SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 200,000 Max Cl/Cd: 58.13 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7003-il-200000.txt Download as CSV file: xf-sd7003-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SD7003-085-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5721 0.07032 0.06673 -0.0324 1.0000 0.0604
-7.750 -0.5749 0.06555 0.06174 -0.0350 1.0000 0.0606
-7.500 -0.5719 0.05815 0.05447 -0.0357 1.0000 0.0620
-7.250 -0.6036 0.03400 0.02865 -0.0390 1.0000 0.0302
-7.000 -0.5886 0.03008 0.02421 -0.0384 1.0000 0.0302
-6.750 -0.5716 0.02648 0.02020 -0.0376 1.0000 0.0307
-6.500 -0.5511 0.02436 0.01787 -0.0369 1.0000 0.0320
-6.250 -0.5285 0.02332 0.01671 -0.0362 1.0000 0.0347
-6.000 -0.5055 0.02183 0.01485 -0.0352 1.0000 0.0375
-5.750 -0.4836 0.01936 0.01211 -0.0342 1.0000 0.0401
-5.500 -0.4602 0.01839 0.01108 -0.0335 1.0000 0.0442
-5.250 -0.4363 0.01732 0.00982 -0.0326 1.0000 0.0500
-5.000 -0.4129 0.01639 0.00891 -0.0318 1.0000 0.0562
-4.750 -0.3894 0.01540 0.00786 -0.0309 1.0000 0.0640
-4.500 -0.3652 0.01492 0.00729 -0.0301 1.0000 0.0728
-4.250 -0.3421 0.01400 0.00645 -0.0293 1.0000 0.0826
-4.000 -0.3186 0.01333 0.00580 -0.0285 1.0000 0.0940
-3.750 -0.2951 0.01274 0.00524 -0.0277 1.0000 0.1068
-3.500 -0.2716 0.01222 0.00479 -0.0269 1.0000 0.1229
-3.250 -0.2482 0.01173 0.00436 -0.0262 1.0000 0.1446
-3.000 -0.2250 0.01115 0.00401 -0.0256 1.0000 0.1793
-2.750 -0.2020 0.01056 0.00376 -0.0250 1.0000 0.2466
-2.500 -0.1796 0.00999 0.00361 -0.0245 1.0000 0.3433
-2.250 -0.1578 0.00952 0.00359 -0.0237 1.0000 0.4488
-2.000 -0.1376 0.00915 0.00367 -0.0225 1.0000 0.5602
-1.750 -0.0961 0.00880 0.00379 -0.0251 0.9901 0.6866
-1.500 -0.0560 0.00860 0.00385 -0.0269 0.9790 0.7787
-1.250 -0.0175 0.00844 0.00386 -0.0282 0.9675 0.8472
-1.000 0.0227 0.00831 0.00379 -0.0296 0.9567 0.9061
-0.750 0.0709 0.00817 0.00365 -0.0328 0.9451 0.9547
-0.500 0.1309 0.00803 0.00344 -0.0387 0.9332 0.9856
-0.250 0.1857 0.00787 0.00319 -0.0439 0.9151 1.0000
0.000 0.2189 0.00777 0.00298 -0.0446 0.8858 1.0000
0.250 0.2449 0.00776 0.00282 -0.0438 0.8538 1.0000
0.500 0.2676 0.00782 0.00273 -0.0424 0.8211 1.0000
0.750 0.2904 0.00793 0.00267 -0.0410 0.7890 1.0000
1.000 0.3137 0.00808 0.00264 -0.0398 0.7576 1.0000
1.250 0.3377 0.00824 0.00264 -0.0387 0.7266 1.0000
1.500 0.3621 0.00842 0.00266 -0.0377 0.6959 1.0000
1.750 0.3869 0.00861 0.00269 -0.0368 0.6653 1.0000
2.000 0.4120 0.00881 0.00274 -0.0360 0.6348 1.0000
2.250 0.4372 0.00903 0.00282 -0.0353 0.6046 1.0000
