S1012 (s1012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.92 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1012-il-1000000.txt Download as CSV file: xf-s1012-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -1.1658 0.09878 0.09587 -0.0210 1.0000 0.0132
-18.750 -1.2005 0.08828 0.08521 -0.0272 1.0000 0.0131
-18.500 -1.2320 0.07843 0.07518 -0.0331 1.0000 0.0131
-18.250 -1.2574 0.06992 0.06651 -0.0382 1.0000 0.0131
-18.000 -1.2810 0.06217 0.05860 -0.0427 1.0000 0.0132
-17.750 -1.2987 0.05598 0.05225 -0.0460 1.0000 0.0132
-17.500 -1.3127 0.05086 0.04700 -0.0481 1.0000 0.0133
-17.250 -1.3231 0.04667 0.04270 -0.0494 1.0000 0.0136
-17.000 -1.3292 0.04336 0.03928 -0.0498 1.0000 0.0137
-16.750 -1.3332 0.04051 0.03633 -0.0498 1.0000 0.0139
-16.500 -1.3351 0.03805 0.03377 -0.0494 1.0000 0.0140
-16.250 -1.3319 0.03617 0.03182 -0.0488 1.0000 0.0143
-16.000 -1.3289 0.03434 0.02991 -0.0480 1.0000 0.0145
-15.750 -1.3249 0.03267 0.02815 -0.0470 1.0000 0.0149
-15.500 -1.3180 0.03128 0.02669 -0.0460 1.0000 0.0151
-15.250 -1.3114 0.02992 0.02524 -0.0449 1.0000 0.0154
-15.000 -1.3019 0.02879 0.02403 -0.0437 1.0000 0.0157
-14.750 -1.2918 0.02773 0.02288 -0.0426 1.0000 0.0159
-14.500 -1.2925 0.02597 0.02103 -0.0404 1.0000 0.0164
-14.250 -1.2866 0.02471 0.01969 -0.0386 1.0000 0.0167
-14.000 -1.2776 0.02367 0.01861 -0.0370 1.0000 0.0172
-13.750 -1.2662 0.02279 0.01769 -0.0355 1.0000 0.0177
-13.500 -1.2535 0.02202 0.01686 -0.0340 1.0000 0.0181
-13.250 -1.2395 0.02133 0.01612 -0.0326 1.0000 0.0187
-13.000 -1.2239 0.02076 0.01549 -0.0314 1.0000 0.0192
-12.750 -1.2080 0.02020 0.01487 -0.0301 1.0000 0.0195
-12.500 -1.1990 0.01923 0.01384 -0.0278 1.0000 0.0204
-12.250 -1.1856 0.01851 0.01310 -0.0261 1.0000 0.0212
-12.000 -1.1698 0.01795 0.01252 -0.0246 1.0000 0.0219
-11.750 -1.1441 0.01742 0.01195 -0.0251 0.9758 0.0229
-11.500 -1.1125 0.01695 0.01138 -0.0266 0.9487 0.0238
-11.250 -1.1006 0.01642 0.01073 -0.0240 0.9246 0.0250
-11.000 -1.0867 0.01597 0.01022 -0.0217 0.9121 0.0264
-10.750 -1.0689 0.01563 0.00983 -0.0202 0.9041 0.0276
-10.500 -1.0489 0.01534 0.00947 -0.0190 0.8978 0.0288
-10.250 -1.0295 0.01490 0.00897 -0.0177 0.8926 0.0304
-10.000 -1.0091 0.01448 0.00855 -0.0167 0.8879 0.0325
-9.750 -0.9870 0.01419 0.00823 -0.0158 0.8839 0.0343
-9.500 -0.9639 0.01399 0.00796 -0.0151 0.8802 0.0355
-9.250 -0.9432 0.01350 0.00747 -0.0141 0.8771 0.0386
-9.000 -0.9200 0.01319 0.00716 -0.0135 0.8741 0.0408
-8.750 -0.8958 0.01297 0.00689 -0.0130 0.8712 0.0425
-8.500 -0.8733 0.01261 0.00651 -0.0122 0.8683 0.0454
-8.250 -0.8498 0.01233 0.00623 -0.0115 0.8657 0.0483
-8.000 -0.8251 0.01213 0.00600 -0.0111 0.8634 0.0507
-7.750 -0.8008 0.01183 0.00570 -0.0106 0.8615 0.0537
-7.500 -0.7765 0.01154 0.00543 -0.0101 0.8594 0.0573
