SM701 (sm701-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.87 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sm701-il-1000000.txt Download as CSV file: xf-sm701-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6237 0.07051 0.06829 -0.0809 0.9974 0.0133
-13.750 -0.6528 0.06018 0.05772 -0.0904 0.9959 0.0133
-13.500 -0.6685 0.05311 0.05044 -0.0972 0.9945 0.0133
-13.250 -0.6813 0.04720 0.04431 -0.1025 0.9926 0.0133
-13.000 -0.6844 0.04316 0.04008 -0.1061 0.9896 0.0135
-12.750 -0.6802 0.03982 0.03654 -0.1097 0.9872 0.0136
-12.500 -0.6692 0.03721 0.03375 -0.1135 0.9853 0.0137
-12.250 -0.6563 0.03456 0.03090 -0.1172 0.9837 0.0138
-12.000 -0.6610 0.03105 0.02712 -0.1180 0.9783 0.0139
-11.750 -0.6513 0.02771 0.02360 -0.1196 0.9752 0.0143
-11.500 -0.6270 0.02632 0.02214 -0.1218 0.9734 0.0145
-11.250 -0.6006 0.02492 0.02065 -0.1242 0.9721 0.0148
-11.000 -0.5709 0.02370 0.01936 -0.1268 0.9712 0.0150
-10.750 -0.5602 0.02273 0.01831 -0.1250 0.9641 0.0152
-10.500 -0.5326 0.02157 0.01707 -0.1264 0.9618 0.0154
-10.250 -0.5040 0.02051 0.01592 -0.1279 0.9598 0.0157
-10.000 -0.4750 0.01942 0.01472 -0.1292 0.9579 0.0160
-9.750 -0.4624 0.01867 0.01390 -0.1269 0.9497 0.0162
-9.500 -0.4367 0.01785 0.01300 -0.1273 0.9455 0.0165
-9.250 -0.4163 0.01716 0.01223 -0.1264 0.9386 0.0167
-9.000 -0.3930 0.01656 0.01156 -0.1260 0.9310 0.0169
-8.750 -0.3699 0.01626 0.01117 -0.1255 0.9211 0.0172
-8.500 -0.3482 0.01482 0.00967 -0.1251 0.9111 0.0176
-8.250 -0.3244 0.01405 0.00885 -0.1249 0.8989 0.0179
-8.000 -0.3013 0.01350 0.00823 -0.1245 0.8854 0.0183
-7.750 -0.2782 0.01306 0.00771 -0.1240 0.8725 0.0186
-7.500 -0.2552 0.01265 0.00723 -0.1235 0.8609 0.0189
-7.250 -0.2320 0.01228 0.00677 -0.1230 0.8504 0.0193
-7.000 -0.2087 0.01192 0.00635 -0.1224 0.8407 0.0197
-6.750 -0.1847 0.01159 0.00595 -0.1220 0.8323 0.0201
-6.500 -0.1602 0.01128 0.00559 -0.1216 0.8245 0.0205
-6.250 -0.1349 0.01103 0.00528 -0.1213 0.8179 0.0208
-6.000 -0.1107 0.01059 0.00478 -0.1210 0.8113 0.0215
-5.750 -0.0855 0.01025 0.00439 -0.1208 0.8051 0.0223
-5.500 -0.0591 0.00999 0.00411 -0.1207 0.7997 0.0230
-5.250 -0.0324 0.00977 0.00385 -0.1207 0.7942 0.0238
-5.000 -0.0052 0.00959 0.00362 -0.1207 0.7891 0.0246
-4.750 0.0222 0.00941 0.00341 -0.1207 0.7842 0.0254
-4.500 0.0494 0.00916 0.00315 -0.1208 0.7789 0.0275
-4.250 0.0769 0.00901 0.00296 -0.1208 0.7732 0.0300
-4.000 0.1041 0.00871 0.00275 -0.1209 0.7675 0.0497
-3.750 0.1310 0.00823 0.00252 -0.1212 0.7615 0.1106
