SM701 (sm701-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 500,000 Max Cl/Cd: 79.64 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sm701-il-500000-n5.txt Download as CSV file: xf-sm701-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5842 0.07944 0.07657 -0.0782 0.9962 0.0124
-14.000 -0.6373 0.06347 0.06022 -0.0911 0.9945 0.0122
-13.750 -0.6530 0.05662 0.05316 -0.0969 0.9928 0.0123
-13.500 -0.6661 0.05097 0.04730 -0.1012 0.9902 0.0123
-13.250 -0.6736 0.04612 0.04223 -0.1052 0.9876 0.0124
-13.000 -0.6706 0.04255 0.03847 -0.1086 0.9854 0.0126
-12.750 -0.6651 0.03912 0.03482 -0.1120 0.9836 0.0127
-12.500 -0.6623 0.03652 0.03204 -0.1132 0.9798 0.0130
-12.250 -0.6551 0.03405 0.02939 -0.1146 0.9760 0.0131
-12.000 -0.6412 0.03184 0.02698 -0.1166 0.9733 0.0133
-11.750 -0.6223 0.02987 0.02482 -0.1190 0.9714 0.0134
-11.500 -0.6140 0.02847 0.02330 -0.1182 0.9650 0.0135
-11.250 -0.5951 0.02704 0.02170 -0.1193 0.9612 0.0137
-11.000 -0.5719 0.02553 0.02005 -0.1211 0.9588 0.0139
-10.750 -0.5623 0.02438 0.01884 -0.1196 0.9513 0.0141
-10.500 -0.5427 0.02332 0.01773 -0.1199 0.9462 0.0144
-10.250 -0.5293 0.02252 0.01689 -0.1187 0.9384 0.0146
-10.000 -0.5101 0.02164 0.01594 -0.1184 0.9313 0.0149
-9.750 -0.4916 0.02084 0.01506 -0.1177 0.9230 0.0151
-9.500 -0.4665 0.02000 0.01415 -0.1182 0.9162 0.0154
-9.250 -0.4429 0.01920 0.01326 -0.1183 0.9078 0.0156
-9.000 -0.4146 0.01839 0.01237 -0.1192 0.9007 0.0159
-8.750 -0.3886 0.01769 0.01158 -0.1196 0.8916 0.0162
-8.500 -0.3606 0.01698 0.01077 -0.1204 0.8832 0.0165
-8.250 -0.3356 0.01640 0.01010 -0.1205 0.8730 0.0168
-8.000 -0.3105 0.01588 0.00948 -0.1205 0.8635 0.0170
-7.750 -0.2872 0.01530 0.00881 -0.1203 0.8537 0.0174
-7.500 -0.2657 0.01474 0.00820 -0.1197 0.8440 0.0178
-7.250 -0.2419 0.01431 0.00771 -0.1195 0.8359 0.0183
-7.000 -0.2188 0.01393 0.00729 -0.1190 0.8281 0.0189
-6.750 -0.1945 0.01357 0.00685 -0.1187 0.8212 0.0193
-6.500 -0.1705 0.01321 0.00645 -0.1184 0.8148 0.0198
-6.250 -0.1458 0.01289 0.00607 -0.1181 0.8082 0.0203
-6.000 -0.1203 0.01261 0.00571 -0.1179 0.8025 0.0208
-5.750 -0.0954 0.01228 0.00535 -0.1176 0.7967 0.0213
-5.500 -0.0698 0.01197 0.00501 -0.1175 0.7914 0.0221
-5.250 -0.0431 0.01173 0.00472 -0.1175 0.7869 0.0230
-5.000 -0.0168 0.01151 0.00447 -0.1174 0.7819 0.0243
-4.750 0.0099 0.01129 0.00422 -0.1174 0.7769 0.0260
-4.500 0.0370 0.01108 0.00399 -0.1175 0.7726 0.0288