-7.250 -0.7512 0.01133 0.00521 -0.0097 0.8575 0.0602
-7.000 -0.7263 0.01109 0.00496 -0.0093 0.8556 0.0639
-6.750 -0.7014 0.01083 0.00473 -0.0089 0.8538 0.0688
-6.500 -0.6755 0.01067 0.00455 -0.0086 0.8521 0.0722
-6.250 -0.6507 0.01041 0.00431 -0.0082 0.8504 0.0786
-6.000 -0.6249 0.01024 0.00414 -0.0079 0.8485 0.0835
-5.750 -0.5991 0.01002 0.00395 -0.0076 0.8470 0.0900
-5.500 -0.5730 0.00983 0.00378 -0.0073 0.8455 0.0968
-5.250 -0.5471 0.00961 0.00361 -0.0071 0.8441 0.1051
-5.000 -0.5206 0.00944 0.00346 -0.0069 0.8427 0.1129
-4.750 -0.4946 0.00923 0.00330 -0.0067 0.8412 0.1242
-4.500 -0.4684 0.00903 0.00316 -0.0064 0.8398 0.1363
-4.250 -0.4422 0.00883 0.00302 -0.0062 0.8383 0.1505
-4.000 -0.4161 0.00863 0.00288 -0.0060 0.8368 0.1676
-3.750 -0.3898 0.00844 0.00276 -0.0057 0.8354 0.1867
-3.500 -0.3641 0.00821 0.00265 -0.0054 0.8341 0.2130
-3.250 -0.3386 0.00799 0.00255 -0.0051 0.8325 0.2473
-3.000 -0.3134 0.00768 0.00243 -0.0048 0.8312 0.2897
-2.750 -0.2889 0.00731 0.00230 -0.0043 0.8297 0.3475
-2.500 -0.2653 0.00687 0.00216 -0.0037 0.8281 0.4223
-2.250 -0.2425 0.00636 0.00200 -0.0030 0.8262 0.5106
-2.000 -0.2218 0.00573 0.00184 -0.0018 0.8242 0.6292
-1.750 -0.1974 0.00549 0.00186 -0.0009 0.8215 0.7077
-1.500 -0.1701 0.00550 0.00188 -0.0006 0.8163 0.7313
-1.250 -0.1423 0.00541 0.00180 -0.0003 0.8084 0.7457
-1.000 -0.1144 0.00541 0.00173 0.0000 0.8004 0.7558
-0.750 -0.0859 0.00538 0.00172 0.0000 0.7953 0.7639
-0.500 -0.0572 0.00537 0.00169 0.0000 0.7905 0.7699
-0.250 -0.0288 0.00537 0.00170 0.0001 0.7859 0.7759
0.000 0.0000 0.00539 0.00172 0.0000 0.7816 0.7815
0.250 0.0288 0.00537 0.00170 0.0000 0.7759 0.7860
0.500 0.0572 0.00537 0.00169 0.0000 0.7700 0.7905
0.750 0.0859 0.00538 0.00173 0.0000 0.7639 0.7954
1.000 0.1144 0.00541 0.00173 0.0000 0.7558 0.8004
1.250 0.1423 0.00541 0.00180 0.0003 0.7456 0.8084
1.500 0.1701 0.00550 0.00188 0.0006 0.7312 0.8163
1.750 0.1974 0.00549 0.00186 0.0009 0.7077 0.8215
2.250 0.2425 0.00636 0.00200 0.0030 0.5105 0.8262
2.500 0.2653 0.00687 0.00216 0.0037 0.4226 0.8281
2.750 0.2888 0.00732 0.00231 0.0044 0.3463 0.8298
3.000 0.3134 0.00768 0.00243 0.0048 0.2896 0.8312
3.250 0.3386 0.00799 0.00256 0.0051 0.2469 0.8324
3.500 0.3641 0.00822 0.00265 0.0054 0.2125 0.8341
3.750 0.3898 0.00844 0.00276 0.0057 0.1867 0.8354
4.000 0.4161 0.00863 0.00288 0.0060 0.1675 0.8368
4.250 0.4422 0.00883 0.00302 0.0062 0.1506 0.8383
4.500 0.4684 0.00903 0.00316 0.0064 0.1362 0.8398
4.750 0.4946 0.00923 0.00330 0.0067 0.1243 0.8412
5.000 0.5206 0.00944 0.00346 0.0069 0.1129 0.8427
5.250 0.5471 0.00961 0.00361 0.0071 0.1051 0.8441
5.500 0.5730 0.00983 0.00378 0.0074 0.0967 0.8455
5.750 0.5992 0.01002 0.00395 0.0076 0.0901 0.8470
