NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.06 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20614-il-1000000-n5.txt Download as CSV file: xf-sc20614-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0614 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2896 0.07658 0.07260 -0.0534 1.0000 0.0194
-19.500 -1.3005 0.07136 0.06726 -0.0560 1.0000 0.0195
-19.250 -1.3080 0.06681 0.06261 -0.0582 1.0000 0.0196
-19.000 -1.3131 0.06271 0.05841 -0.0600 1.0000 0.0197
-18.750 -1.3161 0.05901 0.05462 -0.0616 1.0000 0.0199
-18.500 -1.3170 0.05572 0.05123 -0.0629 1.0000 0.0200
-18.250 -1.3161 0.05274 0.04817 -0.0640 1.0000 0.0201
-18.000 -1.3139 0.04998 0.04533 -0.0649 1.0000 0.0203
-17.750 -1.3104 0.04746 0.04273 -0.0656 1.0000 0.0204
-17.500 -1.3060 0.04511 0.04030 -0.0662 1.0000 0.0205
-17.250 -1.3004 0.04295 0.03807 -0.0667 1.0000 0.0206
-17.000 -1.2937 0.04098 0.03602 -0.0670 1.0000 0.0207
-16.750 -1.2901 0.03875 0.03373 -0.0673 1.0000 0.0209
-16.500 -1.2847 0.03678 0.03170 -0.0674 1.0000 0.0212
-16.250 -1.2776 0.03507 0.02994 -0.0673 1.0000 0.0214
-16.000 -1.2695 0.03349 0.02831 -0.0672 1.0000 0.0216
-15.750 -1.2603 0.03204 0.02682 -0.0670 1.0000 0.0219
-15.500 -1.2503 0.03073 0.02546 -0.0666 1.0000 0.0221
-15.250 -1.2398 0.02948 0.02418 -0.0662 1.0000 0.0223
-15.000 -1.2290 0.02835 0.02300 -0.0656 1.0000 0.0226
-14.750 -1.2187 0.02727 0.02188 -0.0648 1.0000 0.0229
-14.500 -1.2090 0.02629 0.02087 -0.0637 1.0000 0.0231
-14.250 -1.2014 0.02537 0.01991 -0.0621 1.0000 0.0233
-14.000 -1.1960 0.02454 0.01904 -0.0599 1.0000 0.0236
-13.750 -1.1959 0.02379 0.01826 -0.0566 1.0000 0.0237
-13.500 -1.1772 0.02294 0.01736 -0.0569 0.9985 0.0240
-13.250 -1.1537 0.02207 0.01646 -0.0580 0.9962 0.0244
-13.000 -1.1281 0.02112 0.01549 -0.0596 0.9942 0.0250
-12.750 -1.1005 0.02030 0.01466 -0.0614 0.9929 0.0256
-12.500 -1.0751 0.01956 0.01390 -0.0625 0.9906 0.0262
-12.250 -1.0481 0.01886 0.01318 -0.0639 0.9884 0.0267
-12.000 -1.0195 0.01822 0.01252 -0.0654 0.9866 0.0273
-11.750 -0.9894 0.01761 0.01187 -0.0672 0.9851 0.0279
-11.500 -0.9586 0.01699 0.01124 -0.0690 0.9836 0.0286
-11.250 -0.9275 0.01638 0.01063 -0.0710 0.9822 0.0296
-11.000 -0.8956 0.01582 0.01007 -0.0729 0.9810 0.0307
-10.750 -0.8669 0.01533 0.00957 -0.0741 0.9780 0.0318
-10.500 -0.8374 0.01486 0.00908 -0.0754 0.9747 0.0330
-10.250 -0.8068 0.01437 0.00861 -0.0769 0.9720 0.0346
-10.000 -0.7750 0.01393 0.00817 -0.0785 0.9697 0.0362
-9.750 -0.7428 0.01353 0.00776 -0.0802 0.9677 0.0377
-9.500 -0.7130 0.01313 0.00738 -0.0813 0.9641 0.0395
-9.250 -0.6826 0.01278 0.00703 -0.0825 0.9605 0.0414
-9.000 -0.6515 0.01246 0.00670 -0.0836 0.9574 0.0429
-8.750 -0.6202 0.01212 0.00637 -0.0849 0.9546 0.0450
-8.500 -0.5896 0.01184 0.00609 -0.0859 0.9512 0.0470
-8.250 -0.5595 0.01159 0.00583 -0.0867 0.9469 0.0485
