S9032 (9%) (s9032-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 200,000 Max Cl/Cd: 44.92 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9032-il-200000-n5.txt Download as CSV file: xf-s9032-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7580 0.12903 0.12531 0.0232 1.0000 0.0210
-13.250 -0.9177 0.08330 0.07954 -0.0026 1.0000 0.0189
-13.000 -1.0043 0.06105 0.05672 -0.0195 1.0000 0.0173
-12.750 -1.0152 0.05580 0.05135 -0.0234 1.0000 0.0176
-12.500 -1.0289 0.05078 0.04614 -0.0266 1.0000 0.0177
-12.250 -1.0396 0.04690 0.04209 -0.0282 1.0000 0.0179
-12.000 -1.0454 0.04421 0.03927 -0.0284 1.0000 0.0183
-11.750 -1.0523 0.04167 0.03655 -0.0273 1.0000 0.0186
-11.500 -1.0561 0.03961 0.03431 -0.0253 1.0000 0.0191
-11.250 -1.0548 0.03750 0.03197 -0.0236 1.0000 0.0196
-11.000 -1.0487 0.03553 0.02976 -0.0222 1.0000 0.0204
-10.750 -1.0393 0.03370 0.02765 -0.0208 1.0000 0.0212
-10.500 -1.0270 0.03203 0.02571 -0.0196 1.0000 0.0219
-10.250 -1.0142 0.03019 0.02363 -0.0183 1.0000 0.0226
-10.000 -1.0005 0.02835 0.02163 -0.0171 1.0000 0.0234
-9.750 -0.9836 0.02703 0.02019 -0.0161 1.0000 0.0242
-9.500 -0.9650 0.02596 0.01901 -0.0152 1.0000 0.0253
-9.250 -0.9454 0.02494 0.01786 -0.0143 1.0000 0.0267
-9.000 -0.9255 0.02386 0.01662 -0.0133 1.0000 0.0279
-8.750 -0.9052 0.02277 0.01537 -0.0124 1.0000 0.0291
-8.500 -0.8842 0.02178 0.01423 -0.0114 1.0000 0.0300
-8.250 -0.8651 0.02056 0.01294 -0.0104 1.0000 0.0317
-8.000 -0.8436 0.01974 0.01205 -0.0096 1.0000 0.0336
-7.750 -0.8212 0.01900 0.01122 -0.0088 1.0000 0.0361
-7.500 -0.7982 0.01838 0.01047 -0.0080 1.0000 0.0391
-7.250 -0.7765 0.01754 0.00964 -0.0072 1.0000 0.0431
-7.000 -0.7534 0.01693 0.00896 -0.0064 1.0000 0.0477
-6.750 -0.7303 0.01631 0.00825 -0.0056 1.0000 0.0525
-6.500 -0.7070 0.01574 0.00768 -0.0049 1.0000 0.0587
-6.250 -0.6834 0.01523 0.00714 -0.0042 1.0000 0.0658
-6.000 -0.6594 0.01479 0.00667 -0.0035 1.0000 0.0745
-5.750 -0.6358 0.01431 0.00623 -0.0028 1.0000 0.0846
-5.500 -0.6121 0.01387 0.00579 -0.0021 1.0000 0.0961
-5.250 -0.5883 0.01344 0.00540 -0.0013 1.0000 0.1096
-5.000 -0.5646 0.01304 0.00504 -0.0006 1.0000 0.1250
-4.750 -0.5409 0.01266 0.00471 0.0002 1.0000 0.1427
-4.500 -0.5172 0.01229 0.00439 0.0010 1.0000 0.1607
-4.250 -0.4936 0.01194 0.00411 0.0018 1.0000 0.1796
-4.000 -0.4698 0.01163 0.00385 0.0026 1.0000 0.2007
-3.750 -0.4464 0.01130 0.00363 0.0034 1.0000 0.2264
-3.500 -0.4229 0.01099 0.00341 0.0042 1.0000 0.2536
-3.250 -0.3996 0.01069 0.00324 0.0050 1.0000 0.2832
-3.000 -0.3765 0.01040 0.00309 0.0059 1.0000 0.3166
-2.750 -0.3536 0.01013 0.00296 0.0068 1.0000 0.3522
-2.500 -0.3308 0.00988 0.00285 0.0078 1.0000 0.3874
-2.250 -0.2964 0.00965 0.00278 0.0063 0.9934 0.4270
-2.000 -0.2586 0.00941 0.00271 0.0041 0.9830 0.4687
-1.750 -0.2230 0.00918 0.00265 0.0025 0.9705 0.5131
-1.500 -0.1883 0.00894 0.00261 0.0013 0.9555 0.5594
-1.250 -0.1537 0.00873 0.00257 0.0001 0.9369 0.6039
-1.000 -0.1180 0.00855 0.00252 -0.0012 0.9144 0.6435
-0.750 -0.0839 0.00840 0.00248 -0.0020 0.8874 0.6803
