S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 50,000 Max Cl/Cd: 27.63 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8035-il-50000-n5.txt Download as CSV file: xf-s8035-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8035 for RC aerobatic 14% thick
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7617 0.09151 0.08343 -0.0287 1.0000 0.1015
-13.000 -0.8647 0.07115 0.06276 -0.0411 1.0000 0.0979
-12.750 -0.8824 0.06614 0.05762 -0.0427 1.0000 0.0999
-12.500 -0.9017 0.06138 0.05267 -0.0438 1.0000 0.1018
-12.250 -0.9200 0.05714 0.04820 -0.0440 1.0000 0.1041
-12.000 -0.9376 0.05334 0.04408 -0.0432 1.0000 0.1065
-11.750 -0.9349 0.05128 0.04200 -0.0420 1.0000 0.1102
-11.500 -0.9332 0.04950 0.04018 -0.0406 1.0000 0.1145
-11.250 -0.9392 0.04717 0.03761 -0.0384 1.0000 0.1188
-11.000 -0.9382 0.04527 0.03557 -0.0362 1.0000 0.1235
-10.750 -0.9326 0.04394 0.03423 -0.0341 1.0000 0.1287
-10.500 -0.9336 0.04206 0.03207 -0.0314 1.0000 0.1347
-10.250 -0.9221 0.04086 0.03096 -0.0297 1.0000 0.1409
-10.000 -0.9158 0.03930 0.02918 -0.0275 1.0000 0.1481
-9.750 -0.9044 0.03813 0.02805 -0.0256 1.0000 0.1555
-9.500 -0.8961 0.03672 0.02639 -0.0234 1.0000 0.1642
-9.250 -0.8822 0.03569 0.02545 -0.0217 1.0000 0.1722
-9.000 -0.8709 0.03453 0.02417 -0.0197 1.0000 0.1819
-8.750 -0.8585 0.03349 0.02307 -0.0176 1.0000 0.1921
-8.500 -0.8447 0.03256 0.02217 -0.0157 1.0000 0.2024
-8.250 -0.8316 0.03162 0.02119 -0.0137 1.0000 0.2139
-8.000 -0.8182 0.03072 0.02020 -0.0116 1.0000 0.2263
-7.750 -0.8049 0.02989 0.01931 -0.0095 1.0000 0.2398
-7.500 -0.7904 0.02914 0.01861 -0.0075 1.0000 0.2531
-7.250 -0.7757 0.02842 0.01791 -0.0055 1.0000 0.2672
-7.000 -0.7610 0.02774 0.01725 -0.0034 1.0000 0.2821
-6.750 -0.7458 0.02708 0.01659 -0.0014 1.0000 0.2974
-6.500 -0.7307 0.02647 0.01599 0.0007 1.0000 0.3137
-6.250 -0.7154 0.02589 0.01542 0.0028 1.0000 0.3303
-6.000 -0.7001 0.02535 0.01488 0.0048 1.0000 0.3476
-5.750 -0.6848 0.02485 0.01440 0.0069 1.0000 0.3654
-5.500 -0.6691 0.02441 0.01400 0.0090 1.0000 0.3828
-5.250 -0.6537 0.02400 0.01365 0.0112 1.0000 0.4011
-5.000 -0.6385 0.02363 0.01333 0.0133 1.0000 0.4199
-4.750 -0.6234 0.02329 0.01300 0.0155 1.0000 0.4394
-4.500 -0.6087 0.02297 0.01269 0.0177 1.0000 0.4597
-4.250 -0.5932 0.02272 0.01251 0.0198 1.0000 0.4789
-4.000 -0.5777 0.02250 0.01234 0.0219 1.0000 0.4986
-3.750 -0.5623 0.02230 0.01217 0.0240 1.0000 0.5189
-3.500 -0.5472 0.02214 0.01201 0.0260 1.0000 0.5400
-3.250 -0.5310 0.02205 0.01199 0.0279 1.0000 0.5599
-3.000 -0.5016 0.02204 0.01202 0.0273 0.9939 0.5842
-2.750 -0.4610 0.02210 0.01212 0.0247 0.9824 0.6101
-2.500 -0.4222 0.02211 0.01214 0.0225 0.9701 0.6364
-2.250 -0.3835 0.02216 0.01224 0.0206 0.9577 0.6600
-2.000 -0.3461 0.02217 0.01225 0.0188 0.9449 0.6845
-1.750 -0.3066 0.02224 0.01236 0.0169 0.9325 0.7062
-1.500 -0.2663 0.02228 0.01241 0.0149 0.9205 0.7289
-1.250 -0.2203 0.02232 0.01248 0.0120 0.9099 0.7509
-1.000 -0.1785 0.02238 0.01256 0.0099 0.8969 0.7710
