S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 50,000 Max Cl/Cd: 24.49 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8035-il-50000.txt Download as CSV file: xf-s8035-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4807 0.11752 0.10908 0.0071 1.0000 0.3911
-10.500 -0.7216 0.07644 0.06860 -0.0262 1.0000 0.2261
-10.250 -0.7368 0.07089 0.06307 -0.0272 1.0000 0.2291
-10.000 -0.8490 0.05928 0.05140 -0.0261 1.0000 0.2179
-9.750 -0.8812 0.05450 0.04639 -0.0229 1.0000 0.2197
-9.500 -0.9077 0.05023 0.04175 -0.0190 1.0000 0.2229
-9.250 -0.8898 0.04858 0.04015 -0.0175 1.0000 0.2328
-9.000 -0.9063 0.04515 0.03627 -0.0135 1.0000 0.2393
-8.750 -0.8859 0.04386 0.03507 -0.0120 1.0000 0.2514
-8.500 -0.8751 0.04199 0.03313 -0.0098 1.0000 0.2623
-8.250 -0.8704 0.03997 0.03091 -0.0070 1.0000 0.2739
-8.000 -0.8639 0.03819 0.02891 -0.0041 1.0000 0.2869
-7.750 -0.8491 0.03690 0.02758 -0.0020 1.0000 0.3014
-7.500 -0.8344 0.03568 0.02635 0.0002 1.0000 0.3170
-7.250 -0.8206 0.03449 0.02511 0.0025 1.0000 0.3332
-7.000 -0.8026 0.03359 0.02429 0.0045 1.0000 0.3508
-6.750 -0.7845 0.03275 0.02351 0.0066 1.0000 0.3686
-6.500 -0.7670 0.03201 0.02283 0.0088 1.0000 0.3877
-6.250 -0.7517 0.03115 0.02197 0.0111 1.0000 0.4069
-6.000 -0.7397 0.03021 0.02097 0.0138 1.0000 0.4275
-5.750 -0.7210 0.02965 0.02050 0.0160 1.0000 0.4475
-5.500 -0.7033 0.02916 0.02008 0.0184 1.0000 0.4684
-5.250 -0.6905 0.02845 0.01935 0.0211 1.0000 0.4906
-5.000 -0.6727 0.02808 0.01907 0.0236 1.0000 0.5118
-4.750 -0.6562 0.02774 0.01878 0.0262 1.0000 0.5340
-4.500 -0.6436 0.02722 0.01825 0.0291 1.0000 0.5571
-4.250 -0.6251 0.02712 0.01825 0.0317 1.0000 0.5789
-4.000 -0.6131 0.02670 0.01783 0.0346 1.0000 0.6028
-3.750 -0.5955 0.02663 0.01782 0.0373 1.0000 0.6248
-3.500 -0.5813 0.02642 0.01764 0.0402 1.0000 0.6482
-3.250 -0.5667 0.02627 0.01751 0.0430 1.0000 0.6714
-3.000 -0.5510 0.02623 0.01751 0.0458 1.0000 0.6950
-2.750 -0.5369 0.02613 0.01742 0.0487 1.0000 0.7195
-2.500 -0.5207 0.02617 0.01748 0.0513 1.0000 0.7443
-2.250 -0.5031 0.02622 0.01755 0.0536 1.0000 0.7695
-2.000 -0.4887 0.02617 0.01748 0.0561 1.0000 0.7970
-1.750 -0.4567 0.02662 0.01793 0.0562 1.0000 0.8224
-1.500 -0.4227 0.02700 0.01829 0.0553 1.0000 0.8498
-1.250 -0.3810 0.02749 0.01871 0.0527 1.0000 0.8775
-1.000 -0.3013 0.02854 0.01967 0.0434 1.0000 0.9001
-0.750 -0.2339 0.02919 0.02024 0.0352 1.0000 0.9256
-0.500 -0.1533 0.02974 0.02074 0.0239 1.0000 0.9486