-0.500 -0.0532 0.00829 0.00244 -0.0019 0.8569 0.7165
-0.250 -0.0257 0.00821 0.00242 -0.0012 0.8246 0.7534
0.000 0.0000 0.00818 0.00242 0.0000 0.7900 0.7900
0.250 0.0257 0.00821 0.00242 0.0012 0.7533 0.8246
0.500 0.0532 0.00829 0.00244 0.0019 0.7164 0.8570
0.750 0.0840 0.00840 0.00248 0.0019 0.6803 0.8874
1.000 0.1180 0.00855 0.00252 0.0011 0.6434 0.9144
1.250 0.1538 0.00873 0.00257 -0.0001 0.6039 0.9368
1.500 0.1884 0.00894 0.00261 -0.0013 0.5596 0.9554
1.750 0.2230 0.00918 0.00265 -0.0026 0.5130 0.9704
2.000 0.2586 0.00942 0.00272 -0.0041 0.4685 0.9829
2.250 0.2964 0.00965 0.00278 -0.0063 0.4271 0.9932
2.500 0.3312 0.00988 0.00285 -0.0078 0.3873 1.0000
2.750 0.3540 0.01013 0.00297 -0.0069 0.3521 1.0000
3.000 0.3769 0.01041 0.00309 -0.0060 0.3165 1.0000
3.250 0.4000 0.01070 0.00324 -0.0051 0.2829 1.0000
3.500 0.4233 0.01099 0.00342 -0.0043 0.2534 1.0000
3.750 0.4468 0.01130 0.00363 -0.0034 0.2263 1.0000
4.000 0.4703 0.01163 0.00386 -0.0026 0.2006 1.0000
4.250 0.4940 0.01195 0.00411 -0.0018 0.1795 1.0000
4.500 0.5176 0.01229 0.00439 -0.0011 0.1607 1.0000
4.750 0.5412 0.01266 0.00472 -0.0003 0.1426 1.0000
5.000 0.5650 0.01304 0.00505 0.0005 0.1249 1.0000
5.250 0.5887 0.01344 0.00541 0.0013 0.1096 1.0000
5.500 0.6123 0.01387 0.00579 0.0020 0.0960 1.0000
5.750 0.6360 0.01431 0.00623 0.0027 0.0846 1.0000
6.000 0.6596 0.01479 0.00668 0.0035 0.0745 1.0000
6.250 0.6835 0.01523 0.00715 0.0042 0.0659 1.0000
6.500 0.7070 0.01574 0.00768 0.0049 0.0587 1.0000
6.750 0.7303 0.01631 0.00825 0.0056 0.0524 1.0000
7.000 0.7533 0.01693 0.00896 0.0064 0.0477 1.0000
7.250 0.7764 0.01754 0.00963 0.0072 0.0431 1.0000
7.500 0.7979 0.01838 0.01047 0.0081 0.0391 1.0000
7.750 0.8209 0.01901 0.01123 0.0088 0.0361 1.0000
8.000 0.8432 0.01973 0.01204 0.0096 0.0336 1.0000
8.250 0.8647 0.02056 0.01293 0.0105 0.0317 1.0000
8.500 0.8837 0.02177 0.01422 0.0115 0.0300 1.0000
8.750 0.9046 0.02276 0.01536 0.0125 0.0290 1.0000
9.000 0.9248 0.02385 0.01661 0.0135 0.0280 1.0000
9.250 0.9446 0.02493 0.01785 0.0144 0.0267 1.0000
9.500 0.9641 0.02595 0.01900 0.0153 0.0254 1.0000
9.750 0.9828 0.02701 0.02017 0.0163 0.0243 1.0000
10.000 0.9996 0.02832 0.02161 0.0173 0.0235 1.0000
10.250 1.0135 0.03010 0.02355 0.0185 0.0227 1.0000
10.500 1.0259 0.03201 0.02569 0.0198 0.0220 1.0000
10.750 1.0382 0.03366 0.02761 0.0210 0.0212 1.0000
11.000 1.0478 0.03543 0.02965 0.0224 0.0203 1.0000
11.250 1.0536 0.03745 0.03191 0.0239 0.0197 1.0000
11.500 1.0548 0.03954 0.03423 0.0256 0.0191 1.0000
11.750 1.0510 0.04162 0.03649 0.0276 0.0187 1.0000
12.000 1.0444 0.04412 0.03917 0.0287 0.0183 1.0000
12.250 1.0385 0.04684 0.04203 0.0285 0.0179 1.0000
12.500 1.0274 0.05076 0.04613 0.0268 0.0177 1.0000
12.750 1.0161 0.05543 0.05095 0.0238 0.0175 1.0000
13.000 0.9911 0.06334 0.05912 0.0179 0.0177 1.0000
13.250 0.9200 0.08256 0.07879 0.0033 0.0188 1.0000
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Polar data table (+)
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