NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il) Reynolds number: 500,000 Max Cl/Cd: 58.59 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20012-il-500000-n5.txt Download as CSV file: xf-sc20012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0012 AIRFOIL
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 -1.0927 0.12691 0.12365 0.0111 1.0000 0.0157
-18.000 -1.1348 0.11395 0.11052 0.0038 1.0000 0.0156
-17.750 -1.1741 0.10192 0.09831 -0.0030 1.0000 0.0156
-17.500 -1.2078 0.09104 0.08723 -0.0092 1.0000 0.0155
-17.250 -1.2359 0.08145 0.07745 -0.0149 1.0000 0.0155
-17.000 -1.2579 0.07332 0.06913 -0.0197 1.0000 0.0155
-16.750 -1.2753 0.06654 0.06218 -0.0234 1.0000 0.0156
-16.500 -1.2891 0.06089 0.05636 -0.0262 1.0000 0.0156
-16.250 -1.2995 0.05613 0.05144 -0.0281 1.0000 0.0156
-16.000 -1.3072 0.05208 0.04723 -0.0293 1.0000 0.0157
-15.750 -1.3122 0.04856 0.04356 -0.0299 1.0000 0.0158
-15.500 -1.3149 0.04548 0.04034 -0.0302 1.0000 0.0158
-15.250 -1.3177 0.04253 0.03727 -0.0302 1.0000 0.0159
-15.000 -1.3193 0.03984 0.03447 -0.0299 1.0000 0.0161
-14.750 -1.3185 0.03750 0.03202 -0.0294 1.0000 0.0162
-14.500 -1.3154 0.03545 0.02988 -0.0286 1.0000 0.0163
-14.250 -1.3105 0.03365 0.02799 -0.0277 1.0000 0.0165
-14.000 -1.3041 0.03205 0.02630 -0.0266 1.0000 0.0167
-13.750 -1.2964 0.03063 0.02478 -0.0254 1.0000 0.0169
-13.500 -1.2875 0.02935 0.02341 -0.0241 1.0000 0.0171
-13.250 -1.2777 0.02817 0.02214 -0.0226 1.0000 0.0173
-13.000 -1.2672 0.02710 0.02098 -0.0210 1.0000 0.0175
-12.750 -1.2560 0.02612 0.01991 -0.0193 1.0000 0.0178
-12.500 -1.2443 0.02522 0.01893 -0.0174 1.0000 0.0181
-12.250 -1.2318 0.02440 0.01802 -0.0155 1.0000 0.0184
-12.000 -1.2166 0.02361 0.01714 -0.0140 1.0000 0.0187
-11.750 -1.1995 0.02287 0.01632 -0.0128 1.0000 0.0190
-11.500 -1.1826 0.02205 0.01547 -0.0115 1.0000 0.0194
-11.250 -1.1638 0.02136 0.01474 -0.0105 1.0000 0.0200
-11.000 -1.1438 0.02073 0.01406 -0.0095 1.0000 0.0206
-10.750 -1.1233 0.02013 0.01341 -0.0087 1.0000 0.0213
-10.500 -1.1022 0.01955 0.01276 -0.0079 1.0000 0.0219
-10.250 -1.0808 0.01897 0.01213 -0.0071 1.0000 0.0226
-10.000 -1.0591 0.01840 0.01154 -0.0064 1.0000 0.0235
-9.750 -1.0366 0.01789 0.01102 -0.0057 1.0000 0.0245
-9.500 -1.0137 0.01742 0.01050 -0.0051 1.0000 0.0256
-9.250 -0.9906 0.01695 0.01000 -0.0045 1.0000 0.0268
-9.000 -0.9672 0.01651 0.00956 -0.0039 1.0000 0.0282
-8.750 -0.9434 0.01611 0.00914 -0.0034 1.0000 0.0297
-8.500 -0.9195 0.01572 0.00871 -0.0029 1.0000 0.0312
-8.250 -0.8956 0.01534 0.00835 -0.0024 1.0000 0.0329
-8.000 -0.8713 0.01501 0.00800 -0.0019 1.0000 0.0347