-0.250 -0.0820 0.03007 0.02105 0.0134 1.0000 0.9741
0.000 0.0000 0.03022 0.02119 0.0000 1.0000 1.0000
0.250 0.0816 0.03007 0.02105 -0.0133 0.9741 1.0000
0.500 0.1529 0.02974 0.02074 -0.0239 0.9487 1.0000
0.750 0.2338 0.02918 0.02024 -0.0351 0.9256 1.0000
1.000 0.3008 0.02854 0.01967 -0.0433 0.9002 1.0000
1.250 0.3808 0.02749 0.01871 -0.0527 0.8778 1.0000
1.500 0.4223 0.02700 0.01829 -0.0552 0.8499 1.0000
1.750 0.4565 0.02662 0.01793 -0.0562 0.8227 1.0000
2.000 0.4887 0.02616 0.01748 -0.0561 0.7971 1.0000
2.250 0.5030 0.02622 0.01755 -0.0536 0.7696 1.0000
2.500 0.5206 0.02616 0.01747 -0.0513 0.7443 1.0000
2.750 0.5368 0.02613 0.01741 -0.0487 0.7195 1.0000
3.000 0.5510 0.02622 0.01750 -0.0458 0.6951 1.0000
3.250 0.5667 0.02626 0.01751 -0.0430 0.6714 1.0000
3.500 0.5812 0.02642 0.01763 -0.0402 0.6482 1.0000
3.750 0.5955 0.02662 0.01781 -0.0373 0.6248 1.0000
4.000 0.6131 0.02670 0.01782 -0.0346 0.6029 1.0000
4.250 0.6250 0.02712 0.01825 -0.0317 0.5789 1.0000
4.500 0.6436 0.02722 0.01825 -0.0291 0.5571 1.0000
4.750 0.6562 0.02774 0.01877 -0.0262 0.5340 1.0000
5.000 0.6727 0.02808 0.01906 -0.0236 0.5118 1.0000
5.250 0.6905 0.02845 0.01935 -0.0211 0.4906 1.0000
5.500 0.7033 0.02916 0.02008 -0.0184 0.4685 1.0000
5.750 0.7209 0.02965 0.02050 -0.0160 0.4476 1.0000
6.000 0.7397 0.03021 0.02097 -0.0138 0.4275 1.0000
6.250 0.7517 0.03114 0.02197 -0.0111 0.4070 1.0000
6.500 0.7671 0.03200 0.02282 -0.0088 0.3877 1.0000
6.750 0.7845 0.03275 0.02351 -0.0066 0.3687 1.0000
7.000 0.8027 0.03358 0.02429 -0.0045 0.3508 1.0000
7.250 0.8206 0.03449 0.02511 -0.0025 0.3332 1.0000
7.500 0.8346 0.03569 0.02635 -0.0002 0.3170 1.0000
7.750 0.8493 0.03689 0.02757 0.0020 0.3014 1.0000
8.000 0.8643 0.03816 0.02887 0.0041 0.2868 1.0000
8.250 0.8704 0.03997 0.03092 0.0070 0.2739 1.0000
8.500 0.8751 0.04200 0.03314 0.0098 0.2623 1.0000
8.750 0.8860 0.04386 0.03507 0.0120 0.2514 1.0000
9.000 0.9062 0.04516 0.03628 0.0135 0.2393 1.0000
9.250 0.8898 0.04859 0.04016 0.0175 0.2328 1.0000
9.500 0.9079 0.05023 0.04176 0.0189 0.2229 1.0000
9.750 0.8813 0.05451 0.04640 0.0229 0.2197 1.0000
10.000 0.8494 0.05925 0.05136 0.0261 0.2178 1.0000
10.250 0.7374 0.07089 0.06306 0.0271 0.2291 1.0000
10.500 0.7220 0.07647 0.06863 0.0261 0.2261 1.0000
10.750 0.3775 0.11546 0.10759 0.0000 0.3947 1.0000
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Polar data table (+)
Polar graphs
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