2.500 0.4626 0.00926 0.00291 -0.0347 0.5744 1.0000
2.750 0.4880 0.00950 0.00301 -0.0340 0.5444 1.0000
3.000 0.5136 0.00976 0.00315 -0.0334 0.5148 1.0000
3.250 0.5392 0.01003 0.00330 -0.0329 0.4854 1.0000
3.500 0.5649 0.01031 0.00346 -0.0324 0.4565 1.0000
3.750 0.5905 0.01061 0.00365 -0.0319 0.4279 1.0000
4.000 0.6162 0.01092 0.00388 -0.0314 0.4000 1.0000
4.250 0.6418 0.01125 0.00411 -0.0310 0.3728 1.0000
4.500 0.6673 0.01161 0.00437 -0.0305 0.3466 1.0000
4.750 0.6926 0.01200 0.00466 -0.0301 0.3212 1.0000
5.000 0.7182 0.01237 0.00498 -0.0297 0.2961 1.0000
5.250 0.7435 0.01279 0.00533 -0.0293 0.2726 1.0000
5.500 0.7686 0.01324 0.00570 -0.0288 0.2505 1.0000
5.750 0.7938 0.01370 0.00613 -0.0284 0.2294 1.0000
6.000 0.8187 0.01419 0.00657 -0.0280 0.2097 1.0000
6.250 0.8431 0.01476 0.00705 -0.0275 0.1919 1.0000
6.500 0.8679 0.01529 0.00758 -0.0270 0.1748 1.0000
6.750 0.8923 0.01586 0.00817 -0.0265 0.1590 1.0000
7.000 0.9166 0.01646 0.00877 -0.0260 0.1440 1.0000
7.250 0.9405 0.01708 0.00940 -0.0255 0.1298 1.0000
7.500 0.9642 0.01770 0.01002 -0.0250 0.1159 1.0000
7.750 0.9875 0.01836 0.01072 -0.0244 0.1030 1.0000
8.000 1.0102 0.01912 0.01150 -0.0238 0.0911 1.0000
8.250 1.0322 0.02000 0.01239 -0.0231 0.0800 1.0000
8.500 1.0531 0.02099 0.01338 -0.0223 0.0692 1.0000
8.750 1.0741 0.02197 0.01441 -0.0215 0.0598 1.0000
9.000 1.0941 0.02322 0.01580 -0.0205 0.0524 1.0000
9.250 1.1112 0.02491 0.01747 -0.0193 0.0468 1.0000
9.500 1.1314 0.02597 0.01873 -0.0183 0.0424 1.0000
9.750 1.1492 0.02744 0.02022 -0.0173 0.0393 1.0000
10.000 1.1646 0.03000 0.02291 -0.0161 0.0371 1.0000
10.250 1.1817 0.03164 0.02482 -0.0149 0.0353 1.0000
10.500 1.1972 0.03329 0.02670 -0.0136 0.0333 1.0000
10.750 1.2115 0.03481 0.02835 -0.0125 0.0315 1.0000
11.000 1.2235 0.03704 0.03067 -0.0113 0.0303 1.0000
11.250 1.2275 0.04115 0.03507 -0.0099 0.0294 1.0000
11.500 1.2277 0.04425 0.03851 -0.0079 0.0289 1.0000
11.750 1.2235 0.04691 0.04149 -0.0057 0.0286 1.0000
12.000 1.2129 0.04971 0.04455 -0.0033 0.0284 1.0000
12.250 1.1994 0.05298 0.04808 -0.0020 0.0281 1.0000
12.500 1.1833 0.05696 0.05232 -0.0022 0.0280 1.0000
12.750 1.1649 0.06188 0.05747 -0.0039 0.0280 1.0000
13.000 1.1449 0.06768 0.06349 -0.0070 0.0280 1.0000
13.250 1.1223 0.07475 0.07076 -0.0115 0.0282 1.0000
13.500 1.0979 0.08290 0.07910 -0.0173 0.0284 1.0000
13.750 1.0705 0.09249 0.08884 -0.0237 0.0289 1.0000
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Polar data table (+)
Polar graphs
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