NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.11 at α=-0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20710-il-1000000.txt Download as CSV file: xf-sc20710-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9616 0.07910 0.07673 -0.0477 1.0000 0.0141
-16.000 -1.0135 0.06418 0.06152 -0.0581 1.0000 0.0139
-15.750 -1.0374 0.05639 0.05354 -0.0633 1.0000 0.0139
-15.500 -1.0542 0.05073 0.04772 -0.0664 1.0000 0.0140
-15.250 -1.0667 0.04629 0.04313 -0.0682 1.0000 0.0140
-15.000 -1.0754 0.04279 0.03950 -0.0691 1.0000 0.0141
-14.750 -1.0828 0.03978 0.03637 -0.0691 1.0000 0.0142
-14.500 -1.0887 0.03724 0.03372 -0.0685 1.0000 0.0142
-14.250 -1.0947 0.03506 0.03142 -0.0672 1.0000 0.0143
-14.000 -1.1026 0.03323 0.02949 -0.0648 1.0000 0.0144
-13.750 -1.1163 0.03181 0.02800 -0.0606 1.0000 0.0145
-13.500 -1.1195 0.03030 0.02638 -0.0582 1.0000 0.0146
-13.250 -1.1148 0.02888 0.02486 -0.0571 1.0000 0.0148
-13.000 -1.1049 0.02759 0.02347 -0.0565 1.0000 0.0150
-12.750 -1.0919 0.02626 0.02203 -0.0564 1.0000 0.0152
-12.500 -1.0765 0.02498 0.02062 -0.0563 1.0000 0.0153
-12.250 -1.0562 0.02376 0.01928 -0.0568 0.9998 0.0155
-12.000 -1.0278 0.02258 0.01796 -0.0587 0.9990 0.0156
-11.750 -0.9986 0.02156 0.01683 -0.0604 0.9983 0.0158
-11.500 -0.9688 0.02068 0.01586 -0.0621 0.9975 0.0159
-11.250 -0.9407 0.01871 0.01372 -0.0643 0.9968 0.0164
-11.000 -0.9101 0.01762 0.01255 -0.0663 0.9961 0.0168
-10.750 -0.8785 0.01690 0.01178 -0.0681 0.9955 0.0172
-10.500 -0.8465 0.01629 0.01113 -0.0698 0.9950 0.0176
-10.250 -0.8141 0.01572 0.01051 -0.0716 0.9946 0.0181
-10.000 -0.7814 0.01518 0.00992 -0.0733 0.9942 0.0186
-9.750 -0.7499 0.01471 0.00940 -0.0747 0.9933 0.0192
-9.500 -0.7190 0.01433 0.00897 -0.0759 0.9922 0.0196
-9.250 -0.6862 0.01349 0.00808 -0.0778 0.9914 0.0206
-9.000 -0.6538 0.01303 0.00761 -0.0794 0.9905 0.0215
-8.750 -0.6212 0.01268 0.00725 -0.0809 0.9896 0.0225
-8.500 -0.5884 0.01236 0.00690 -0.0824 0.9888 0.0236
-8.250 -0.5548 0.01187 0.00639 -0.0841 0.9882 0.0255
-8.000 -0.5217 0.01158 0.00612 -0.0857 0.9876 0.0275
-7.750 -0.4888 0.01139 0.00591 -0.0870 0.9869 0.0293
-7.500 -0.4545 0.01096 0.00550 -0.0889 0.9864 0.0327
-7.250 -0.4212 0.01077 0.00531 -0.0904 0.9859 0.0351
-7.000 -0.3870 0.01045 0.00499 -0.0921 0.9855 0.0382
-6.750 -0.3532 0.01023 0.00480 -0.0937 0.9851 0.0411
-6.500 -0.3194 0.01007 0.00463 -0.0952 0.9846 0.0431
-6.250 -0.2846 0.00977 0.00435 -0.0971 0.9843 0.0475
-6.000 -0.2504 0.00959 0.00418 -0.0987 0.9840 0.0512
-5.750 -0.2157 0.00935 0.00398 -0.1004 0.9837 0.0574
-5.500 -0.1863 0.00916 0.00383 -0.1010 0.9818 0.0653
-5.250 -0.1543 0.00892 0.00366 -0.1022 0.9802 0.0791
-5.000 -0.1205 0.00865 0.00350 -0.1037 0.9791 0.1016
-4.750 -0.0855 0.00834 0.00334 -0.1057 0.9784 0.1368
-4.500 -0.0493 0.00795 0.00318 -0.1080 0.9779 0.1943
-4.250 -0.0116 0.00745 0.00303 -0.1108 0.9777 0.2839
-4.000 0.0276 0.00688 0.00287 -0.1140 0.9779 0.4000
-3.750 0.0680 0.00631 0.00275 -0.1174 0.9782 0.5323
-3.500 0.1041 0.00613 0.00270 -0.1193 0.9770 0.5797
-3.250 0.1409 0.00600 0.00261 -0.1211 0.9758 0.6033
-3.000 0.1785 0.00586 0.00252 -0.1232 0.9748 0.6217
-2.750 0.2181 0.00567 0.00234 -0.1255 0.9732 0.6347
-2.500 0.2523 0.00546 0.00215 -0.1265 0.9676 0.6434
-2.250 0.2844 0.00534 0.00206 -0.1272 0.9623 0.6531
-2.000 0.3165 0.00528 0.00198 -0.1277 0.9562 0.6632
-1.750 0.3450 0.00520 0.00193 -0.1275 0.9456 0.6687
