SM701 (sm701-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 200,000 Max Cl/Cd: 68.59 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sm701-il-200000.txt Download as CSV file: xf-sm701-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SM701
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3864 0.11578 0.11250 -0.0391 1.0000 0.0642
-10.500 -0.3796 0.11185 0.10857 -0.0420 0.9981 0.0666
-10.250 -0.4295 0.09486 0.09158 -0.0663 0.9907 0.0713
-10.000 -0.4152 0.08935 0.08613 -0.0674 0.9881 0.0726
-9.750 -0.3777 0.09076 0.08753 -0.0634 0.9864 0.0739
-9.500 -0.3574 0.08790 0.08466 -0.0661 0.9839 0.0761
-9.250 -0.2449 0.06960 0.06648 -0.0828 0.9621 0.0881
-9.000 -0.2564 0.06139 0.05824 -0.0896 0.9590 0.0903
-8.750 -0.2959 0.05365 0.05042 -0.0949 0.9490 0.0912
-8.500 -0.3291 0.04848 0.04511 -0.0976 0.9391 0.0917
-8.250 -0.3635 0.04466 0.04083 -0.0996 0.9274 0.0962
-8.000 -0.4621 0.04163 0.03625 -0.0954 0.9239 0.0531
-7.750 -0.4510 0.03531 0.02869 -0.0942 0.9180 0.0431
-7.500 -0.4196 0.03294 0.02605 -0.0957 0.9159 0.0427
-7.250 -0.3984 0.03095 0.02384 -0.0952 0.9110 0.0425
-7.000 -0.3758 0.02953 0.02218 -0.0947 0.9055 0.0428
-6.750 -0.3445 0.02728 0.01986 -0.0959 0.9032 0.0441
-6.500 -0.3103 0.02597 0.01850 -0.0974 0.9014 0.0452
-6.250 -0.2741 0.02471 0.01716 -0.0990 0.9001 0.0461
-6.000 -0.2632 0.02419 0.01660 -0.0961 0.8920 0.0467
-5.750 -0.2315 0.02324 0.01560 -0.0969 0.8892 0.0479
-5.500 -0.1971 0.02232 0.01464 -0.0982 0.8872 0.0496
-5.250 -0.1620 0.02128 0.01360 -0.0998 0.8857 0.0523
-5.000 -0.1441 0.02081 0.01319 -0.0985 0.8799 0.0551
-4.750 -0.1190 0.02028 0.01264 -0.0983 0.8751 0.0587
-4.500 -0.0848 0.01932 0.01171 -0.1000 0.8729 0.0650
-4.250 -0.0467 0.01826 0.01074 -0.1025 0.8713 0.0865
-4.000 -0.0095 0.01534 0.00953 -0.1074 0.8700 0.4153
-3.750 0.0297 0.01518 0.00968 -0.1092 0.8687 0.5466
-3.500 0.0405 0.01566 0.01012 -0.1060 0.8596 0.5716
-3.250 0.0762 0.01583 0.01024 -0.1069 0.8570 0.6033
-3.000 0.1120 0.01606 0.01051 -0.1073 0.8550 0.6266
-2.750 0.1496 0.01624 0.01068 -0.1082 0.8532 0.6457
-2.500 0.1628 0.01669 0.01111 -0.1052 0.8448 0.6577
-2.250 0.1969 0.01674 0.01110 -0.1057 0.8412 0.6706
-2.000 0.2315 0.01690 0.01128 -0.1056 0.8386 0.6845
-1.750 0.2683 0.01698 0.01136 -0.1059 0.8362 0.6971
-1.500 0.2832 0.01712 0.01145 -0.1038 0.8268 0.7044
-1.250 0.3223 0.01676 0.01101 -0.1056 0.8230 0.7083
-1.000 0.3636 0.01644 0.01060 -0.1078 0.8199 0.7117
-0.750 0.3795 0.01654 0.01069 -0.1057 0.8108 0.7159
-0.500 0.4187 0.01621 0.01026 -0.1079 0.8063 0.7203
-0.250 0.4507 0.01603 0.01002 -0.1088 0.8006 0.7240
0.000 0.4756 0.01596 0.00994 -0.1081 0.7931 0.7269
0.250 0.5130 0.01570 0.00960 -0.1097 0.7882 0.7300
0.500 0.5363 0.01568 0.00958 -0.1089 0.7799 0.7340
0.750 0.5716 0.01546 0.00927 -0.1104 0.7734 0.7386
1.000 0.5992 0.01535 0.00915 -0.1103 0.7659 0.7416
1.250 0.6275 0.01521 0.00900 -0.1102 0.7580 0.7446
1.500 0.6566 0.01510 0.00886 -0.1103 0.7501 0.7484
1.750 0.6856 0.01497 0.00870 -0.1105 0.7413 0.7530
2.000 0.7141 0.01486 0.00856 -0.1106 0.7321 0.7573
2.250 0.7428 0.01470 0.00838 -0.1105 0.7230 0.7604
2.500 0.7660 0.01463 0.00834 -0.1095 0.7120 0.7644
2.750 0.7959 0.01450 0.00817 -0.1098 0.7021 0.7691
3.000 0.8225 0.01438 0.00803 -0.1095 0.6901 0.7741
3.250 0.8438 0.01431 0.00800 -0.1080 0.6769 0.7782
