S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 100,000 Max Cl/Cd: 38.68 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8035-il-100000.txt Download as CSV file: xf-s8035-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9187 0.07859 0.07269 -0.0444 1.0000 0.0818
-14.000 -0.9527 0.07159 0.06551 -0.0475 1.0000 0.0814
-13.750 -0.9847 0.06582 0.05952 -0.0492 1.0000 0.0813
-13.500 -1.0143 0.06111 0.05458 -0.0493 1.0000 0.0813
-13.250 -1.0418 0.05729 0.05048 -0.0480 1.0000 0.0816
-13.000 -1.0656 0.05423 0.04714 -0.0454 1.0000 0.0819
-12.750 -1.0492 0.05127 0.04430 -0.0453 1.0000 0.0849
-12.500 -1.0483 0.04956 0.04254 -0.0433 1.0000 0.0876
-12.250 -1.0572 0.04743 0.04022 -0.0402 1.0000 0.0897
-12.000 -1.0696 0.04535 0.03784 -0.0361 1.0000 0.0919
-11.750 -1.0804 0.04328 0.03536 -0.0320 1.0000 0.0940
-11.500 -1.0635 0.04097 0.03314 -0.0313 1.0000 0.0982
-11.250 -1.0562 0.03955 0.03162 -0.0290 1.0000 0.1026
-11.000 -1.0567 0.03792 0.02961 -0.0255 1.0000 0.1069
-10.750 -1.0384 0.03619 0.02800 -0.0246 1.0000 0.1125
-10.500 -1.0301 0.03495 0.02657 -0.0221 1.0000 0.1185
-10.250 -1.0168 0.03339 0.02494 -0.0203 1.0000 0.1247
-10.000 -1.0038 0.03236 0.02383 -0.0182 1.0000 0.1318
-9.750 -0.9898 0.03105 0.02248 -0.0163 1.0000 0.1392
-9.500 -0.9768 0.03010 0.02141 -0.0141 1.0000 0.1473
-9.250 -0.9601 0.02899 0.02037 -0.0125 1.0000 0.1559
-9.000 -0.9482 0.02799 0.01914 -0.0100 1.0000 0.1652
-8.750 -0.9303 0.02708 0.01836 -0.0085 1.0000 0.1753
-8.500 -0.9139 0.02612 0.01743 -0.0067 1.0000 0.1858
-8.250 -0.8986 0.02522 0.01647 -0.0047 1.0000 0.1972
-8.000 -0.8840 0.02449 0.01565 -0.0025 1.0000 0.2097
-7.750 -0.8668 0.02373 0.01499 -0.0007 1.0000 0.2224
-7.500 -0.8501 0.02299 0.01432 0.0012 1.0000 0.2357
-7.250 -0.8340 0.02232 0.01369 0.0032 1.0000 0.2498
-7.000 -0.8181 0.02168 0.01310 0.0052 1.0000 0.2648
-6.750 -0.8024 0.02110 0.01256 0.0073 1.0000 0.2807
-6.500 -0.7871 0.02056 0.01206 0.0095 1.0000 0.2973
-6.250 -0.7721 0.02008 0.01161 0.0117 1.0000 0.3150
-6.000 -0.7577 0.01963 0.01118 0.0141 1.0000 0.3335
-5.750 -0.7422 0.01919 0.01086 0.0162 1.0000 0.3515
-5.500 -0.7271 0.01882 0.01058 0.0184 1.0000 0.3702
-5.250 -0.7120 0.01848 0.01031 0.0206 1.0000 0.3896
-5.000 -0.6973 0.01818 0.01005 0.0228 1.0000 0.4100
-4.750 -0.6821 0.01791 0.00985 0.0249 1.0000 0.4302
-4.500 -0.6663 0.01769 0.00974 0.0270 1.0000 0.4502
-4.250 -0.6509 0.01751 0.00962 0.0290 1.0000 0.4713
-4.000 -0.6357 0.01736 0.00952 0.0310 1.0000 0.4931
-3.750 -0.6199 0.01724 0.00952 0.0329 1.0000 0.5137
-3.500 -0.6047 0.01716 0.00949 0.0349 1.0000 0.5359
-3.250 -0.5895 0.01710 0.00951 0.0368 1.0000 0.5582
-3.000 -0.5597 0.01722 0.00974 0.0360 0.9951 0.5847
-2.750 -0.5145 0.01744 0.01007 0.0324 0.9844 0.6138
-2.500 -0.4710 0.01759 0.01031 0.0293 0.9730 0.6417
-2.250 -0.4288 0.01768 0.01045 0.0265 0.9613 0.6694
-2.000 -0.3860 0.01776 0.01064 0.0239 0.9498 0.6951
-1.750 -0.3397 0.01781 0.01077 0.0208 0.9393 0.7209
-1.500 -0.2965 0.01782 0.01084 0.0184 0.9275 0.7461
-1.250 -0.2553 0.01785 0.01094 0.0166 0.9153 0.7686
-1.000 -0.2071 0.01787 0.01101 0.0136 0.9053 0.7905
-0.750 -0.1551 0.01782 0.01099 0.0099 0.8961 0.8119
-0.500 -0.1104 0.01782 0.01102 0.0077 0.8839 0.8305