6.000 0.6249 0.01024 0.00414 0.0079 0.0835 0.8485
6.250 0.6507 0.01041 0.00431 0.0082 0.0786 0.8504
6.500 0.6754 0.01067 0.00455 0.0086 0.0722 0.8521
6.750 0.7014 0.01083 0.00473 0.0089 0.0689 0.8538
7.000 0.7262 0.01109 0.00496 0.0093 0.0638 0.8556
7.250 0.7512 0.01133 0.00521 0.0097 0.0602 0.8575
7.500 0.7765 0.01154 0.00544 0.0101 0.0573 0.8594
7.750 0.8009 0.01183 0.00570 0.0106 0.0537 0.8615
8.000 0.8251 0.01213 0.00600 0.0111 0.0507 0.8633
8.250 0.8499 0.01232 0.00623 0.0115 0.0483 0.8657
8.500 0.8733 0.01261 0.00651 0.0122 0.0454 0.8683
8.750 0.8958 0.01297 0.00690 0.0130 0.0425 0.8712
9.000 0.9200 0.01319 0.00716 0.0135 0.0408 0.8741
9.250 0.9432 0.01349 0.00746 0.0141 0.0385 0.8771
9.500 0.9639 0.01398 0.00795 0.0151 0.0356 0.8802
9.750 0.9870 0.01420 0.00823 0.0158 0.0344 0.8839
10.000 1.0090 0.01448 0.00855 0.0167 0.0325 0.8879
10.250 1.0295 0.01490 0.00897 0.0177 0.0304 0.8926
10.500 1.0489 0.01533 0.00946 0.0190 0.0288 0.8978
10.750 1.0690 0.01563 0.00984 0.0202 0.0276 0.9041
11.000 1.0868 0.01598 0.01023 0.0217 0.0264 0.9122
11.250 1.1010 0.01641 0.01072 0.0239 0.0251 0.9246
11.500 1.1124 0.01697 0.01141 0.0266 0.0239 0.9492
11.750 1.1443 0.01743 0.01195 0.0250 0.0229 0.9758
12.000 1.1699 0.01795 0.01252 0.0246 0.0220 1.0000
12.250 1.1859 0.01851 0.01309 0.0261 0.0212 1.0000
12.500 1.1989 0.01925 0.01385 0.0278 0.0203 1.0000
12.750 1.2084 0.02019 0.01486 0.0300 0.0195 1.0000
13.000 1.2238 0.02078 0.01551 0.0314 0.0192 1.0000
13.250 1.2398 0.02133 0.01612 0.0326 0.0186 1.0000
13.500 1.2535 0.02204 0.01688 0.0340 0.0181 1.0000
13.750 1.2655 0.02286 0.01776 0.0356 0.0178 1.0000
14.000 1.2780 0.02366 0.01860 0.0370 0.0173 1.0000
14.250 1.2875 0.02466 0.01966 0.0385 0.0169 1.0000
14.500 1.2926 0.02599 0.02105 0.0404 0.0163 1.0000
14.750 1.2908 0.02783 0.02298 0.0426 0.0159 1.0000
15.000 1.3024 0.02878 0.02402 0.0437 0.0157 1.0000
15.250 1.3104 0.03002 0.02534 0.0449 0.0154 1.0000
15.500 1.3198 0.03118 0.02658 0.0459 0.0151 1.0000
15.750 1.3224 0.03290 0.02839 0.0471 0.0149 1.0000
16.000 1.3274 0.03450 0.03008 0.0480 0.0147 1.0000
16.250 1.3322 0.03617 0.03182 0.0488 0.0143 1.0000
16.500 1.3340 0.03819 0.03392 0.0494 0.0141 1.0000
16.750 1.3337 0.04050 0.03632 0.0497 0.0139 1.0000
17.000 1.3309 0.04323 0.03914 0.0498 0.0137 1.0000
17.250 1.3246 0.04656 0.04257 0.0493 0.0135 1.0000
17.500 1.3146 0.05068 0.04681 0.0481 0.0133 1.0000
17.750 1.3009 0.05573 0.05200 0.0460 0.0132 1.0000
18.000 1.2797 0.06247 0.05890 0.0424 0.0131 1.0000
18.250 1.2588 0.06980 0.06639 0.0381 0.0131 1.0000
18.500 1.2348 0.07807 0.07482 0.0332 0.0131 1.0000
18.750 1.2001 0.08847 0.08540 0.0270 0.0131 1.0000
19.000 1.1660 0.09888 0.09597 0.0209 0.0132 1.0000
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