S1012 (s1012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 500,000 Max Cl/Cd: 56.79 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1012-il-500000-n5.txt Download as CSV file: xf-s1012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1012
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.0833 0.10294 0.09955 -0.0179 1.0000 0.0142
-18.000 -1.1205 0.09166 0.08808 -0.0245 1.0000 0.0141
-17.750 -1.1544 0.08113 0.07736 -0.0308 1.0000 0.0140
-17.500 -1.1801 0.07226 0.06831 -0.0363 1.0000 0.0140
-17.250 -1.2013 0.06467 0.06054 -0.0408 1.0000 0.0141
-17.000 -1.2163 0.05866 0.05436 -0.0441 1.0000 0.0142
-16.750 -1.2284 0.05361 0.04917 -0.0464 1.0000 0.0143
-16.500 -1.2364 0.04957 0.04499 -0.0478 1.0000 0.0144
-16.250 -1.2417 0.04619 0.04147 -0.0486 1.0000 0.0146
-16.000 -1.2445 0.04334 0.03850 -0.0488 1.0000 0.0149
-15.750 -1.2459 0.04079 0.03582 -0.0486 1.0000 0.0152
-15.500 -1.2446 0.03864 0.03356 -0.0481 1.0000 0.0155
-15.250 -1.2424 0.03666 0.03144 -0.0474 1.0000 0.0157
-15.000 -1.2409 0.03472 0.02940 -0.0464 1.0000 0.0160
-14.750 -1.2391 0.03288 0.02747 -0.0452 1.0000 0.0163
-14.500 -1.2340 0.03134 0.02586 -0.0441 1.0000 0.0167
-14.250 -1.2276 0.02996 0.02440 -0.0428 1.0000 0.0170
-14.000 -1.2194 0.02874 0.02310 -0.0415 1.0000 0.0175
-13.750 -1.2099 0.02763 0.02191 -0.0402 1.0000 0.0180
-13.500 -1.1992 0.02661 0.02082 -0.0389 1.0000 0.0186
-13.250 -1.1880 0.02565 0.01975 -0.0375 1.0000 0.0192
-13.000 -1.1757 0.02478 0.01879 -0.0361 1.0000 0.0196
-12.750 -1.1655 0.02377 0.01774 -0.0345 1.0000 0.0203
-12.500 -1.1527 0.02294 0.01687 -0.0330 1.0000 0.0210
-12.250 -1.1388 0.02220 0.01607 -0.0316 1.0000 0.0217
-12.000 -1.1240 0.02151 0.01533 -0.0303 1.0000 0.0225
-11.500 -1.0819 0.02015 0.01381 -0.0298 0.9607 0.0244
-11.250 -1.0565 0.01945 0.01306 -0.0304 0.9398 0.0259
-11.000 -1.0388 0.01894 0.01247 -0.0291 0.9232 0.0272
-10.500 -1.0061 0.01808 0.01141 -0.0257 0.9023 0.0296
-10.250 -0.9903 0.01763 0.01090 -0.0238 0.8950 0.0311
-10.000 -0.9721 0.01722 0.01046 -0.0224 0.8890 0.0328
-9.750 -0.9524 0.01686 0.01001 -0.0212 0.8840 0.0345
-9.250 -0.9114 0.01606 0.00913 -0.0191 0.8763 0.0384
-9.000 -0.8896 0.01570 0.00875 -0.0183 0.8728 0.0407
-8.750 -0.8673 0.01539 0.00837 -0.0175 0.8695 0.0426
-8.500 -0.8457 0.01501 0.00797 -0.0166 0.8666 0.0450
-8.000 -0.7997 0.01440 0.00729 -0.0152 0.8617 0.0504
-7.750 -0.7765 0.01407 0.00695 -0.0146 0.8592 0.0534
-7.500 -0.7530 0.01376 0.00665 -0.0140 0.8566 0.0571
-7.250 -0.7289 0.01350 0.00635 -0.0135 0.8541 0.0604
