SM701 (sm701-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 200,000 Max Cl/Cd: 64.37 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sm701-il-200000-n5.txt Download as CSV file: xf-sm701-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5078 0.06842 0.06440 -0.0819 0.9929 0.0199
-11.500 -0.5323 0.05962 0.05531 -0.0903 0.9874 0.0198
-11.250 -0.5504 0.05254 0.04788 -0.0974 0.9821 0.0199
-11.000 -0.5630 0.04763 0.04264 -0.1010 0.9739 0.0202
-10.750 -0.5715 0.04382 0.03849 -0.1029 0.9651 0.0203
-10.500 -0.5726 0.04034 0.03460 -0.1047 0.9577 0.0206
-10.250 -0.5723 0.03778 0.03170 -0.1037 0.9466 0.0208
-10.000 -0.5633 0.03544 0.02900 -0.1034 0.9387 0.0210
-9.750 -0.5468 0.03334 0.02674 -0.1035 0.9325 0.0212
-9.500 -0.5221 0.03154 0.02479 -0.1048 0.9295 0.0215
-9.250 -0.5093 0.03026 0.02339 -0.1032 0.9204 0.0218
-9.000 -0.4842 0.02880 0.02178 -0.1040 0.9166 0.0221
-8.750 -0.4602 0.02750 0.02034 -0.1042 0.9120 0.0226
-8.500 -0.4401 0.02635 0.01906 -0.1035 0.9049 0.0230
-8.250 -0.4107 0.02522 0.01779 -0.1046 0.9016 0.0238
-8.000 -0.3814 0.02415 0.01656 -0.1055 0.8980 0.0247
-7.750 -0.3597 0.02332 0.01559 -0.1048 0.8910 0.0252
-7.500 -0.3309 0.02220 0.01445 -0.1056 0.8874 0.0258
-7.250 -0.2995 0.02122 0.01346 -0.1069 0.8846 0.0264
-7.000 -0.2777 0.02051 0.01273 -0.1063 0.8775 0.0270
-6.750 -0.2495 0.01973 0.01190 -0.1069 0.8728 0.0278
-6.500 -0.2176 0.01895 0.01105 -0.1083 0.8695 0.0287
-6.250 -0.1932 0.01837 0.01040 -0.1081 0.8635 0.0298
-6.000 -0.1669 0.01773 0.00974 -0.1084 0.8582 0.0312
-5.750 -0.1358 0.01713 0.00909 -0.1096 0.8545 0.0330
-5.500 -0.1080 0.01663 0.00853 -0.1101 0.8495 0.0350
-5.250 -0.0828 0.01617 0.00803 -0.1100 0.8434 0.0370
-5.000 -0.0529 0.01569 0.00751 -0.1108 0.8393 0.0408
-4.750 -0.0218 0.01520 0.00701 -0.1118 0.8358 0.0486
-4.500 0.0010 0.01477 0.00668 -0.1113 0.8295 0.0675
-4.250 0.0284 0.01423 0.00630 -0.1119 0.8246 0.1069
-4.000 0.0588 0.01366 0.00590 -0.1130 0.8209 0.1611
-3.750 0.0839 0.01297 0.00557 -0.1134 0.8159 0.2505
-3.500 0.1084 0.01194 0.00546 -0.1140 0.8105 0.4639
-3.250 0.1385 0.01195 0.00556 -0.1144 0.8063 0.5320
-3.000 0.1693 0.01204 0.00562 -0.1148 0.8022 0.5625
-2.750 0.1952 0.01215 0.00570 -0.1143 0.7962 0.5815
-2.500 0.2242 0.01225 0.00575 -0.1143 0.7910 0.5966
-2.250 0.2550 0.01241 0.00585 -0.1145 0.7865 0.6157
-2.000 0.2789 0.01259 0.00606 -0.1134 0.7793 0.6297
-1.750 0.3092 0.01259 0.00592 -0.1139 0.7733 0.6367
-1.500 0.3372 0.01257 0.00584 -0.1138 0.7667 0.6397
-1.250 0.3642 0.01256 0.00579 -0.1136 0.7593 0.6428
-1.000 0.3947 0.01253 0.00567 -0.1140 0.7532 0.6461
-0.750 0.4204 0.01253 0.00563 -0.1136 0.7456 0.6495
-0.500 0.4504 0.01251 0.00551 -0.1141 0.7393 0.6533
-0.250 0.4770 0.01252 0.00549 -0.1138 0.7322 0.6563
0.000 0.5043 0.01252 0.00547 -0.1137 0.7250 0.6589
0.250 0.5322 0.01253 0.00544 -0.1137 0.7180 0.6618
0.500 0.5586 0.01254 0.00543 -0.1134 0.7098 0.6654
0.750 0.5871 0.01255 0.00538 -0.1135 0.7022 0.6694
1.000 0.6131 0.01257 0.00538 -0.1132 0.6932 0.6727
1.250 0.6396 0.01259 0.00539 -0.1128 0.6843 0.6754
1.500 0.6657 0.01261 0.00540 -0.1124 0.6744 0.6786
1.750 0.6909 0.01265 0.00544 -0.1119 0.6637 0.6823
2.000 0.7171 0.01269 0.00543 -0.1116 0.6522 0.6866
2.250 0.7423 0.01274 0.00545 -0.1110 0.6393 0.6903
2.500 0.7659 0.01279 0.00551 -0.1102 0.6240 0.6936
2.750 0.7896 0.01286 0.00555 -0.1093 0.6071 0.6974
3.000 0.8127 0.01296 0.00560 -0.1084 0.5862 0.7017
3.250 0.8352 0.01311 0.00564 -0.1074 0.5622 0.7061
