 0.3935
-3.000 -0.3764 0.01301 0.00457 0.0050 1.0000 0.4325
-2.750 -0.3540 0.01269 0.00441 0.0061 1.0000 0.4726
-2.500 -0.3317 0.01240 0.00428 0.0074 1.0000 0.5144
-2.250 -0.3096 0.01213 0.00419 0.0086 1.0000 0.5580
-2.000 -0.2877 0.01190 0.00414 0.0100 1.0000 0.6020
-1.750 -0.2656 0.01170 0.00411 0.0114 1.0000 0.6450
-1.500 -0.2437 0.01154 0.00409 0.0128 1.0000 0.6865
-1.250 -0.2222 0.01141 0.00412 0.0143 1.0000 0.7283
-1.000 -0.1934 0.01133 0.00420 0.0144 0.9950 0.7732
-0.750 -0.1504 0.01131 0.00431 0.0118 0.9812 0.8221
-0.500 -0.1042 0.01131 0.00441 0.0087 0.9664 0.8660
-0.250 -0.0535 0.01133 0.00447 0.0047 0.9491 0.9010
0.000 0.0000 0.01133 0.00449 0.0000 0.9280 0.9280
0.250 0.0535 0.01133 0.00447 -0.0047 0.9010 0.9491
0.500 0.1042 0.01131 0.00441 -0.0087 0.8661 0.9663
0.750 0.1504 0.01131 0.00431 -0.0119 0.8223 0.9811
1.000 0.1934 0.01133 0.00420 -0.0144 0.7733 0.9949
1.250 0.2224 0.01141 0.00412 -0.0143 0.7280 1.0000
1.500 0.2439 0.01154 0.00409 -0.0128 0.6863 1.0000
1.750 0.2659 0.01170 0.00411 -0.0114 0.6449 1.0000
2.000 0.2879 0.01190 0.00414 -0.0101 0.6018 1.0000
2.250 0.3099 0.01213 0.00419 -0.0087 0.5580 1.0000
2.500 0.3320 0.01240 0.00428 -0.0074 0.5143 1.0000
2.750 0.3543 0.01269 0.00441 -0.0062 0.4723 1.0000
3.000 0.3768 0.01301 0.00457 -0.0051 0.4324 1.0000
3.250 0.3994 0.01334 0.00477 -0.0040 0.3935 1.0000
3.500 0.4219 0.01372 0.00499 -0.0030 0.3555 1.0000
3.750 0.4446 0.01412 0.00527 -0.0020 0.3180 1.0000
4.000 0.4673 0.01455 0.00556 -0.0010 0.2823 1.0000
4.250 0.4902 0.01500 0.00589 -0.0001 0.2500 1.0000
4.500 0.5132 0.01547 0.00627 0.0007 0.2212 1.0000
4.750 0.5361 0.01598 0.00672 0.0015 0.1953 1.0000
5.000 0.5590 0.01653 0.00718 0.0024 0.1722 1.0000
5.250 0.5821 0.01710 0.00772 0.0032 0.1536 1.0000
5.500 0.6051 0.01771 0.00831 0.0040 0.1361 1.0000
5.750 0.6278 0.01835 0.00893 0.0048 0.1202 1.0000
6.000 0.6505 0.01904 0.00964 0.0056 0.1069 1.0000
6.250 0.6730 0.01977 0.01038 0.0065 0.0950 1.0000
6.500 0.6951 0.02057 0.01118 0.0073 0.0853 1.0000
6.750 0.7171 0.02136 0.01200 0.0081 0.0761 1.0000
7.000 0.7392 0.02229 0.01304 0.0090 0.0690 1.0000
7.250 0.7600 0.02328 0.01403 0.0099 0.0627 1.0000
7.500 0.7819 0.02427 0.01521 0.0108 0.0569 1.0000
7.750 0.8028 0.02538 0.01640 0.0117 0.0529 1.0000
8.000 0.8222 0.02688 0.01791 0.0126 0.0500 1.0000
8.250 0.8429 0.02838 0.01970 0.0137 0.0473 1.0000
8.500 0.8626 0.02981 0.02136 0.0146 0.0443 1.0000
8.750 0.8815 0.03106 0.02275 0.0154 0.0416 1.0000
9.000 0.8986 0.03281 0.02457 0.0163 0.0398 1.0000
9.250 0.9141 0.03511 0.02718 0.0174 0.0385 1.0000
9.500 0.9271 0.03765 0.03014 0.0186 0.0374 1.0000
9.750 0.9362 0.04055 0.03346 0.0199 0.0364 1.0000
10.000 0.9411 0.04362 0.03692 0.0211 0.0354 1.0000
10.250 0.9424 0.04667 0.04032 0.0223 0.0343 1.0000
10.500 0.9406 0.04954 0.04346 0.0234 0.0332 1.0000
10.750 0.9332 0.05248 0.04661 0.0245 0.0325 1.0000
11.000 0.9169 0.05603 0.05037 0.0251 0.0323 1.0000
11.250 0.8884 0.06197 0.05656 0.0222 0.0325 1.0000
11.500 0.8011 0.08325 0.07816 0.0043 0.0359 1.0000
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Polar data table (+)
Polar graphs
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