S1012 (s1012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 50,000 Max Cl/Cd: 25.54 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1012-il-50000-n5.txt Download as CSV file: xf-s1012-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6653 0.09990 0.09214 -0.0281 1.0000 0.0808
-12.000 -0.7025 0.08749 0.07974 -0.0364 1.0000 0.0805
-11.750 -0.7467 0.07740 0.06957 -0.0424 1.0000 0.0795
-11.500 -0.7848 0.07041 0.06243 -0.0447 1.0000 0.0790
-11.250 -0.8147 0.06535 0.05719 -0.0446 1.0000 0.0791
-11.000 -0.8385 0.06141 0.05304 -0.0429 1.0000 0.0797
-10.750 -0.8584 0.05811 0.04950 -0.0401 1.0000 0.0807
-10.500 -0.8740 0.05486 0.04592 -0.0371 1.0000 0.0823
-10.250 -0.8869 0.05163 0.04221 -0.0339 1.0000 0.0841
-10.000 -0.8792 0.04956 0.04008 -0.0323 1.0000 0.0867
-9.750 -0.8707 0.04769 0.03810 -0.0305 1.0000 0.0893
-9.500 -0.8649 0.04567 0.03585 -0.0283 1.0000 0.0925
-9.250 -0.8619 0.04348 0.03324 -0.0255 1.0000 0.0963
-9.000 -0.8524 0.04171 0.03133 -0.0234 1.0000 0.0998
-8.750 -0.8406 0.04033 0.02987 -0.0213 1.0000 0.1033
-8.500 -0.8320 0.03890 0.02820 -0.0187 1.0000 0.1079
-8.250 -0.8230 0.03743 0.02644 -0.0160 1.0000 0.1126
-8.000 -0.8097 0.03633 0.02537 -0.0140 1.0000 0.1170
-7.750 -0.7972 0.03515 0.02400 -0.0117 1.0000 0.1224
-7.500 -0.7836 0.03402 0.02271 -0.0096 1.0000 0.1283
-7.250 -0.7691 0.03308 0.02174 -0.0076 1.0000 0.1346
-7.000 -0.7521 0.03204 0.02048 -0.0059 1.0000 0.1417
-6.750 -0.7358 0.03120 0.01969 -0.0041 1.0000 0.1493
-6.500 -0.7174 0.03034 0.01872 -0.0026 1.0000 0.1583
-6.250 -0.6990 0.02957 0.01790 -0.0011 1.0000 0.1679
-6.000 -0.6808 0.02884 0.01718 0.0004 1.0000 0.1790
-5.750 -0.6624 0.02814 0.01646 0.0020 1.0000 0.1913
-5.500 -0.6458 0.02746 0.01579 0.0037 1.0000 0.2057
-5.250 -0.6305 0.02679 0.01516 0.0057 1.0000 0.2219
-5.000 -0.6163 0.02610 0.01456 0.0078 1.0000 0.2408
-4.750 -0.6029 0.02542 0.01396 0.0100 1.0000 0.2652
-4.500 -0.5912 0.02465 0.01341 0.0124 1.0000 0.2947
-4.000 -0.5718 0.02287 0.01236 0.0180 1.0000 0.3989
-3.750 -0.5628 0.02204 0.01227 0.0217 1.0000 0.5016
-3.500 -0.5244 0.02320 0.01431 0.0240 1.0000 0.6647
-3.250 -0.5173 0.02346 0.01445 0.0284 1.0000 0.7287
-3.000 -0.5108 0.02364 0.01447 0.0327 1.0000 0.7713
-2.750 -0.4951 0.02407 0.01477 0.0359 1.0000 0.8039
-2.500 -0.4773 0.02447 0.01504 0.0387 1.0000 0.8321
-2.250 -0.4422 0.02516 0.01558 0.0387 1.0000 0.8565
-2.000 -0.4129 0.02560 0.01588 0.0392 1.0000 0.8799
-1.750 -0.3521 0.02641 0.01651 0.0342 1.0000 0.9019
-1.500 -0.2846 0.02709 0.01701 0.0274 1.0000 0.9265
-1.250 -0.2119 0.02743 0.01720 0.0191 1.0000 0.9454
-1.000 -0.1668 0.02745 0.01713 0.0151 1.0000 0.9587
-0.750 -0.1296 0.02742 0.01703 0.0124 0.9998 0.9691
-0.500 -0.0837 0.02733 0.01689 0.0078 0.9962 0.9756