-0.250 -0.0569 0.01780 0.01102 0.0041 0.8731 0.8471
0.000 0.0000 0.01774 0.01095 0.0000 0.8621 0.8621
0.250 0.0569 0.01780 0.01102 -0.0041 0.8470 0.8730
0.500 0.1103 0.01782 0.01102 -0.0077 0.8306 0.8839
0.750 0.1554 0.01782 0.01099 -0.0099 0.8121 0.8961
1.000 0.2070 0.01787 0.01101 -0.0136 0.7905 0.9053
1.250 0.2552 0.01785 0.01094 -0.0166 0.7687 0.9153
1.500 0.2965 0.01782 0.01084 -0.0184 0.7461 0.9275
1.750 0.3396 0.01781 0.01077 -0.0208 0.7209 0.9393
2.000 0.3861 0.01776 0.01064 -0.0240 0.6951 0.9498
2.250 0.4290 0.01767 0.01046 -0.0266 0.6694 0.9614
2.500 0.4711 0.01758 0.01031 -0.0293 0.6417 0.9731
2.750 0.5145 0.01744 0.01007 -0.0324 0.6139 0.9844
3.000 0.5598 0.01721 0.00973 -0.0360 0.5847 0.9951
3.250 0.5895 0.01709 0.00951 -0.0368 0.5583 1.0000
3.500 0.6047 0.01716 0.00949 -0.0349 0.5362 1.0000
3.750 0.6199 0.01724 0.00952 -0.0329 0.5138 1.0000
4.000 0.6356 0.01736 0.00951 -0.0310 0.4931 1.0000
4.250 0.6509 0.01751 0.00962 -0.0290 0.4714 1.0000
4.500 0.6663 0.01769 0.00973 -0.0270 0.4502 1.0000
4.750 0.6821 0.01791 0.00985 -0.0249 0.4303 1.0000
5.000 0.6973 0.01818 0.01005 -0.0228 0.4100 1.0000
5.250 0.7120 0.01848 0.01031 -0.0206 0.3896 1.0000
5.500 0.7271 0.01882 0.01058 -0.0184 0.3703 1.0000
5.750 0.7422 0.01919 0.01086 -0.0162 0.3516 1.0000
6.000 0.7577 0.01963 0.01118 -0.0141 0.3335 1.0000
6.250 0.7721 0.02007 0.01161 -0.0117 0.3150 1.0000
6.500 0.7871 0.02056 0.01206 -0.0095 0.2974 1.0000
6.750 0.8024 0.02109 0.01256 -0.0073 0.2807 1.0000
7.000 0.8180 0.02167 0.01309 -0.0052 0.2648 1.0000
7.250 0.8340 0.02231 0.01368 -0.0032 0.2498 1.0000
7.500 0.8501 0.02299 0.01432 -0.0012 0.2357 1.0000
7.750 0.8668 0.02373 0.01499 0.0007 0.2224 1.0000
8.000 0.8840 0.02449 0.01565 0.0025 0.2097 1.0000
8.250 0.8986 0.02522 0.01647 0.0047 0.1972 1.0000
8.500 0.9139 0.02612 0.01743 0.0067 0.1858 1.0000
8.750 0.9303 0.02707 0.01835 0.0085 0.1753 1.0000
9.000 0.9483 0.02799 0.01914 0.0100 0.1652 1.0000
9.250 0.9601 0.02898 0.02036 0.0125 0.1558 1.0000
9.500 0.9768 0.03009 0.02140 0.0141 0.1473 1.0000
9.750 0.9898 0.03105 0.02247 0.0163 0.1391 1.0000
10.000 1.0039 0.03236 0.02383 0.0182 0.1318 1.0000
10.250 1.0169 0.03340 0.02495 0.0202 0.1248 1.0000
10.500 1.0302 0.03495 0.02658 0.0221 0.1185 1.0000
10.750 1.0386 0.03622 0.02804 0.0246 0.1126 1.0000
11.000 1.0571 0.03796 0.02964 0.0254 0.1069 1.0000
11.250 1.0564 0.03956 0.03162 0.0290 0.1026 1.0000
11.500 1.0637 0.04098 0.03316 0.0313 0.0982 1.0000
11.750 1.0807 0.04325 0.03533 0.0319 0.0940 1.0000
12.000 1.0699 0.04533 0.03782 0.0361 0.0919 1.0000
12.250 1.0576 0.04743 0.04021 0.0401 0.0897 1.0000
12.500 1.0492 0.04952 0.04249 0.0433 0.0875 1.0000
12.750 1.0487 0.05134 0.04438 0.0453 0.0850 1.0000
13.000 1.0660 0.05422 0.04712 0.0453 0.0819 1.0000
13.250 1.0410 0.05728 0.05047 0.0480 0.0815 1.0000
13.500 1.0150 0.06111 0.05457 0.0493 0.0813 1.0000
13.750 0.9859 0.06579 0.05950 0.0491 0.0813 1.0000
14.000 0.9533 0.07161 0.06554 0.0474 0.0814 1.0000
14.250 0.9184 0.07872 0.07283 0.0443 0.0818 1.0000
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Polar data table (+)
Polar graphs
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