-8.000 -0.5287 0.01129 0.00554 -0.0878 0.9428 0.0508
-7.750 -0.4977 0.01102 0.00528 -0.0888 0.9393 0.0528
-7.500 -0.4670 0.01080 0.00504 -0.0897 0.9357 0.0545
-7.250 -0.4361 0.01056 0.00481 -0.0906 0.9314 0.0567
-7.000 -0.4051 0.01032 0.00459 -0.0916 0.9270 0.0594
-6.750 -0.3741 0.01012 0.00438 -0.0925 0.9229 0.0621
-6.500 -0.3429 0.00989 0.00418 -0.0934 0.9187 0.0658
-6.250 -0.3117 0.00970 0.00400 -0.0943 0.9141 0.0691
-6.000 -0.2804 0.00951 0.00382 -0.0953 0.9099 0.0733
-5.500 -0.2170 0.00910 0.00348 -0.0973 0.9019 0.0860
-5.250 -0.1852 0.00890 0.00332 -0.0983 0.8974 0.0943
-5.000 -0.1535 0.00873 0.00317 -0.0993 0.8928 0.1038
-4.500 -0.0888 0.00830 0.00288 -0.1016 0.8841 0.1341
-4.250 -0.0562 0.00809 0.00275 -0.1028 0.8791 0.1542
-4.000 -0.0234 0.00787 0.00261 -0.1041 0.8745 0.1796
-3.750 0.0100 0.00762 0.00248 -0.1055 0.8703 0.2120
-3.500 0.0439 0.00735 0.00236 -0.1071 0.8650 0.2489
-3.250 0.0786 0.00702 0.00220 -0.1089 0.8575 0.3034
-3.000 0.1139 0.00666 0.00204 -0.1108 0.8490 0.3666
-2.750 0.1496 0.00629 0.00188 -0.1129 0.8386 0.4361
-2.500 0.1841 0.00601 0.00178 -0.1145 0.8230 0.5105
-2.250 0.2156 0.00596 0.00177 -0.1152 0.8056 0.5446
-2.000 0.2461 0.00597 0.00179 -0.1157 0.7904 0.5641
-1.750 0.2757 0.00606 0.00180 -0.1158 0.7690 0.5760
-1.500 0.3046 0.00620 0.00181 -0.1158 0.7345 0.5828
-1.250 0.3319 0.00651 0.00186 -0.1156 0.6684 0.5913
-1.000 0.3573 0.00709 0.00200 -0.1151 0.5608 0.5984
-0.750 0.3825 0.00777 0.00223 -0.1147 0.4486 0.6047
-0.500 0.4098 0.00821 0.00238 -0.1146 0.3773 0.6106
-0.250 0.4372 0.00861 0.00254 -0.1145 0.3148 0.6160
0.000 0.4646 0.00900 0.00270 -0.1145 0.2565 0.6201
0.250 0.4927 0.00928 0.00283 -0.1145 0.2201 0.6227
0.500 0.5210 0.00954 0.00295 -0.1145 0.1907 0.6251
0.750 0.5491 0.00981 0.00307 -0.1145 0.1615 0.6272
1.000 0.5777 0.01002 0.00319 -0.1146 0.1446 0.6288
1.250 0.6062 0.01022 0.00331 -0.1146 0.1284 0.6301
1.500 0.6344 0.01044 0.00345 -0.1146 0.1112 0.6318
1.750 0.6627 0.01064 0.00360 -0.1146 0.0988 0.6335
2.000 0.6910 0.01085 0.00375 -0.1146 0.0891 0.6353
2.250 0.7193 0.01105 0.00390 -0.1146 0.0816 0.6370
2.500 0.7475 0.01124 0.00406 -0.1146 0.0757 0.6387
2.750 0.7756 0.01145 0.00423 -0.1145 0.0698 0.6403
3.000 0.8037 0.01165 0.00439 -0.1144 0.0651 0.6420
3.250 0.8316 0.01185 0.00457 -0.1143 0.0613 0.6435
3.500 0.8595 0.01205 0.00474 -0.1142 0.0581 0.6450
3.750 0.8872 0.01228 0.00493 -0.1141 0.0552 0.6465
4.000 0.9151 0.01246 0.00513 -0.1140 0.0535 0.6481
4.250 0.9426 0.01267 0.00534 -0.1138 0.0517 0.6498
4.500 0.9700 0.01291 0.00556 -0.1136 0.0498 0.6515
4.750 0.9972 0.01314 0.00579 -0.1134 0.0481 0.6533
5.000 1.0245 0.01335 0.00601 -0.1131 0.0468 0.6552
5.250 1.0515 0.01359 0.00625 -0.1129 0.0453 0.6570
5.500 1.0782 0.01385 0.00649 -0.1126 0.0438 0.6589
5.750 1.1047 0.01412 0.00676 -0.1122 0.0424 0.6606
6.000 1.1314 0.01436 0.00701 -0.1119 0.0414 0.6623