-1.500 0.3735 0.00517 0.00188 -0.1273 0.9330 0.6724
-1.250 0.4019 0.00516 0.00183 -0.1271 0.9172 0.6755
-1.000 0.4302 0.00519 0.00180 -0.1268 0.8990 0.6794
-0.750 0.4577 0.00525 0.00184 -0.1264 0.8758 0.6842
-0.500 0.4848 0.00538 0.00187 -0.1259 0.8427 0.6885
-0.250 0.5065 0.00599 0.00195 -0.1242 0.7177 0.6930
0.000 0.5251 0.00711 0.00227 -0.1223 0.5279 0.6972
0.250 0.5472 0.00801 0.00257 -0.1213 0.3768 0.7007
0.500 0.5714 0.00871 0.00281 -0.1207 0.2615 0.7034
0.750 0.5971 0.00925 0.00301 -0.1203 0.1815 0.7057
1.000 0.6235 0.00970 0.00320 -0.1201 0.1253 0.7078
1.250 0.6507 0.01003 0.00338 -0.1199 0.0946 0.7097
1.500 0.6780 0.01029 0.00355 -0.1198 0.0745 0.7120
1.750 0.7054 0.01054 0.00373 -0.1196 0.0627 0.7141
2.000 0.7328 0.01076 0.00395 -0.1194 0.0553 0.7162
2.250 0.7601 0.01103 0.00417 -0.1192 0.0492 0.7183
2.500 0.7877 0.01123 0.00437 -0.1190 0.0462 0.7204
2.750 0.8153 0.01144 0.00458 -0.1189 0.0432 0.7228
3.000 0.8422 0.01178 0.00489 -0.1186 0.0395 0.7250
3.250 0.8699 0.01196 0.00507 -0.1185 0.0379 0.7270
3.500 0.8971 0.01216 0.00528 -0.1183 0.0356 0.7291
3.750 0.9232 0.01256 0.00568 -0.1178 0.0324 0.7310
4.000 0.9505 0.01274 0.00589 -0.1176 0.0307 0.7330
4.250 0.9772 0.01301 0.00614 -0.1173 0.0284 0.7351
4.500 1.0033 0.01340 0.00654 -0.1169 0.0260 0.7372
4.750 1.0302 0.01365 0.00681 -0.1166 0.0244 0.7394
5.000 1.0565 0.01399 0.00712 -0.1162 0.0229 0.7414
5.250 1.0817 0.01451 0.00768 -0.1156 0.0216 0.7433
5.500 1.1077 0.01482 0.00804 -0.1152 0.0209 0.7456
5.750 1.1334 0.01519 0.00845 -0.1146 0.0201 0.7476
6.000 1.1588 0.01557 0.00886 -0.1141 0.0194 0.7498
6.250 1.1839 0.01601 0.00933 -0.1135 0.0188 0.7522
6.500 1.2077 0.01666 0.01001 -0.1126 0.0182 0.7545
6.750 1.2300 0.01756 0.01099 -0.1115 0.0177 0.7566
7.000 1.2546 0.01806 0.01154 -0.1108 0.0174 0.7584
7.250 1.2787 0.01856 0.01212 -0.1101 0.0172 0.7607
7.500 1.3027 0.01907 0.01270 -0.1093 0.0168 0.7627
7.750 1.3262 0.01962 0.01333 -0.1084 0.0164 0.7647
8.000 1.3493 0.02022 0.01400 -0.1075 0.0161 0.7669
8.250 1.3719 0.02087 0.01472 -0.1065 0.0158 0.7691
8.500 1.3942 0.02154 0.01544 -0.1055 0.0155 0.7713
8.750 1.4159 0.02226 0.01623 -0.1044 0.0152 0.7733
9.000 1.4367 0.02307 0.01711 -0.1032 0.0150 0.7754
9.250 1.4553 0.02415 0.01829 -0.1016 0.0147 0.7775
9.500 1.4703 0.02576 0.02008 -0.0995 0.0144 0.7794
9.750 1.4810 0.02805 0.02262 -0.0968 0.0142 0.7814
10.000 1.4984 0.02904 0.02374 -0.0951 0.0141 0.7837
10.250 1.5144 0.03013 0.02496 -0.0932 0.0140 0.7861
10.500 1.5288 0.03136 0.02633 -0.0911 0.0139 0.7883
10.750 1.5413 0.03268 0.02781 -0.0888 0.0138 0.7902
11.000 1.5512 0.03412 0.02943 -0.0861 0.0137 0.7924
11.250 1.5578 0.03572 0.03121 -0.0830 0.0136 0.7945
11.500 1.5602 0.03734 0.03300 -0.0793 0.0135 0.7967
11.750 1.5570 0.03889 0.03471 -0.0746 0.0134 0.7991
12.000 1.5548 0.04064 0.03661 -0.0706 0.0133 0.8014
12.250 1.5514 0.04259 0.03872 -0.0668 0.0132 0.8036
12.500 1.5455 0.04487 0.04116 -0.0633 0.0131 0.8055
12.750 1.5380 0.04740 0.04387 -0.0601 0.0130 0.8076
13.000 1.5259 0.05059 0.04724 -0.0572 0.0129 0.8095
13.250 1.5110 0.05436 0.05121 -0.0551 0.0129 0.8112
13.500 1.4907 0.05919 0.05625 -0.0539 0.0128 0.8129
13.750 1.4677 0.06512 0.06238 -0.0546 0.0128 0.8145
14.000 1.4360 0.07375 0.07125 -0.0584 0.0128 0.8158
14.250 1.3823 0.09036 0.08820 -0.0705 0.0130 0.8164
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