NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 500,000 Max Cl/Cd: 64.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20712-il-500000-n5.txt Download as CSV file: xf-sc20712-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0712 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 -1.0340 0.09184 0.08810 -0.0469 1.0000 0.0182
-18.000 -1.0600 0.08296 0.07905 -0.0521 1.0000 0.0182
-17.750 -1.0794 0.07551 0.07144 -0.0565 1.0000 0.0182
-17.500 -1.0938 0.06919 0.06497 -0.0602 1.0000 0.0183
-17.250 -1.1044 0.06378 0.05942 -0.0633 1.0000 0.0184
-17.000 -1.1120 0.05910 0.05462 -0.0658 1.0000 0.0185
-16.750 -1.1174 0.05503 0.05043 -0.0678 1.0000 0.0187
-16.500 -1.1206 0.05145 0.04674 -0.0693 1.0000 0.0188
-16.250 -1.1224 0.04830 0.04346 -0.0704 1.0000 0.0190
-16.000 -1.1231 0.04549 0.04055 -0.0712 1.0000 0.0191
-15.750 -1.1225 0.04296 0.03791 -0.0716 1.0000 0.0193
-15.500 -1.1208 0.04068 0.03553 -0.0717 1.0000 0.0195
-15.250 -1.1183 0.03861 0.03336 -0.0716 1.0000 0.0198
-15.000 -1.1152 0.03674 0.03139 -0.0711 1.0000 0.0200
-14.750 -1.1120 0.03504 0.02960 -0.0703 1.0000 0.0202
-14.500 -1.1087 0.03351 0.02798 -0.0692 1.0000 0.0204
-14.250 -1.1053 0.03213 0.02651 -0.0678 1.0000 0.0206
-14.000 -1.1045 0.03080 0.02511 -0.0658 1.0000 0.0208
-13.750 -1.1074 0.02955 0.02382 -0.0631 1.0000 0.0211
-13.500 -1.1143 0.02853 0.02277 -0.0592 1.0000 0.0213
-13.250 -1.1155 0.02754 0.02175 -0.0563 1.0000 0.0215
-13.000 -1.1092 0.02658 0.02074 -0.0545 1.0000 0.0218
-12.750 -1.0848 0.02556 0.01967 -0.0561 0.9987 0.0224
-12.500 -1.0578 0.02458 0.01862 -0.0579 0.9971 0.0230
-12.250 -1.0299 0.02363 0.01758 -0.0599 0.9956 0.0236
-12.000 -1.0009 0.02273 0.01660 -0.0619 0.9943 0.0242
-11.750 -0.9713 0.02186 0.01564 -0.0640 0.9933 0.0247
-11.500 -0.9441 0.02092 0.01469 -0.0657 0.9915 0.0254
-11.250 -0.9149 0.02018 0.01391 -0.0674 0.9897 0.0261
-11.000 -0.8845 0.01951 0.01319 -0.0691 0.9881 0.0269
-10.750 -0.8536 0.01887 0.01250 -0.0709 0.9867 0.0278
-10.500 -0.8222 0.01829 0.01185 -0.0727 0.9855 0.0286
-10.250 -0.7905 0.01764 0.01117 -0.0746 0.9845 0.0297
-10.000 -0.7583 0.01709 0.01061 -0.0764 0.9836 0.0308
-9.750 -0.7254 0.01660 0.01010 -0.0783 0.9828 0.0321
-9.500 -0.6921 0.01614 0.00958 -0.0802 0.9821 0.0333
-9.250 -0.6637 0.01564 0.00907 -0.0810 0.9795 0.0345
-9.000 -0.6328 0.01519 0.00862 -0.0824 0.9776 0.0359
-8.750 -0.6009 0.01480 0.00822 -0.0838 0.9761 0.0376
-8.500 -0.5682 0.01444 0.00783 -0.0854 0.9747 0.0393
-8.250 -0.5347 0.01402 0.00744 -0.0872 0.9736 0.0414
-8.000 -0.5008 0.01367 0.00709 -0.0890 0.9726 0.0438