-7.750 -0.8421 0.01465 0.00762 -0.0025 0.9910 0.0366
-7.500 -0.8109 0.01430 0.00728 -0.0035 0.9777 0.0388
-7.250 -0.7799 0.01401 0.00695 -0.0044 0.9629 0.0410
-7.000 -0.7509 0.01366 0.00659 -0.0048 0.9459 0.0430
-6.750 -0.7242 0.01339 0.00629 -0.0047 0.9273 0.0450
-6.500 -0.6990 0.01317 0.00600 -0.0041 0.9088 0.0470
-6.250 -0.6744 0.01292 0.00570 -0.0035 0.8916 0.0491
-6.000 -0.6494 0.01268 0.00543 -0.0029 0.8765 0.0519
-5.500 -0.5978 0.01224 0.00490 -0.0021 0.8523 0.0577
-5.250 -0.5717 0.01202 0.00465 -0.0018 0.8428 0.0607
-5.000 -0.5448 0.01182 0.00441 -0.0016 0.8340 0.0635
-4.500 -0.4913 0.01138 0.00395 -0.0013 0.8198 0.0725
-4.250 -0.4643 0.01116 0.00374 -0.0012 0.8134 0.0790
-4.000 -0.4372 0.01095 0.00355 -0.0011 0.8079 0.0879
-3.750 -0.4099 0.01073 0.00337 -0.0010 0.8030 0.1003
-3.500 -0.3824 0.01050 0.00320 -0.0010 0.7982 0.1151
-3.250 -0.3551 0.01028 0.00304 -0.0010 0.7938 0.1329
-3.000 -0.3280 0.01002 0.00288 -0.0009 0.7896 0.1595
-2.750 -0.3009 0.00972 0.00272 -0.0009 0.7853 0.1951
-2.500 -0.2738 0.00940 0.00257 -0.0009 0.7807 0.2387
-2.250 -0.2472 0.00901 0.00241 -0.0009 0.7766 0.2967
-2.000 -0.2211 0.00853 0.00224 -0.0008 0.7731 0.3775
-1.750 -0.1953 0.00804 0.00207 -0.0006 0.7699 0.4661
-1.500 -0.1700 0.00750 0.00198 -0.0003 0.7664 0.5738
-1.250 -0.1428 0.00733 0.00204 -0.0001 0.7613 0.6419
-1.000 -0.1144 0.00731 0.00205 0.0000 0.7545 0.6670
-0.750 -0.0860 0.00731 0.00206 0.0000 0.7477 0.6877
-0.500 -0.0574 0.00729 0.00208 0.0000 0.7400 0.7038
-0.250 -0.0287 0.00732 0.00206 0.0000 0.7321 0.7139
0.000 0.0000 0.00729 0.00207 0.0000 0.7234 0.7234
0.250 0.0287 0.00732 0.00206 0.0000 0.7138 0.7322
0.500 0.0574 0.00729 0.00208 0.0000 0.7037 0.7401
0.750 0.0860 0.00731 0.00206 0.0000 0.6883 0.7478
1.000 0.1144 0.00731 0.00205 0.0000 0.6672 0.7547
1.250 0.1427 0.00733 0.00204 0.0001 0.6414 0.7615
1.500 0.1700 0.00750 0.00198 0.0003 0.5739 0.7664
1.750 0.1953 0.00804 0.00207 0.0006 0.4663 0.7699
2.000 0.2211 0.00853 0.00224 0.0008 0.3778 0.7731
2.250 0.2472 0.00901 0.00241 0.0009 0.2969 0.7766
2.500 0.2738 0.00940 0.00257 0.0009 0.2389 0.7807
2.750 0.3009 0.00972 0.00272 0.0009 0.1950 0.7853
3.000 0.3280 0.01002 0.00288 0.0009 0.1596 0.7896
3.250 0.3551 0.01028 0.00304 0.0010 0.1326 0.7938
3.500 0.3825 0.01050 0.00320 0.0010 0.1151 0.7982
3.750 0.4099 0.01073 0.00337 0.0010 0.1002 0.8030
4.000 0.4372 0.01096 0.00355 0.0011 0.0879 0.8079
4.250 0.4643 0.01115 0.00374 0.0012 0.0790 0.8134
4.500 0.4913 0.01138 0.00395 0.0013 0.0725 0.8198
5.000 0.5449 0.01182 0.00441 0.0016 0.0635 0.8340
5.250 0.5717 0.01202 0.00465 0.0018 0.0607 0.8428