-4.250 0.0643 0.01085 0.00377 -0.1176 0.7685 0.0349
-4.000 0.0910 0.01054 0.00356 -0.1177 0.7637 0.0566
-3.500 0.1457 0.00999 0.00318 -0.1181 0.7539 0.1199
-3.250 0.1724 0.00954 0.00297 -0.1184 0.7480 0.1845
-3.000 0.1996 0.00893 0.00270 -0.1190 0.7416 0.2907
-2.750 0.2276 0.00820 0.00247 -0.1199 0.7353 0.4420
-2.500 0.2557 0.00807 0.00247 -0.1201 0.7282 0.4975
-2.250 0.2840 0.00807 0.00246 -0.1201 0.7217 0.5246
-2.000 0.3124 0.00807 0.00249 -0.1202 0.7156 0.5500
-1.750 0.3407 0.00812 0.00254 -0.1203 0.7094 0.5705
-1.500 0.3690 0.00819 0.00259 -0.1203 0.7038 0.5877
-1.250 0.3970 0.00821 0.00262 -0.1203 0.6976 0.5957
-1.000 0.4252 0.00825 0.00260 -0.1203 0.6911 0.5988
-0.750 0.4534 0.00828 0.00257 -0.1204 0.6849 0.6016
-0.500 0.4813 0.00830 0.00256 -0.1204 0.6777 0.6040
-0.250 0.5088 0.00833 0.00256 -0.1203 0.6707 0.6066
0.000 0.5364 0.00835 0.00257 -0.1202 0.6623 0.6094
0.250 0.5636 0.00841 0.00258 -0.1201 0.6536 0.6121
0.500 0.5907 0.00845 0.00259 -0.1199 0.6434 0.6148
0.750 0.6175 0.00851 0.00261 -0.1197 0.6321 0.6177
1.000 0.6436 0.00859 0.00263 -0.1194 0.6184 0.6206
1.250 0.6688 0.00867 0.00267 -0.1188 0.6017 0.6233
1.500 0.6930 0.00880 0.00272 -0.1181 0.5804 0.6261
1.750 0.7156 0.00899 0.00280 -0.1171 0.5548 0.6291
2.000 0.7367 0.00925 0.00291 -0.1158 0.5254 0.6322
2.250 0.7579 0.00954 0.00305 -0.1146 0.4977 0.6353
2.500 0.7794 0.00982 0.00321 -0.1134 0.4727 0.6383
2.750 0.8005 0.01010 0.00340 -0.1122 0.4482 0.6415
3.000 0.8219 0.01039 0.00358 -0.1111 0.4265 0.6451
3.250 0.8436 0.01066 0.00378 -0.1100 0.4065 0.6488
3.500 0.8652 0.01093 0.00396 -0.1089 0.3884 0.6523
3.750 0.8859 0.01119 0.00415 -0.1077 0.3713 0.6557
4.000 0.9059 0.01145 0.00436 -0.1063 0.3550 0.6592
4.250 0.9264 0.01170 0.00457 -0.1050 0.3413 0.6631
4.500 0.9469 0.01197 0.00479 -0.1038 0.3288 0.6675
5.000 0.9882 0.01253 0.00529 -0.1014 0.3034 0.6762
5.250 1.0091 0.01281 0.00556 -0.1003 0.2932 0.6809
5.750 1.0504 0.01341 0.00611 -0.0980 0.2729 0.6903
6.000 1.0704 0.01373 0.00642 -0.0968 0.2635 0.6952
6.250 1.0909 0.01403 0.00672 -0.0957 0.2545 0.7007
6.750 1.1308 0.01469 0.00738 -0.0933 0.2387 0.7117
7.000 1.1503 0.01504 0.00774 -0.0921 0.2312 0.7183
7.250 1.1701 0.01540 0.00810 -0.0910 0.2238 0.7246
7.500 1.1888 0.01578 0.00851 -0.0897 0.2176 0.7315
7.750 1.2084 0.01614 0.00889 -0.0886 0.2111 0.7385
8.250 1.2453 0.01697 0.00977 -0.0860 0.1988 0.7532
