SA7035 (sa7035-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 100,000 Max Cl/Cd: 53.33 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7035-il-100000-n5.txt Download as CSV file: xf-sa7035-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4102 0.08661 0.08177 -0.0347 1.0000 0.0247
-8.250 -0.4091 0.08341 0.07861 -0.0344 1.0000 0.0240
-8.000 -0.4124 0.07959 0.07488 -0.0359 1.0000 0.0239
-7.750 -0.4164 0.07650 0.07187 -0.0363 1.0000 0.0233
-7.500 -0.4232 0.07267 0.06813 -0.0380 1.0000 0.0229
-7.250 -0.4283 0.06831 0.06380 -0.0406 1.0000 0.0227
-7.000 -0.4324 0.06437 0.05987 -0.0417 1.0000 0.0220
-6.750 -0.4371 0.05996 0.05542 -0.0427 1.0000 0.0217
-6.500 -0.4400 0.05567 0.05103 -0.0430 1.0000 0.0212
-6.250 -0.4404 0.05134 0.04653 -0.0430 1.0000 0.0209
-6.000 -0.4381 0.04677 0.04171 -0.0427 1.0000 0.0203
-5.750 -0.4318 0.04232 0.03691 -0.0423 1.0000 0.0197
-5.500 -0.4217 0.03795 0.03208 -0.0417 1.0000 0.0192
-5.250 -0.3918 0.03303 0.02642 -0.0442 0.9953 0.0188
-5.000 -0.3597 0.02948 0.02225 -0.0461 0.9901 0.0188
-4.750 -0.3258 0.02672 0.01896 -0.0479 0.9853 0.0190
-4.500 -0.2924 0.02453 0.01637 -0.0492 0.9804 0.0195
-4.250 -0.2585 0.02269 0.01418 -0.0504 0.9750 0.0205
-4.000 -0.2218 0.02117 0.01241 -0.0522 0.9707 0.0220
-3.750 -0.1901 0.02002 0.01108 -0.0529 0.9637 0.0255
-3.500 -0.1543 0.01889 0.00991 -0.0547 0.9585 0.0299
-3.250 -0.1218 0.01787 0.00873 -0.0556 0.9515 0.0368
-3.000 -0.0863 0.01681 0.00776 -0.0572 0.9456 0.0670
-2.750 -0.0543 0.01556 0.00717 -0.0586 0.9390 0.1914
-2.500 -0.0228 0.01458 0.00687 -0.0598 0.9319 0.3634
-2.250 0.0066 0.01394 0.00669 -0.0601 0.9238 0.5050
-2.000 0.0368 0.01346 0.00655 -0.0599 0.9163 0.6355
-1.750 0.0619 0.01314 0.00645 -0.0584 0.9065 0.7374
-1.500 0.0926 0.01287 0.00630 -0.0577 0.8991 0.8296
-1.250 0.1329 0.01269 0.00608 -0.0592 0.8907 0.9120
-1.000 0.1889 0.01249 0.00571 -0.0645 0.8848 0.9759
-0.750 0.2293 0.01237 0.00541 -0.0670 0.8743 1.0000
-0.500 0.2558 0.01233 0.00520 -0.0666 0.8611 1.0000
-0.250 0.2823 0.01229 0.00502 -0.0662 0.8476 1.0000
0.000 0.3090 0.01226 0.00486 -0.0657 0.8336 1.0000
0.250 0.3356 0.01224 0.00471 -0.0653 0.8190 1.0000
0.500 0.3623 0.01222 0.00459 -0.0647 0.8040 1.0000
0.750 0.3891 0.01222 0.00448 -0.0642 0.7885 1.0000
1.000 0.4152 0.01225 0.00441 -0.0636 0.7716 1.0000
1.250 0.4413 0.01229 0.00437 -0.0630 0.7539 1.0000
1.500 0.4676 0.01234 0.00432 -0.0624 0.7359 1.0000
1.750 0.4940 0.01241 0.00429 -0.0618 0.7177 1.0000
2.000 0.5196 0.01252 0.00432 -0.0611 0.6978 1.0000
2.250 0.5455 0.01265 0.00437 -0.0604 0.6781 1.0000
2.500 0.5712 0.01280 0.00444 -0.0598 0.6580 1.0000
2.750 0.5967 0.01297 0.00453 -0.0592 0.6371 1.0000
3.000 0.6222 0.01316 0.00465 -0.0585 0.6166 1.0000
