S7075 (9%) (s7075-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 50,000 Max Cl/Cd: 40.16 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7075-il-50000-n5.txt Download as CSV file: xf-s7075-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7075 (9%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3869 0.11462 0.10740 -0.0324 1.0000 0.1130
-9.250 -0.4001 0.11318 0.10609 -0.0347 1.0000 0.1143
-9.000 -0.4090 0.11098 0.10401 -0.0359 1.0000 0.1147
-8.750 -0.4072 0.10735 0.10048 -0.0355 1.0000 0.1150
-8.500 -0.3854 0.10238 0.09544 -0.0332 1.0000 0.1118
-8.250 -0.3981 0.09463 0.08772 -0.0375 1.0000 0.0579
-8.000 -0.3984 0.09176 0.08492 -0.0363 1.0000 0.0562
-7.750 -0.4052 0.08900 0.08226 -0.0354 1.0000 0.0546
-7.500 -0.4147 0.08630 0.07968 -0.0346 1.0000 0.0533
-7.250 -0.4232 0.08277 0.07624 -0.0355 1.0000 0.0518
-6.750 -0.4417 0.07151 0.06491 -0.0437 1.0000 0.0467
-6.500 -0.4401 0.06812 0.06150 -0.0435 1.0000 0.0462
-6.250 -0.4375 0.06439 0.05772 -0.0439 1.0000 0.0458
-6.000 -0.4327 0.06042 0.05363 -0.0447 1.0000 0.0453
-5.750 -0.4249 0.05630 0.04933 -0.0458 1.0000 0.0448
-5.500 -0.4139 0.05204 0.04480 -0.0470 1.0000 0.0444
-5.250 -0.3992 0.04790 0.04030 -0.0483 1.0000 0.0442
-5.000 -0.3811 0.04395 0.03587 -0.0495 1.0000 0.0449
-4.750 -0.3600 0.04040 0.03170 -0.0504 1.0000 0.0460
-4.500 -0.3372 0.03728 0.02799 -0.0509 1.0000 0.0474
-4.250 -0.3154 0.03480 0.02523 -0.0510 1.0000 0.0486
-4.000 -0.2918 0.03261 0.02269 -0.0509 1.0000 0.0498
-3.750 -0.2676 0.03075 0.02050 -0.0507 1.0000 0.0512
-3.500 -0.2429 0.02912 0.01854 -0.0502 1.0000 0.0534
-3.250 -0.2185 0.02780 0.01685 -0.0496 1.0000 0.0576
-3.000 -0.1953 0.02665 0.01562 -0.0490 1.0000 0.0634
-2.750 -0.1720 0.02568 0.01445 -0.0481 1.0000 0.0703
-2.500 -0.1491 0.02483 0.01355 -0.0475 1.0000 0.0822
-2.250 -0.1226 0.02401 0.01270 -0.0475 0.9990 0.1037
-2.000 -0.0849 0.02296 0.01188 -0.0500 0.9940 0.1629
-1.750 -0.0493 0.02161 0.01152 -0.0525 0.9887 0.3501
-1.500 -0.0246 0.02052 0.01181 -0.0511 0.9832 0.6526
-1.250 0.0081 0.01990 0.01153 -0.0506 0.9736 1.0000
-1.000 0.0462 0.02023 0.01139 -0.0531 0.9655 1.0000
-0.750 0.0859 0.02061 0.01137 -0.0559 0.9576 1.0000
-0.500 0.1209 0.02090 0.01134 -0.0577 0.9479 1.0000
-0.250 0.1591 0.02124 0.01141 -0.0601 0.9392 1.0000
0.000 0.1959 0.02153 0.01148 -0.0622 0.9297 1.0000
0.250 0.2293 0.02180 0.01156 -0.0636 0.9190 1.0000
0.500 0.2657 0.02206 0.01167 -0.0655 0.9091 1.0000
0.750 0.3039 0.02229 0.01177 -0.0676 0.8994 1.0000
1.000 0.3356 0.02249 0.01188 -0.0685 0.8873 1.0000
1.250 0.3684 0.02267 0.01199 -0.0695 0.8752 1.0000
1.500 0.4021 0.02281 0.01208 -0.0706 0.8632 1.0000