-0.750 -0.1353 0.02242 0.01262 0.0077 0.8838 0.7907
-0.500 -0.0915 0.02244 0.01264 0.0053 0.8704 0.8094
-0.250 -0.0464 0.02244 0.01265 0.0027 0.8567 0.8267
0.000 0.0000 0.02245 0.01265 0.0000 0.8423 0.8423
0.250 0.0464 0.02245 0.01265 -0.0028 0.8267 0.8567
0.500 0.0915 0.02244 0.01264 -0.0053 0.8095 0.8704
0.750 0.1353 0.02242 0.01262 -0.0077 0.7907 0.8838
1.000 0.1784 0.02238 0.01256 -0.0099 0.7710 0.8969
1.250 0.2202 0.02232 0.01248 -0.0120 0.7510 0.9099
1.500 0.2663 0.02228 0.01241 -0.0149 0.7291 0.9205
1.750 0.3066 0.02224 0.01236 -0.0170 0.7064 0.9325
2.000 0.3460 0.02217 0.01225 -0.0188 0.6845 0.9449
2.250 0.3834 0.02216 0.01224 -0.0206 0.6600 0.9577
2.500 0.4222 0.02211 0.01214 -0.0225 0.6365 0.9701
2.750 0.4610 0.02210 0.01212 -0.0247 0.6101 0.9824
3.000 0.5017 0.02204 0.01201 -0.0273 0.5842 0.9939
3.250 0.5310 0.02204 0.01199 -0.0279 0.5599 1.0000
3.500 0.5471 0.02213 0.01201 -0.0260 0.5400 1.0000
3.750 0.5623 0.02230 0.01217 -0.0240 0.5189 1.0000
4.000 0.5776 0.02250 0.01234 -0.0219 0.4986 1.0000
4.250 0.5932 0.02272 0.01251 -0.0198 0.4790 1.0000
4.500 0.6087 0.02297 0.01269 -0.0177 0.4597 1.0000
4.750 0.6234 0.02328 0.01299 -0.0155 0.4394 1.0000
5.000 0.6385 0.02363 0.01332 -0.0133 0.4199 1.0000
5.250 0.6537 0.02400 0.01365 -0.0112 0.4011 1.0000
5.500 0.6692 0.02441 0.01400 -0.0090 0.3829 1.0000
5.750 0.6848 0.02485 0.01439 -0.0069 0.3654 1.0000
6.000 0.7001 0.02535 0.01488 -0.0048 0.3476 1.0000
6.250 0.7154 0.02589 0.01541 -0.0028 0.3303 1.0000
6.500 0.7307 0.02647 0.01598 -0.0007 0.3137 1.0000
6.750 0.7458 0.02708 0.01658 0.0014 0.2974 1.0000
7.000 0.7610 0.02774 0.01724 0.0034 0.2821 1.0000
7.250 0.7757 0.02842 0.01791 0.0055 0.2672 1.0000
7.500 0.7904 0.02914 0.01861 0.0075 0.2531 1.0000
7.750 0.8049 0.02989 0.01931 0.0095 0.2398 1.0000
8.000 0.8182 0.03071 0.02019 0.0116 0.2263 1.0000
8.250 0.8317 0.03162 0.02119 0.0137 0.2139 1.0000
8.500 0.8448 0.03256 0.02217 0.0157 0.2024 1.0000
8.750 0.8586 0.03349 0.02307 0.0176 0.1922 1.0000
9.000 0.8708 0.03452 0.02416 0.0197 0.1818 1.0000
9.250 0.8823 0.03569 0.02544 0.0217 0.1722 1.0000
9.500 0.8963 0.03672 0.02639 0.0234 0.1641 1.0000
9.750 0.9046 0.03813 0.02805 0.0256 0.1555 1.0000
10.000 0.9161 0.03930 0.02918 0.0274 0.1482 1.0000
10.250 0.9222 0.04086 0.03096 0.0297 0.1409 1.0000
10.500 0.9340 0.04207 0.03208 0.0313 0.1347 1.0000
10.750 0.9329 0.04393 0.03423 0.0341 0.1287 1.0000
11.000 0.9386 0.04526 0.03555 0.0362 0.1234 1.0000
11.250 0.9398 0.04716 0.03760 0.0383 0.1188 1.0000
11.500 0.9337 0.04950 0.04018 0.0405 0.1145 1.0000
11.750 0.9355 0.05128 0.04200 0.0420 0.1102 1.0000
12.000 0.9382 0.05334 0.04408 0.0431 0.1065 1.0000
12.250 0.9204 0.05714 0.04820 0.0439 0.1040 1.0000
12.500 0.9023 0.06138 0.05267 0.0437 0.1018 1.0000
12.750 0.8835 0.06608 0.05756 0.0427 0.0998 1.0000
13.000 0.8653 0.07117 0.06278 0.0409 0.0980 1.0000
13.250 0.7616 0.09171 0.08364 0.0284 0.1015 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8035 for RC aerobatic 14% thick (s8035-il)