3.500 0.8674 0.01423 0.00793 -0.1071 0.6628 0.7830
3.750 0.8924 0.01417 0.00783 -0.1065 0.6470 0.7887
4.000 0.9137 0.01410 0.00778 -0.1051 0.6294 0.7931
4.250 0.9345 0.01408 0.00772 -0.1035 0.6093 0.7984
4.500 0.9555 0.01413 0.00770 -0.1022 0.5853 0.8053
4.750 0.9729 0.01422 0.00769 -0.1000 0.5594 0.8107
5.000 0.9898 0.01443 0.00779 -0.0979 0.5309 0.8173
5.250 1.0066 0.01475 0.00795 -0.0960 0.5028 0.8242
5.500 1.0204 0.01512 0.00818 -0.0933 0.4778 0.8310
5.750 1.0356 0.01550 0.00847 -0.0912 0.4540 0.8393
6.000 1.0468 0.01587 0.00876 -0.0881 0.4338 0.8473
6.250 1.0604 0.01630 0.00910 -0.0858 0.4148 0.8570
6.500 1.0731 0.01673 0.00946 -0.0831 0.3977 0.8675
6.750 1.0855 0.01713 0.00984 -0.0805 0.3822 0.8785
7.000 1.0980 0.01752 0.01022 -0.0779 0.3678 0.8915
7.250 1.1093 0.01789 0.01058 -0.0751 0.3548 0.9073
7.500 1.1179 0.01822 0.01090 -0.0717 0.3432 0.9301
7.750 1.1319 0.01849 0.01115 -0.0697 0.3317 1.0000
8.000 1.1575 0.01912 0.01177 -0.0704 0.3188 1.0000
8.250 1.1811 0.01978 0.01238 -0.0707 0.3072 1.0000
8.500 1.2035 0.02050 0.01299 -0.0707 0.2970 1.0000
8.750 1.2238 0.02112 0.01363 -0.0703 0.2869 1.0000
9.000 1.2445 0.02182 0.01429 -0.0698 0.2781 1.0000
9.250 1.2630 0.02250 0.01494 -0.0690 0.2694 1.0000
9.500 1.2821 0.02321 0.01566 -0.0683 0.2614 1.0000
9.750 1.3000 0.02392 0.01635 -0.0674 0.2539 1.0000
10.000 1.3190 0.02468 0.01711 -0.0667 0.2468 1.0000
10.250 1.3350 0.02541 0.01788 -0.0656 0.2397 1.0000
10.500 1.3546 0.02622 0.01864 -0.0650 0.2333 1.0000
10.750 1.3695 0.02700 0.01952 -0.0638 0.2269 1.0000
11.000 1.3871 0.02782 0.02030 -0.0630 0.2210 1.0000
11.250 1.4030 0.02870 0.02126 -0.0619 0.2152 1.0000
11.500 1.4167 0.02958 0.02220 -0.0607 0.2093 1.0000
11.750 1.4376 0.03047 0.02300 -0.0604 0.2037 1.0000
12.000 1.4472 0.03148 0.02419 -0.0588 0.1986 1.0000
12.250 1.4601 0.03246 0.02522 -0.0576 0.1935 1.0000
12.500 1.4793 0.03344 0.02612 -0.0571 0.1883 1.0000
12.750 1.4871 0.03462 0.02751 -0.0555 0.1836 1.0000
13.000 1.4978 0.03574 0.02871 -0.0543 0.1788 1.0000
13.250 1.5167 0.03678 0.02964 -0.0539 0.1738 1.0000
13.500 1.5211 0.03822 0.03131 -0.0523 0.1697 1.0000
13.750 1.5292 0.03955 0.03274 -0.0511 0.1652 1.0000
14.000 1.5423 0.04077 0.03392 -0.0503 0.1607 1.0000
14.250 1.5493 0.04236 0.03567 -0.0492 0.1566 1.0000
14.500 1.5537 0.04403 0.03749 -0.0480 0.1524 1.0000
14.750 1.5605 0.04559 0.03909 -0.0470 0.1484 1.0000
15.000 1.5711 0.04715 0.04066 -0.0464 0.1441 1.0000
15.250 1.5709 0.04932 0.04304 -0.0453 0.1404 1.0000
15.500 1.5737 0.05133 0.04515 -0.0445 0.1363 1.0000
15.750 1.5833 0.05295 0.04671 -0.0441 0.1321 1.0000
16.000 1.5799 0.05569 0.04968 -0.0434 0.1286 1.0000
16.250 1.5781 0.05835 0.05250 -0.0430 0.1247 1.0000
16.500 1.5791 0.06081 0.05499 -0.0427 0.1209 1.0000
16.750 1.5797 0.06349 0.05773 -0.0426 0.1169 1.0000
17.000 1.5739 0.06698 0.06143 -0.0428 0.1132 1.0000
17.250 1.5709 0.07025 0.06480 -0.0431 0.1096 1.0000
17.500 1.5730 0.07293 0.06740 -0.0434 0.1055 1.0000
17.750 1.5635 0.07736 0.07211 -0.0443 0.1024 1.0000
18.000 1.5568 0.08155 0.07645 -0.0455 0.0987 1.0000
18.250 1.5524 0.08546 0.08040 -0.0466 0.0953 1.0000
18.500 1.5465 0.08973 0.08477 -0.0479 0.0920 1.0000
18.750 1.5367 0.09482 0.09008 -0.0499 0.0888 1.0000
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