5.500 0.5978 0.01224 0.00490 0.0021 0.0576 0.8523
6.000 0.6494 0.01268 0.00543 0.0029 0.0519 0.8765
6.250 0.6744 0.01292 0.00570 0.0034 0.0491 0.8916
6.500 0.6991 0.01316 0.00600 0.0041 0.0469 0.9087
6.750 0.7243 0.01339 0.00629 0.0047 0.0450 0.9273
7.000 0.7510 0.01366 0.00659 0.0048 0.0430 0.9459
7.250 0.7799 0.01400 0.00694 0.0044 0.0409 0.9630
7.500 0.8110 0.01430 0.00728 0.0035 0.0388 0.9778
7.750 0.8422 0.01465 0.00762 0.0025 0.0366 0.9911
8.000 0.8714 0.01501 0.00800 0.0019 0.0347 1.0000
8.250 0.8956 0.01534 0.00835 0.0024 0.0329 1.0000
8.500 0.9196 0.01572 0.00871 0.0029 0.0312 1.0000
8.750 0.9435 0.01611 0.00914 0.0034 0.0297 1.0000
9.000 0.9673 0.01651 0.00956 0.0039 0.0282 1.0000
9.250 0.9907 0.01695 0.00999 0.0045 0.0268 1.0000
9.500 1.0138 0.01742 0.01050 0.0051 0.0256 1.0000
9.750 1.0367 0.01789 0.01102 0.0057 0.0245 1.0000
10.000 1.0593 0.01840 0.01154 0.0063 0.0235 1.0000
10.250 1.0809 0.01897 0.01213 0.0071 0.0226 1.0000
10.500 1.1024 0.01955 0.01276 0.0078 0.0219 1.0000
10.750 1.1234 0.02013 0.01341 0.0087 0.0212 1.0000
11.000 1.1440 0.02073 0.01406 0.0095 0.0206 1.0000
11.250 1.1640 0.02136 0.01474 0.0104 0.0200 1.0000
11.500 1.1829 0.02205 0.01546 0.0114 0.0194 1.0000
11.750 1.1998 0.02287 0.01632 0.0127 0.0190 1.0000
12.000 1.2169 0.02361 0.01714 0.0139 0.0187 1.0000
12.250 1.2323 0.02440 0.01802 0.0154 0.0183 1.0000
12.500 1.2448 0.02522 0.01893 0.0173 0.0181 1.0000
12.750 1.2566 0.02612 0.01991 0.0192 0.0178 1.0000
13.000 1.2678 0.02710 0.02098 0.0209 0.0175 1.0000
13.250 1.2784 0.02817 0.02214 0.0225 0.0173 1.0000
13.500 1.2882 0.02934 0.02340 0.0239 0.0171 1.0000
13.750 1.2972 0.03062 0.02477 0.0253 0.0169 1.0000
14.000 1.3050 0.03204 0.02629 0.0265 0.0167 1.0000
14.250 1.3115 0.03364 0.02798 0.0275 0.0165 1.0000
14.500 1.3164 0.03543 0.02986 0.0285 0.0163 1.0000
14.750 1.3195 0.03748 0.03201 0.0292 0.0162 1.0000
15.000 1.3205 0.03981 0.03445 0.0297 0.0161 1.0000
15.250 1.3190 0.04250 0.03724 0.0300 0.0159 1.0000
15.500 1.3163 0.04544 0.04030 0.0300 0.0158 1.0000
15.750 1.3137 0.04851 0.04352 0.0297 0.0158 1.0000
16.000 1.3089 0.05202 0.04718 0.0290 0.0157 1.0000
16.250 1.3013 0.05607 0.05137 0.0279 0.0156 1.0000
16.500 1.2909 0.06083 0.05630 0.0260 0.0156 1.0000
16.750 1.2772 0.06647 0.06211 0.0232 0.0156 1.0000
17.000 1.2599 0.07324 0.06905 0.0194 0.0155 1.0000
17.250 1.2379 0.08139 0.07739 0.0146 0.0155 1.0000
17.500 1.2099 0.09097 0.08716 0.0090 0.0155 1.0000
17.750 1.1761 0.10189 0.09828 0.0027 0.0156 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0012 AIRFOIL (sc20012-il)