6.250 1.1578 0.01461 0.00727 -0.1115 0.0401 0.6643
6.500 1.1839 0.01488 0.00756 -0.1111 0.0387 0.6663
6.750 1.2096 0.01520 0.00787 -0.1106 0.0372 0.6682
7.000 1.2355 0.01546 0.00815 -0.1101 0.0361 0.6704
7.250 1.2610 0.01575 0.00845 -0.1096 0.0346 0.6728
7.500 1.2861 0.01607 0.00876 -0.1090 0.0332 0.6751
7.750 1.3110 0.01641 0.00910 -0.1083 0.0321 0.6771
8.000 1.3358 0.01673 0.00945 -0.1077 0.0311 0.6791
8.250 1.3601 0.01707 0.00981 -0.1070 0.0300 0.6811
8.500 1.3840 0.01744 0.01019 -0.1062 0.0290 0.6832
8.750 1.4074 0.01784 0.01061 -0.1053 0.0281 0.6855
9.000 1.4308 0.01821 0.01101 -0.1044 0.0275 0.6879
9.250 1.4537 0.01861 0.01144 -0.1035 0.0268 0.6901
9.500 1.4762 0.01902 0.01187 -0.1025 0.0262 0.6921
9.750 1.4980 0.01946 0.01233 -0.1014 0.0256 0.6939
10.000 1.5192 0.01993 0.01282 -0.1001 0.0250 0.6960
10.250 1.5392 0.02044 0.01337 -0.0987 0.0243 0.6981
10.500 1.5591 0.02091 0.01389 -0.0973 0.0239 0.7003
10.750 1.5783 0.02139 0.01441 -0.0957 0.0236 0.7026
11.000 1.5965 0.02189 0.01496 -0.0940 0.0233 0.7049
11.250 1.6135 0.02241 0.01553 -0.0921 0.0230 0.7070
11.500 1.6271 0.02296 0.01612 -0.0896 0.0227 0.7089
11.750 1.6421 0.02357 0.01678 -0.0874 0.0224 0.7111
12.000 1.6572 0.02421 0.01748 -0.0853 0.0221 0.7134
12.250 1.6718 0.02491 0.01823 -0.0833 0.0218 0.7158
12.500 1.6857 0.02566 0.01904 -0.0812 0.0215 0.7182
12.750 1.6988 0.02648 0.01991 -0.0790 0.0212 0.7204
13.000 1.7107 0.02739 0.02087 -0.0768 0.0209 0.7226
13.250 1.7213 0.02840 0.02194 -0.0745 0.0206 0.7245
13.500 1.7335 0.02932 0.02293 -0.0725 0.0205 0.7266
13.750 1.7452 0.03027 0.02397 -0.0705 0.0204 0.7288
14.000 1.7562 0.03129 0.02507 -0.0685 0.0202 0.7311
14.250 1.7665 0.03239 0.02625 -0.0665 0.0201 0.7334
14.500 1.7762 0.03356 0.02751 -0.0646 0.0199 0.7358
14.750 1.7850 0.03482 0.02885 -0.0627 0.0197 0.7381
15.000 1.7932 0.03616 0.03026 -0.0609 0.0195 0.7402
15.250 1.8004 0.03763 0.03181 -0.0591 0.0193 0.7422
15.500 1.8065 0.03923 0.03350 -0.0574 0.0192 0.7444
15.750 1.8114 0.04097 0.03534 -0.0557 0.0190 0.7467
16.000 1.8153 0.04286 0.03732 -0.0542 0.0189 0.7491
16.250 1.8181 0.04492 0.03947 -0.0527 0.0187 0.7515
16.500 1.8197 0.04717 0.04181 -0.0515 0.0186 0.7538
16.750 1.8196 0.04965 0.04439 -0.0503 0.0184 0.7559
17.000 1.8184 0.05236 0.04720 -0.0494 0.0183 0.7579
17.250 1.8154 0.05542 0.05037 -0.0488 0.0182 0.7598
17.500 1.8107 0.05885 0.05391 -0.0485 0.0181 0.7619
17.750 1.8040 0.06270 0.05788 -0.0486 0.0180 0.7640
18.000 1.7948 0.06708 0.06238 -0.0491 0.0179 0.7661
18.250 1.7827 0.07216 0.06760 -0.0503 0.0178 0.7681
18.500 1.7670 0.07809 0.07367 -0.0523 0.0177 0.7700
18.750 1.7468 0.08508 0.08082 -0.0551 0.0176 0.7716
19.000 1.7212 0.09331 0.08924 -0.0590 0.0176 0.7729
19.250 1.6893 0.10301 0.09913 -0.0641 0.0176 0.7738
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0614 AIRFOIL (sc20614-il)