-3.500 0.1584 0.00786 0.00232 -0.1215 0.7553 0.1744
-3.250 0.1861 0.00721 0.00207 -0.1222 0.7496 0.2897
-3.000 0.2146 0.00640 0.00183 -0.1232 0.7440 0.4606
-2.750 0.2436 0.00631 0.00182 -0.1235 0.7388 0.5091
-2.500 0.2726 0.00629 0.00182 -0.1238 0.7341 0.5305
-2.250 0.3016 0.00628 0.00182 -0.1240 0.7291 0.5458
-2.000 0.3304 0.00632 0.00181 -0.1241 0.7241 0.5555
-1.750 0.3593 0.00634 0.00182 -0.1243 0.7192 0.5640
-1.500 0.3882 0.00635 0.00184 -0.1245 0.7142 0.5754
-1.250 0.4169 0.00642 0.00187 -0.1246 0.7089 0.5877
-1.000 0.4454 0.00651 0.00195 -0.1247 0.7036 0.6005
-0.750 0.4741 0.00651 0.00196 -0.1248 0.6981 0.6068
-0.500 0.5024 0.00653 0.00196 -0.1249 0.6921 0.6096
-0.250 0.5307 0.00656 0.00196 -0.1250 0.6864 0.6124
0.000 0.5591 0.00658 0.00197 -0.1251 0.6795 0.6150
0.250 0.5869 0.00664 0.00197 -0.1250 0.6725 0.6176
0.500 0.6154 0.00666 0.00198 -0.1252 0.6652 0.6199
0.750 0.6427 0.00669 0.00199 -0.1251 0.6571 0.6231
1.000 0.6705 0.00671 0.00201 -0.1251 0.6480 0.6259
1.250 0.6974 0.00677 0.00204 -0.1249 0.6377 0.6287
1.500 0.7244 0.00683 0.00207 -0.1247 0.6256 0.6316
1.750 0.7505 0.00693 0.00211 -0.1244 0.6100 0.6346
2.000 0.7754 0.00707 0.00216 -0.1238 0.5898 0.6373
2.250 0.7994 0.00721 0.00224 -0.1231 0.5643 0.6410
2.500 0.8218 0.00746 0.00236 -0.1220 0.5344 0.6442
2.750 0.8434 0.00775 0.00251 -0.1209 0.5033 0.6475
3.000 0.8651 0.00806 0.00269 -0.1198 0.4741 0.6508
3.250 0.8878 0.00835 0.00285 -0.1188 0.4494 0.6539
3.500 0.9101 0.00860 0.00302 -0.1179 0.4266 0.6579
3.750 0.9326 0.00886 0.00320 -0.1170 0.4041 0.6619
4.000 0.9549 0.00913 0.00339 -0.1160 0.3840 0.6661
4.250 0.9773 0.00939 0.00357 -0.1151 0.3667 0.6700
4.500 0.9991 0.00963 0.00375 -0.1140 0.3503 0.6741
4.750 1.0202 0.00986 0.00394 -0.1128 0.3352 0.6785
5.000 1.0410 0.01009 0.00412 -0.1116 0.3216 0.6832
5.250 1.0619 0.01033 0.00432 -0.1104 0.3096 0.6877
5.500 1.0824 0.01059 0.00455 -0.1091 0.2975 0.6926
5.750 1.1036 0.01084 0.00477 -0.1080 0.2859 0.6981
6.000 1.1247 0.01110 0.00500 -0.1069 0.2754 0.7038
6.250 1.1450 0.01138 0.00527 -0.1056 0.2654 0.7093
6.500 1.1664 0.01162 0.00551 -0.1046 0.2564 0.7154
6.750 1.1866 0.01192 0.00578 -0.1034 0.2473 0.7215
7.000 1.2068 0.01221 0.00606 -0.1022 0.2385 0.7278
7.250 1.2274 0.01248 0.00635 -0.1011 0.2313 0.7348
7.500 1.2475 0.01279 0.00665 -0.0999 0.2237 0.7417
7.750 1.2671 0.01310 0.00698 -0.0986 0.2166 0.7493
8.000 1.2868 0.01342 0.00730 -0.0974 0.2096 0.7573