-7.750 -0.4665 0.01335 0.00675 -0.0908 0.9717 0.0462
-7.500 -0.4318 0.01297 0.00640 -0.0927 0.9710 0.0492
-7.250 -0.3970 0.01267 0.00608 -0.0946 0.9703 0.0522
-7.000 -0.3617 0.01233 0.00576 -0.0966 0.9697 0.0559
-6.750 -0.3299 0.01205 0.00550 -0.0978 0.9678 0.0598
-6.500 -0.2992 0.01178 0.00525 -0.0988 0.9650 0.0637
-6.250 -0.2663 0.01151 0.00501 -0.1002 0.9630 0.0690
-6.000 -0.2326 0.01124 0.00477 -0.1017 0.9614 0.0753
-5.750 -0.1987 0.01099 0.00455 -0.1033 0.9600 0.0828
-5.500 -0.1642 0.01071 0.00434 -0.1050 0.9587 0.0932
-5.250 -0.1293 0.01043 0.00412 -0.1069 0.9576 0.1070
-5.000 -0.0938 0.01011 0.00391 -0.1089 0.9565 0.1286
-4.750 -0.0576 0.00974 0.00370 -0.1111 0.9555 0.1633
-4.500 -0.0222 0.00928 0.00349 -0.1133 0.9535 0.2203
-4.250 0.0142 0.00875 0.00327 -0.1159 0.9513 0.2966
-4.000 0.0516 0.00826 0.00306 -0.1186 0.9496 0.3710
-3.750 0.0909 0.00772 0.00289 -0.1218 0.9481 0.4676
-3.500 0.1259 0.00749 0.00288 -0.1235 0.9460 0.5309
-3.250 0.1589 0.00742 0.00290 -0.1245 0.9438 0.5628
-3.000 0.1916 0.00738 0.00289 -0.1255 0.9417 0.5807
-2.750 0.2234 0.00737 0.00290 -0.1261 0.9383 0.5996
-2.500 0.2524 0.00736 0.00295 -0.1261 0.9313 0.6123
-2.250 0.2842 0.00730 0.00289 -0.1265 0.9233 0.6221
-2.000 0.3134 0.00728 0.00284 -0.1264 0.9102 0.6319
-1.750 0.3424 0.00726 0.00281 -0.1263 0.8957 0.6377
-1.500 0.3712 0.00727 0.00278 -0.1260 0.8779 0.6426
-1.250 0.3996 0.00731 0.00274 -0.1257 0.8519 0.6473
-1.000 0.4282 0.00739 0.00269 -0.1255 0.8203 0.6516
-0.750 0.4550 0.00754 0.00270 -0.1249 0.7797 0.6549
-0.500 0.4804 0.00784 0.00274 -0.1240 0.7152 0.6576
-0.250 0.5009 0.00863 0.00292 -0.1223 0.5818 0.6601
0.000 0.5223 0.00953 0.00321 -0.1212 0.4500 0.6624
0.250 0.5457 0.01030 0.00347 -0.1205 0.3345 0.6645
0.500 0.5708 0.01091 0.00369 -0.1201 0.2501 0.6666
0.750 0.5972 0.01137 0.00387 -0.1199 0.1931 0.6685
1.000 0.6238 0.01173 0.00407 -0.1196 0.1556 0.6704
1.250 0.6507 0.01204 0.00427 -0.1194 0.1292 0.6723
1.500 0.6779 0.01231 0.00447 -0.1192 0.1119 0.6742
1.750 0.7053 0.01256 0.00467 -0.1191 0.0983 0.6763
2.000 0.7327 0.01282 0.00487 -0.1189 0.0873 0.6785
2.250 0.7601 0.01308 0.00508 -0.1187 0.0785 0.6805
2.500 0.7874 0.01335 0.00530 -0.1186 0.0709 0.6825
2.750 0.8150 0.01358 0.00552 -0.1184 0.0656 0.6845
3.250 0.8690 0.01412 0.00601 -0.1180 0.0558 0.6881
3.500 0.8956 0.01441 0.00630 -0.1176 0.0521 0.6898
3.750 0.9223 0.01468 0.00658 -0.1173 0.0491 0.6916
4.000 0.9486 0.01501 0.00689 -0.1169 0.0461 0.6936
4.250 0.9750 0.01531 0.00720 -0.1165 0.0438 0.6956
4.500 1.0014 0.01562 0.00752 -0.1162 0.0417 0.6978
4.750 1.0273 0.01598 0.00787 -0.1157 0.0397 0.7000