3.500 0.8552 0.01330 0.00574 -0.1058 0.5362 0.7098
3.750 0.8741 0.01358 0.00588 -0.1041 0.5103 0.7144
4.000 0.8931 0.01389 0.00607 -0.1025 0.4850 0.7196
4.250 0.9107 0.01424 0.00630 -0.1007 0.4616 0.7243
4.500 0.9279 0.01458 0.00657 -0.0988 0.4399 0.7287
4.750 0.9444 0.01492 0.00684 -0.0969 0.4203 0.7340
5.000 0.9613 0.01529 0.00713 -0.0950 0.4023 0.7398
5.250 0.9771 0.01566 0.00747 -0.0930 0.3854 0.7448
5.500 0.9940 0.01606 0.00783 -0.0912 0.3695 0.7511
5.750 1.0115 0.01647 0.00820 -0.0895 0.3552 0.7577
6.000 1.0282 0.01688 0.00861 -0.0878 0.3424 0.7639
6.250 1.0451 0.01733 0.00902 -0.0861 0.3297 0.7714
6.500 1.0621 0.01775 0.00945 -0.0845 0.3176 0.7780
6.750 1.0794 0.01818 0.00989 -0.0829 0.3066 0.7859
7.000 1.0956 0.01866 0.01037 -0.0813 0.2968 0.7937
7.250 1.1126 0.01910 0.01084 -0.0797 0.2866 0.8029
7.500 1.1286 0.01958 0.01135 -0.0780 0.2774 0.8125
7.750 1.1444 0.02010 0.01188 -0.0764 0.2686 0.8234
8.000 1.1603 0.02057 0.01241 -0.0747 0.2608 0.8351
8.250 1.1745 0.02111 0.01297 -0.0729 0.2528 0.8481
8.500 1.1891 0.02160 0.01353 -0.0710 0.2458 0.8633
8.750 1.2016 0.02212 0.01411 -0.0688 0.2386 0.8834
9.250 1.2250 0.02302 0.01516 -0.0644 0.2263 1.0000
9.500 1.2409 0.02383 0.01594 -0.0634 0.2199 1.0000
9.750 1.2592 0.02451 0.01667 -0.0627 0.2136 1.0000
10.000 1.2754 0.02530 0.01747 -0.0618 0.2077 1.0000
10.250 1.2906 0.02617 0.01834 -0.0608 0.2026 1.0000
10.500 1.3077 0.02693 0.01917 -0.0601 0.1970 1.0000
10.750 1.3218 0.02786 0.02012 -0.0590 0.1915 1.0000
11.000 1.3363 0.02880 0.02108 -0.0581 0.1869 1.0000
11.250 1.3521 0.02968 0.02204 -0.0572 0.1821 1.0000
11.500 1.3651 0.03072 0.02311 -0.0562 0.1771 1.0000
11.750 1.3775 0.03184 0.02425 -0.0552 0.1730 1.0000
12.000 1.3924 0.03281 0.02533 -0.0545 0.1682 1.0000
12.250 1.4046 0.03397 0.02653 -0.0535 0.1638 1.0000
12.500 1.4144 0.03532 0.02789 -0.0525 0.1598 1.0000
12.750 1.4281 0.03643 0.02911 -0.0518 0.1557 1.0000
13.000 1.4396 0.03770 0.03048 -0.0510 0.1513 1.0000
13.250 1.4488 0.03917 0.03199 -0.0501 0.1475 1.0000
13.500 1.4583 0.04067 0.03355 -0.0493 0.1438 1.0000
13.750 1.4694 0.04206 0.03507 -0.0486 0.1395 1.0000
14.000 1.4779 0.04370 0.03678 -0.0479 0.1357 1.0000
14.250 1.4834 0.04563 0.03872 -0.0472 0.1321 1.0000
14.500 1.4930 0.04726 0.04050 -0.0467 0.1284 1.0000
14.750 1.5006 0.04909 0.04245 -0.0462 0.1245 1.0000
15.000 1.5053 0.05124 0.04466 -0.0458 0.1209 1.0000
15.250 1.5090 0.05354 0.04701 -0.0454 0.1177 1.0000
15.500 1.5162 0.05558 0.04920 -0.0451 0.1139 1.0000
15.750 1.5199 0.05802 0.05175 -0.0450 0.1101 1.0000
16.000 1.5203 0.06087 0.05465 -0.0449 0.1068 1.0000
16.250 1.5231 0.06355 0.05746 -0.0450 0.1034 1.0000
16.500 1.5254 0.06637 0.06042 -0.0452 0.0995 1.0000
16.750 1.5233 0.06980 0.06392 -0.0457 0.0957 1.0000
17.000 1.5208 0.07339 0.06759 -0.0463 0.0924 1.0000
17.250 1.5208 0.07677 0.07113 -0.0470 0.0885 1.0000
17.500 1.5162 0.08086 0.07532 -0.0481 0.0849 1.0000
17.750 1.5089 0.08545 0.07996 -0.0495 0.0819 1.0000
18.000 1.5061 0.08950 0.08418 -0.0508 0.0782 1.0000
18.250 1.4987 0.09433 0.08913 -0.0525 0.0748 1.0000
18.500 1.4880 0.09979 0.09466 -0.0547 0.0720 1.0000
18.750 1.4811 0.10471 0.09973 -0.0568 0.0689 1.0000
19.000 1.4718 0.11015 0.10531 -0.0592 0.0658 1.0000
19.250 1.4592 0.11621 0.11148 -0.0621 0.0631 1.0000
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Polar data table (+)
Polar graphs
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