-7.000 -0.7052 0.01321 0.00605 -0.0129 0.8519 0.0641
-6.750 -0.6811 0.01294 0.00578 -0.0123 0.8501 0.0684
-6.500 -0.6563 0.01273 0.00552 -0.0118 0.8484 0.0721
-6.250 -0.6318 0.01244 0.00527 -0.0114 0.8466 0.0774
-6.000 -0.6067 0.01221 0.00504 -0.0110 0.8448 0.0825
-5.750 -0.5815 0.01197 0.00481 -0.0106 0.8430 0.0879
-5.500 -0.5563 0.01174 0.00460 -0.0103 0.8413 0.0948
-5.250 -0.5308 0.01153 0.00440 -0.0099 0.8396 0.1012
-5.000 -0.5054 0.01131 0.00421 -0.0096 0.8378 0.1095
-4.750 -0.4800 0.01109 0.00402 -0.0092 0.8360 0.1185
-4.500 -0.4542 0.01091 0.00384 -0.0089 0.8345 0.1274
-4.250 -0.4286 0.01071 0.00368 -0.0085 0.8332 0.1389
-4.000 -0.4029 0.01050 0.00353 -0.0082 0.8319 0.1528
-3.750 -0.3770 0.01029 0.00339 -0.0080 0.8304 0.1681
-3.500 -0.3511 0.01008 0.00326 -0.0077 0.8289 0.1866
-3.250 -0.3257 0.00983 0.00312 -0.0074 0.8271 0.2106
-3.000 -0.3003 0.00958 0.00300 -0.0071 0.8253 0.2384
-2.750 -0.2754 0.00929 0.00287 -0.0067 0.8238 0.2764
-2.500 -0.2509 0.00897 0.00274 -0.0062 0.8221 0.3226
-2.250 -0.2269 0.00862 0.00260 -0.0057 0.8204 0.3780
-2.000 -0.2044 0.00816 0.00245 -0.0048 0.8188 0.4529
-1.750 -0.1829 0.00765 0.00229 -0.0038 0.8171 0.5414
-1.500 -0.1624 0.00714 0.00225 -0.0024 0.8151 0.6464
-1.250 -0.1370 0.00706 0.00239 -0.0017 0.8129 0.7062
-1.000 -0.1095 0.00706 0.00244 -0.0015 0.8094 0.7288
-0.750 -0.0823 0.00703 0.00237 -0.0010 0.8018 0.7432
-0.500 -0.0553 0.00695 0.00226 -0.0006 0.7885 0.7536
-0.250 -0.0279 0.00692 0.00222 -0.0002 0.7773 0.7616
0.000 0.0000 0.00691 0.00218 0.0000 0.7698 0.7698
0.250 0.0279 0.00692 0.00222 0.0002 0.7618 0.7772
0.500 0.0553 0.00695 0.00226 0.0006 0.7535 0.7885
0.750 0.0822 0.00703 0.00237 0.0010 0.7431 0.8018
1.000 0.1095 0.00706 0.00244 0.0015 0.7290 0.8094
1.250 0.1370 0.00706 0.00239 0.0017 0.7064 0.8129
1.750 0.1828 0.00765 0.00229 0.0038 0.5403 0.8171
2.000 0.2043 0.00817 0.00245 0.0049 0.4516 0.8188
2.250 0.2270 0.00861 0.00260 0.0057 0.3784 0.8204
2.500 0.2509 0.00897 0.00274 0.0062 0.3226 0.8221
2.750 0.2754 0.00929 0.00287 0.0067 0.2771 0.8238
3.000 0.3003 0.00958 0.00300 0.0071 0.2387 0.8253
3.250 0.3257 0.00983 0.00312 0.0074 0.2107 0.8271
3.500 0.3511 0.01008 0.00326 0.0078 0.1864 0.8289
3.750 0.3770 0.01029 0.00339 0.0080 0.1681 0.8304
4.000 0.4029 0.01050 0.00353 0.0082 0.1528 0.8319
4.250 0.4286 0.01071 0.00368 0.0086 0.1388 0.8332
4.500 0.4542 0.01091 0.00384 0.0089 0.1273 0.8345
4.750 0.4800 0.01109 0.00402 0.0092 0.1184 0.8360
5.000 0.5054 0.01131 0.00421 0.0096 0.1094 0.8378
5.250 0.5308 0.01152 0.00440 0.0099 0.1013 0.8396