5.000 1.0533 0.01633 0.00823 -0.1153 0.0381 0.7022
5.250 1.0792 0.01666 0.00858 -0.1149 0.0364 0.7043
5.500 1.1044 0.01702 0.00897 -0.1143 0.0350 0.7063
5.750 1.1290 0.01747 0.00943 -0.1136 0.0337 0.7083
6.000 1.1539 0.01786 0.00987 -0.1130 0.0327 0.7104
6.250 1.1787 0.01825 0.01031 -0.1123 0.0316 0.7128
6.500 1.2033 0.01865 0.01074 -0.1117 0.0304 0.7154
6.750 1.2275 0.01911 0.01120 -0.1110 0.0294 0.7181
7.000 1.2509 0.01965 0.01176 -0.1101 0.0284 0.7206
7.250 1.2747 0.02010 0.01228 -0.1093 0.0277 0.7226
7.500 1.2979 0.02057 0.01282 -0.1084 0.0269 0.7245
7.750 1.3208 0.02106 0.01338 -0.1075 0.0262 0.7265
8.000 1.3434 0.02157 0.01394 -0.1065 0.0255 0.7287
8.250 1.3653 0.02214 0.01454 -0.1054 0.0248 0.7310
8.500 1.3857 0.02285 0.01528 -0.1041 0.0242 0.7334
8.750 1.4072 0.02342 0.01594 -0.1030 0.0237 0.7358
9.000 1.4281 0.02403 0.01661 -0.1018 0.0232 0.7381
9.250 1.4483 0.02463 0.01729 -0.1004 0.0226 0.7401
9.500 1.4679 0.02524 0.01799 -0.0990 0.0220 0.7421
9.750 1.4868 0.02587 0.01869 -0.0975 0.0215 0.7443
10.000 1.5045 0.02656 0.01944 -0.0958 0.0211 0.7465
10.250 1.5201 0.02735 0.02029 -0.0938 0.0207 0.7491
10.500 1.5330 0.02829 0.02129 -0.0914 0.0204 0.7518
10.750 1.5456 0.02909 0.02220 -0.0888 0.0201 0.7545
11.000 1.5566 0.02995 0.02318 -0.0861 0.0198 0.7568
11.250 1.5678 0.03090 0.02425 -0.0835 0.0196 0.7590
11.500 1.5787 0.03191 0.02539 -0.0810 0.0193 0.7612
11.750 1.5887 0.03300 0.02659 -0.0785 0.0190 0.7636
12.000 1.5982 0.03413 0.02784 -0.0760 0.0187 0.7662
12.250 1.6067 0.03536 0.02917 -0.0736 0.0185 0.7689
12.500 1.6143 0.03667 0.03059 -0.0712 0.0183 0.7716
12.750 1.6211 0.03806 0.03209 -0.0688 0.0181 0.7739
13.000 1.6264 0.03958 0.03373 -0.0664 0.0179 0.7760
13.250 1.6306 0.04124 0.03551 -0.0641 0.0177 0.7783
13.500 1.6333 0.04310 0.03749 -0.0619 0.0175 0.7806
13.750 1.6340 0.04520 0.03970 -0.0599 0.0174 0.7830
14.000 1.6324 0.04762 0.04224 -0.0579 0.0172 0.7853
14.250 1.6285 0.05040 0.04514 -0.0563 0.0171 0.7875
14.500 1.6213 0.05366 0.04854 -0.0549 0.0170 0.7894
14.750 1.6158 0.05696 0.05202 -0.0540 0.0169 0.7912
15.000 1.6076 0.06079 0.05603 -0.0536 0.0168 0.7930
15.250 1.5979 0.06508 0.06051 -0.0538 0.0167 0.7950
15.500 1.5848 0.07023 0.06586 -0.0549 0.0166 0.7970
15.750 1.5694 0.07628 0.07210 -0.0570 0.0166 0.7989
16.000 1.5501 0.08357 0.07960 -0.0605 0.0165 0.8006
16.250 1.5263 0.09235 0.08860 -0.0654 0.0165 0.8020
16.500 1.4951 0.10329 0.09977 -0.0721 0.0165 0.8029
16.750 1.4553 0.11643 0.11315 -0.0803 0.0166 0.8034
17.000 1.4074 0.13174 0.12870 -0.0901 0.0166 0.8034
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