8.500 1.2635 0.01740 0.01024 -0.0848 0.1933 0.7608
8.750 1.2806 0.01789 0.01076 -0.0834 0.1881 0.7696
9.000 1.2989 0.01832 0.01124 -0.0822 0.1830 0.7788
9.250 1.3159 0.01884 0.01179 -0.0809 0.1776 0.7892
9.500 1.3319 0.01938 0.01239 -0.0794 0.1732 0.8001
9.750 1.3494 0.01986 0.01295 -0.0782 0.1690 0.8116
10.000 1.3652 0.02044 0.01357 -0.0768 0.1641 0.8243
10.500 1.3950 0.02163 0.01492 -0.0738 0.1561 0.8560
10.750 1.4083 0.02221 0.01559 -0.0720 0.1518 0.8797
11.000 1.4157 0.02276 0.01626 -0.0691 0.1480 0.9428
11.250 1.4299 0.02350 0.01704 -0.0678 0.1442 1.0000
11.500 1.4461 0.02424 0.01783 -0.0669 0.1405 1.0000
11.750 1.4608 0.02509 0.01870 -0.0659 0.1361 1.0000
12.000 1.4732 0.02611 0.01972 -0.0646 0.1318 1.0000
12.250 1.4886 0.02695 0.02061 -0.0637 0.1285 1.0000
12.500 1.5019 0.02794 0.02163 -0.0627 0.1233 1.0000
12.750 1.5124 0.02916 0.02284 -0.0615 0.1184 1.0000
13.000 1.5263 0.03015 0.02388 -0.0607 0.1143 1.0000
13.250 1.5370 0.03140 0.02515 -0.0596 0.1086 1.0000
13.500 1.5473 0.03271 0.02648 -0.0586 0.1044 1.0000
13.750 1.5586 0.03397 0.02779 -0.0577 0.0997 1.0000
14.000 1.5671 0.03549 0.02932 -0.0568 0.0951 1.0000
14.250 1.5768 0.03695 0.03082 -0.0559 0.0914 1.0000
14.500 1.5855 0.03851 0.03242 -0.0551 0.0868 1.0000
14.750 1.5913 0.04039 0.03431 -0.0542 0.0823 1.0000
15.000 1.5999 0.04205 0.03603 -0.0536 0.0785 1.0000
15.250 1.6052 0.04405 0.03805 -0.0529 0.0739 1.0000
15.500 1.6099 0.04617 0.04022 -0.0522 0.0701 1.0000
15.750 1.6150 0.04830 0.04241 -0.0517 0.0662 1.0000
16.000 1.6167 0.05085 0.04499 -0.0513 0.0621 1.0000
16.250 1.6198 0.05331 0.04750 -0.0510 0.0581 1.0000
16.500 1.6198 0.05620 0.05044 -0.0507 0.0541 1.0000
16.750 1.6194 0.05922 0.05352 -0.0507 0.0504 1.0000
17.000 1.6176 0.06252 0.05687 -0.0508 0.0466 1.0000
17.250 1.6149 0.06602 0.06043 -0.0511 0.0438 1.0000
17.500 1.6119 0.06967 0.06418 -0.0516 0.0407 1.0000
17.750 1.6059 0.07386 0.06843 -0.0524 0.0380 1.0000
18.000 1.6010 0.07801 0.07268 -0.0533 0.0357 1.0000
18.250 1.5931 0.08272 0.07748 -0.0546 0.0331 1.0000
18.500 1.5834 0.08782 0.08267 -0.0562 0.0311 1.0000
18.750 1.5748 0.09287 0.08783 -0.0579 0.0292 1.0000
19.000 1.5626 0.09863 0.09369 -0.0601 0.0271 1.0000
19.250 1.5506 0.10443 0.09961 -0.0624 0.0256 1.0000
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Polar data table (+)
Polar graphs
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