5.500 0.5563 0.01174 0.00460 0.0103 0.0948 0.8413
5.750 0.5815 0.01197 0.00481 0.0106 0.0879 0.8430
6.000 0.6066 0.01221 0.00504 0.0110 0.0825 0.8448
6.250 0.6318 0.01244 0.00527 0.0114 0.0774 0.8466
6.500 0.6563 0.01273 0.00552 0.0118 0.0721 0.8483
6.750 0.6810 0.01294 0.00578 0.0123 0.0685 0.8500
7.000 0.7052 0.01321 0.00605 0.0129 0.0643 0.8519
7.250 0.7289 0.01350 0.00635 0.0135 0.0603 0.8541
7.500 0.7530 0.01376 0.00664 0.0140 0.0571 0.8566
7.750 0.7765 0.01407 0.00695 0.0146 0.0534 0.8592
8.000 0.7998 0.01440 0.00729 0.0152 0.0505 0.8617
8.500 0.8457 0.01501 0.00797 0.0166 0.0450 0.8666
8.750 0.8673 0.01539 0.00837 0.0175 0.0426 0.8695
9.000 0.8897 0.01570 0.00874 0.0183 0.0407 0.8727
9.250 0.9115 0.01605 0.00913 0.0191 0.0383 0.8763
9.750 0.9525 0.01685 0.01001 0.0212 0.0344 0.8840
10.000 0.9722 0.01722 0.01045 0.0224 0.0328 0.8890
10.250 0.9904 0.01762 0.01090 0.0238 0.0311 0.8950
10.500 1.0063 0.01808 0.01140 0.0257 0.0296 0.9023
11.000 1.0389 0.01895 0.01247 0.0291 0.0272 0.9233
11.250 1.0568 0.01945 0.01305 0.0303 0.0259 0.9399
11.500 1.0823 0.02015 0.01381 0.0298 0.0244 0.9609
12.000 1.1243 0.02151 0.01532 0.0302 0.0226 1.0000
12.250 1.1391 0.02220 0.01607 0.0316 0.0217 1.0000
12.500 1.1530 0.02295 0.01687 0.0330 0.0210 1.0000
12.750 1.1658 0.02377 0.01774 0.0344 0.0203 1.0000
13.000 1.1763 0.02477 0.01877 0.0360 0.0196 1.0000
13.250 1.1882 0.02567 0.01977 0.0374 0.0191 1.0000
13.500 1.1999 0.02660 0.02080 0.0388 0.0185 1.0000
13.750 1.2109 0.02759 0.02187 0.0401 0.0180 1.0000
14.000 1.2200 0.02872 0.02308 0.0414 0.0175 1.0000
14.250 1.2279 0.02997 0.02441 0.0427 0.0172 1.0000
14.500 1.2348 0.03132 0.02584 0.0440 0.0167 1.0000
14.750 1.2395 0.03288 0.02748 0.0452 0.0163 1.0000
15.000 1.2408 0.03476 0.02944 0.0464 0.0159 1.0000
15.250 1.2426 0.03668 0.03147 0.0473 0.0157 1.0000
15.500 1.2462 0.03854 0.03346 0.0480 0.0154 1.0000
15.750 1.2471 0.04072 0.03575 0.0485 0.0151 1.0000
16.000 1.2461 0.04323 0.03839 0.0487 0.0149 1.0000
16.250 1.2427 0.04614 0.04143 0.0485 0.0146 1.0000
16.500 1.2380 0.04945 0.04486 0.0478 0.0144 1.0000
16.750 1.2287 0.05367 0.04922 0.0463 0.0143 1.0000
17.000 1.2173 0.05860 0.05431 0.0440 0.0142 1.0000
17.250 1.2040 0.06436 0.06022 0.0408 0.0140 1.0000
17.500 1.1835 0.07183 0.06787 0.0364 0.0140 1.0000
17.750 1.1564 0.08090 0.07713 0.0308 0.0140 1.0000
18.000 1.1221 0.09156 0.08798 0.0244 0.0140 1.0000
18.250 1.0853 0.10275 0.09934 0.0179 0.0142 1.0000
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