-0.250 -0.0431 0.02736 0.01689 0.0042 0.9921 0.9823
0.000 0.0001 0.02728 0.01680 0.0000 0.9872 0.9872
0.250 0.0432 0.02736 0.01688 -0.0042 0.9823 0.9921
0.500 0.0837 0.02733 0.01689 -0.0078 0.9756 0.9962
0.750 0.1296 0.02742 0.01702 -0.0124 0.9692 0.9998
1.000 0.1667 0.02745 0.01713 -0.0151 0.9588 1.0000
1.250 0.2118 0.02742 0.01720 -0.0191 0.9455 1.0000
1.500 0.2843 0.02708 0.01701 -0.0274 0.9265 1.0000
1.750 0.3517 0.02641 0.01651 -0.0341 0.9021 1.0000
2.000 0.4124 0.02560 0.01588 -0.0391 0.8800 1.0000
2.250 0.4423 0.02515 0.01557 -0.0387 0.8564 1.0000
2.500 0.4773 0.02447 0.01505 -0.0387 0.8323 1.0000
2.750 0.4951 0.02407 0.01477 -0.0359 0.8040 1.0000
3.000 0.5107 0.02364 0.01448 -0.0327 0.7716 1.0000
3.250 0.5174 0.02346 0.01444 -0.0285 0.7294 1.0000
3.500 0.5245 0.02319 0.01429 -0.0240 0.6642 1.0000
3.750 0.5627 0.02203 0.01227 -0.0217 0.5017 1.0000
4.000 0.5717 0.02287 0.01236 -0.0180 0.3989 1.0000
4.250 0.5808 0.02380 0.01286 -0.0150 0.3362 1.0000
4.500 0.5912 0.02464 0.01341 -0.0124 0.2947 1.0000
4.750 0.6029 0.02541 0.01396 -0.0100 0.2652 1.0000
5.000 0.6162 0.02610 0.01456 -0.0077 0.2406 1.0000
5.250 0.6305 0.02679 0.01516 -0.0057 0.2220 1.0000
5.500 0.6457 0.02746 0.01579 -0.0037 0.2055 1.0000
5.750 0.6624 0.02813 0.01645 -0.0020 0.1914 1.0000
6.000 0.6807 0.02883 0.01718 -0.0004 0.1789 1.0000
6.250 0.6989 0.02957 0.01789 0.0011 0.1679 1.0000
6.500 0.7174 0.03034 0.01872 0.0026 0.1583 1.0000
6.750 0.7358 0.03119 0.01968 0.0041 0.1493 1.0000
7.000 0.7520 0.03204 0.02047 0.0059 0.1417 1.0000
7.250 0.7690 0.03308 0.02173 0.0076 0.1345 1.0000
7.500 0.7836 0.03402 0.02270 0.0096 0.1283 1.0000
7.750 0.7974 0.03516 0.02401 0.0117 0.1225 1.0000
8.000 0.8096 0.03632 0.02537 0.0140 0.1170 1.0000
8.250 0.8230 0.03742 0.02644 0.0161 0.1127 1.0000
8.500 0.8319 0.03890 0.02820 0.0187 0.1078 1.0000
8.750 0.8407 0.04034 0.02988 0.0213 0.1034 1.0000
9.000 0.8524 0.04170 0.03131 0.0234 0.0997 1.0000
9.250 0.8619 0.04348 0.03325 0.0255 0.0963 1.0000
9.500 0.8650 0.04567 0.03585 0.0283 0.0926 1.0000
9.750 0.8708 0.04769 0.03810 0.0305 0.0893 1.0000
10.000 0.8795 0.04954 0.04006 0.0322 0.0866 1.0000
10.250 0.8869 0.05162 0.04220 0.0339 0.0841 1.0000
10.500 0.8742 0.05487 0.04593 0.0371 0.0823 1.0000
10.750 0.8585 0.05813 0.04952 0.0401 0.0807 1.0000
11.000 0.8387 0.06141 0.05303 0.0429 0.0797 1.0000
11.250 0.8151 0.06536 0.05719 0.0446 0.0791 1.0000
11.500 0.7850 0.07044 0.06246 0.0446 0.0790 1.0000
11.750 0.7470 0.07745 0.06962 0.0423 0.0795 1.0000
12.000 0.7033 0.08747 0.07972 0.0363 0.0805 1.0000
12.250 0.6657 0.10003 0.09226 0.0279 0.0808 1.0000
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Polar data table (+)
Polar graphs
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