8.250 1.3056 0.01378 0.00767 -0.0961 0.2030 0.7661
8.500 1.3259 0.01408 0.00800 -0.0950 0.1977 0.7752
8.750 1.3435 0.01448 0.00841 -0.0935 0.1913 0.7851
9.000 1.3627 0.01482 0.00880 -0.0924 0.1861 0.7951
9.500 1.3977 0.01567 0.00970 -0.0895 0.1750 0.8185
9.750 1.4166 0.01602 0.01011 -0.0883 0.1711 0.8318
10.000 1.4340 0.01643 0.01058 -0.0869 0.1665 0.8471
10.250 1.4487 0.01695 0.01114 -0.0851 0.1613 0.8665
10.500 1.4643 0.01734 0.01163 -0.0834 0.1572 0.8930
10.750 1.4732 0.01761 0.01205 -0.0804 0.1531 1.0000
11.000 1.4888 0.01827 0.01268 -0.0790 0.1475 1.0000
11.250 1.5058 0.01885 0.01328 -0.0779 0.1434 1.0000
11.500 1.5228 0.01944 0.01388 -0.0768 0.1388 1.0000
11.750 1.5364 0.02024 0.01466 -0.0754 0.1330 1.0000
12.000 1.5529 0.02088 0.01532 -0.0743 0.1287 1.0000
12.250 1.5677 0.02163 0.01608 -0.0731 0.1243 1.0000
12.500 1.5798 0.02257 0.01700 -0.0717 0.1187 1.0000
12.750 1.5955 0.02330 0.01776 -0.0706 0.1154 1.0000
13.000 1.6090 0.02418 0.01866 -0.0694 0.1111 1.0000
13.250 1.6199 0.02527 0.01973 -0.0680 0.1060 1.0000
13.500 1.6339 0.02615 0.02066 -0.0670 0.1028 1.0000
13.750 1.6457 0.02721 0.02173 -0.0658 0.0983 1.0000
14.000 1.6550 0.02849 0.02301 -0.0645 0.0936 1.0000
14.250 1.6677 0.02953 0.02409 -0.0635 0.0906 1.0000
14.500 1.6772 0.03085 0.02541 -0.0624 0.0859 1.0000
14.750 1.6854 0.03231 0.02688 -0.0612 0.0812 1.0000
15.000 1.6947 0.03371 0.02830 -0.0602 0.0769 1.0000
15.250 1.7004 0.03544 0.03003 -0.0591 0.0720 1.0000
15.500 1.7084 0.03702 0.03164 -0.0582 0.0681 1.0000
15.750 1.7131 0.03893 0.03356 -0.0571 0.0637 1.0000
16.000 1.7191 0.04079 0.03545 -0.0563 0.0599 1.0000
16.250 1.7228 0.04289 0.03757 -0.0555 0.0558 1.0000
16.500 1.7250 0.04521 0.03992 -0.0547 0.0521 1.0000
16.750 1.7275 0.04758 0.04233 -0.0541 0.0481 1.0000
17.000 1.7269 0.05034 0.04510 -0.0536 0.0443 1.0000
17.250 1.7282 0.05297 0.04779 -0.0532 0.0411 1.0000
17.500 1.7242 0.05629 0.05113 -0.0529 0.0374 1.0000
17.750 1.7228 0.05941 0.05431 -0.0529 0.0345 1.0000
18.000 1.7163 0.06328 0.05822 -0.0530 0.0313 1.0000
18.250 1.7108 0.06715 0.06215 -0.0534 0.0282 1.0000
18.500 1.7017 0.07163 0.06670 -0.0541 0.0254 1.0000
18.750 1.6917 0.07642 0.07156 -0.0551 0.0226 1.0000
19.000 1.6799 0.08163 0.07685 -0.0564 0.0200 1.0000
19.250 1.6643 0.08757 0.08287 -0.0582 0.0175 1.0000
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Polar data table (+)
Polar graphs
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