1.750 0.4372 0.02289 0.01214 -0.0718 0.8514 1.0000
2.000 0.4758 0.02289 0.01212 -0.0734 0.8406 1.0000
2.250 0.5080 0.02290 0.01216 -0.0739 0.8271 1.0000
2.500 0.5395 0.02288 0.01217 -0.0742 0.8130 1.0000
2.750 0.5712 0.02281 0.01214 -0.0744 0.7985 1.0000
3.000 0.6031 0.02269 0.01208 -0.0745 0.7836 1.0000
3.250 0.6304 0.02267 0.01214 -0.0739 0.7658 1.0000
3.500 0.6605 0.02255 0.01209 -0.0736 0.7483 1.0000
3.750 0.6925 0.02235 0.01197 -0.0735 0.7305 1.0000
4.000 0.7263 0.02209 0.01182 -0.0735 0.7122 1.0000
4.250 0.7544 0.02204 0.01184 -0.0728 0.6891 1.0000
4.500 0.7860 0.02190 0.01175 -0.0724 0.6659 1.0000
4.750 0.8161 0.02185 0.01173 -0.0718 0.6398 1.0000
5.000 0.8437 0.02194 0.01188 -0.0710 0.6109 1.0000
5.250 0.8699 0.02214 0.01206 -0.0699 0.5799 1.0000
5.500 0.8937 0.02246 0.01237 -0.0687 0.5466 1.0000
5.750 0.9166 0.02285 0.01276 -0.0672 0.5118 1.0000
6.000 0.9378 0.02335 0.01319 -0.0657 0.4760 1.0000
6.250 0.9574 0.02394 0.01373 -0.0640 0.4390 1.0000
6.500 0.9757 0.02464 0.01433 -0.0623 0.4016 1.0000
6.750 0.9926 0.02543 0.01502 -0.0604 0.3637 1.0000
7.000 1.0082 0.02632 0.01586 -0.0585 0.3255 1.0000
7.250 1.0227 0.02734 0.01673 -0.0566 0.2889 1.0000
7.500 1.0369 0.02845 0.01776 -0.0548 0.2534 1.0000
7.750 1.0502 0.02970 0.01889 -0.0530 0.2213 1.0000
8.000 1.0631 0.03105 0.02014 -0.0512 0.1925 1.0000
8.250 1.0765 0.03250 0.02156 -0.0495 0.1678 1.0000
8.500 1.0886 0.03404 0.02298 -0.0478 0.1480 1.0000
8.750 1.1028 0.03561 0.02459 -0.0463 0.1313 1.0000
9.000 1.1162 0.03722 0.02623 -0.0447 0.1182 1.0000
9.250 1.1287 0.03886 0.02785 -0.0431 0.1076 1.0000
9.500 1.1471 0.04065 0.02990 -0.0420 0.0988 1.0000
9.750 1.1653 0.04256 0.03185 -0.0411 0.0926 1.0000
10.000 1.1813 0.04450 0.03405 -0.0399 0.0860 1.0000
10.250 1.1963 0.04642 0.03593 -0.0389 0.0810 1.0000
10.500 1.2115 0.04885 0.03881 -0.0377 0.0768 1.0000
10.750 1.2259 0.05140 0.04165 -0.0365 0.0738 1.0000
11.000 1.2381 0.05394 0.04440 -0.0354 0.0714 1.0000
11.250 1.2529 0.05664 0.04716 -0.0347 0.0689 1.0000
11.500 1.2475 0.05980 0.05081 -0.0322 0.0674 1.0000
11.750 1.2391 0.06319 0.05461 -0.0301 0.0658 1.0000
12.000 1.2283 0.06685 0.05862 -0.0284 0.0646 1.0000
12.250 1.2149 0.07089 0.06297 -0.0273 0.0636 1.0000
12.500 1.1983 0.07547 0.06783 -0.0270 0.0629 1.0000
12.750 1.1773 0.08088 0.07351 -0.0277 0.0626 1.0000
13.000 1.1504 0.08761 0.08049 -0.0300 0.0627 1.0000
13.250 1.1159 0.09646 0.08958 -0.0346 0.0635 1.0000
13.500 1.0751 0.10823 0.10146 -0.0420 0.0649 1.0000
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Polar data table (+)
Polar graphs
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