3.250 0.6474 0.01337 0.00483 -0.0579 0.5949 1.0000
3.500 0.6725 0.01361 0.00499 -0.0572 0.5734 1.0000
3.750 0.6973 0.01386 0.00519 -0.0565 0.5507 1.0000
4.000 0.7220 0.01413 0.00541 -0.0558 0.5280 1.0000
4.250 0.7465 0.01444 0.00568 -0.0551 0.5058 1.0000
4.500 0.7710 0.01475 0.00597 -0.0545 0.4831 1.0000
4.750 0.7952 0.01509 0.00627 -0.0538 0.4610 1.0000
5.000 0.8192 0.01545 0.00661 -0.0531 0.4382 1.0000
5.250 0.8429 0.01583 0.00701 -0.0524 0.4153 1.0000
5.500 0.8662 0.01626 0.00739 -0.0516 0.3925 1.0000
5.750 0.8895 0.01668 0.00783 -0.0509 0.3689 1.0000
6.000 0.9124 0.01715 0.00829 -0.0501 0.3460 1.0000
6.250 0.9349 0.01765 0.00881 -0.0493 0.3233 1.0000
6.500 0.9573 0.01817 0.00936 -0.0485 0.3009 1.0000
6.750 0.9789 0.01876 0.00993 -0.0476 0.2789 1.0000
7.000 1.0004 0.01935 0.01055 -0.0468 0.2557 1.0000
7.250 1.0212 0.02000 0.01121 -0.0458 0.2324 1.0000
7.500 1.0410 0.02073 0.01191 -0.0448 0.2096 1.0000
7.750 1.0610 0.02146 0.01272 -0.0439 0.1866 1.0000
8.000 1.0800 0.02228 0.01355 -0.0428 0.1655 1.0000
8.250 1.0981 0.02317 0.01445 -0.0417 0.1447 1.0000
8.500 1.1155 0.02413 0.01544 -0.0404 0.1258 1.0000
8.750 1.1319 0.02518 0.01652 -0.0391 0.1068 1.0000
9.000 1.1463 0.02638 0.01771 -0.0376 0.0911 1.0000
9.250 1.1592 0.02768 0.01905 -0.0360 0.0771 1.0000
9.500 1.1706 0.02908 0.02047 -0.0343 0.0654 1.0000
9.750 1.1816 0.03045 0.02197 -0.0324 0.0552 1.0000
10.000 1.1898 0.03193 0.02357 -0.0303 0.0480 1.0000
10.250 1.1922 0.03367 0.02530 -0.0277 0.0426 1.0000
10.500 1.1984 0.03529 0.02715 -0.0255 0.0377 1.0000
10.750 1.2006 0.03719 0.02918 -0.0233 0.0346 1.0000
11.000 1.1988 0.03956 0.03161 -0.0212 0.0320 1.0000
11.250 1.2025 0.04164 0.03395 -0.0197 0.0290 1.0000
11.500 1.2034 0.04394 0.03641 -0.0184 0.0267 1.0000
11.750 1.2017 0.04660 0.03920 -0.0173 0.0250 1.0000
12.000 1.1979 0.04974 0.04244 -0.0165 0.0239 1.0000
12.250 1.1963 0.05297 0.04586 -0.0159 0.0230 1.0000
12.500 1.1938 0.05639 0.04963 -0.0156 0.0217 1.0000
12.750 1.1891 0.06011 0.05361 -0.0160 0.0206 1.0000
13.000 1.1825 0.06417 0.05788 -0.0169 0.0195 1.0000
13.250 1.1753 0.06853 0.06244 -0.0181 0.0189 1.0000
13.500 1.1665 0.07333 0.06742 -0.0200 0.0183 1.0000
13.750 1.1564 0.07851 0.07277 -0.0223 0.0178 1.0000
14.000 1.1450 0.08421 0.07864 -0.0250 0.0175 1.0000
14.250 1.1325 0.09044 0.08505 -0.0282 0.0173 1.0000
14.500 1.1186 0.09730 0.09211 -0.0319 0.0173 1.0000
14.750 1.1029 0.10493 0.09993 -0.0363 0.0172 1.0000
15.000 1.0844 0.11371 0.10892 -0.0417 0.0173 1.0000
15.250 1.0584 0.12524 0.12069 -0.0489 0.0179 1.0000
15.500 1.0110 0.14445 0.14008 -0.0603 0.0205 1.0000
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Polar data table (+)
Polar graphs
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