SM701 (sm701-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SM701 (sm701-il) Reynolds number: 500,000 Max Cl/Cd: 95.88 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sm701-il-500000.txt Download as CSV file: xf-sm701-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3392 0.08208 0.07982 -0.0808 0.9865 0.0342
-10.500 -0.3986 0.06092 0.05838 -0.1029 0.9817 0.0346
-10.250 -0.4667 0.02478 0.02082 -0.1173 0.9584 0.0252
-10.000 -0.5061 0.03415 0.02992 -0.1169 0.9580 0.0242
-9.750 -0.5017 0.03093 0.02640 -0.1155 0.9485 0.0236
-9.500 -0.4793 0.02742 0.02248 -0.1173 0.9459 0.0231
-9.250 -0.4498 0.02501 0.01979 -0.1192 0.9443 0.0231
-9.000 -0.4331 0.02356 0.01817 -0.1179 0.9364 0.0233
-8.750 -0.4046 0.02229 0.01674 -0.1188 0.9328 0.0240
-8.500 -0.3732 0.02097 0.01526 -0.1201 0.9303 0.0244
-8.250 -0.3512 0.01992 0.01409 -0.1193 0.9231 0.0246
-8.000 -0.3225 0.01889 0.01295 -0.1199 0.9180 0.0249
-7.750 -0.2896 0.01799 0.01194 -0.1212 0.9147 0.0252
-7.500 -0.2672 0.01709 0.01098 -0.1204 0.9058 0.0254
-7.250 -0.2380 0.01589 0.00975 -0.1211 0.9008 0.0259
-7.000 -0.2143 0.01513 0.00898 -0.1208 0.8926 0.0266
-6.750 -0.1856 0.01450 0.00832 -0.1214 0.8862 0.0274
-6.500 -0.1604 0.01402 0.00779 -0.1213 0.8781 0.0283
-6.250 -0.1332 0.01353 0.00723 -0.1215 0.8710 0.0292
-6.000 -0.1078 0.01310 0.00674 -0.1214 0.8637 0.0299
-5.750 -0.0825 0.01266 0.00623 -0.1212 0.8567 0.0305
-5.500 -0.0566 0.01212 0.00564 -0.1213 0.8507 0.0319
-5.250 -0.0319 0.01180 0.00530 -0.1210 0.8438 0.0334
-5.000 -0.0039 0.01152 0.00495 -0.1212 0.8383 0.0353
-4.750 0.0226 0.01121 0.00462 -0.1213 0.8328 0.0388
-4.500 0.0488 0.01091 0.00433 -0.1212 0.8270 0.0463
-4.250 0.0753 0.01025 0.00394 -0.1216 0.8219 0.1064
-4.000 0.1013 0.00960 0.00364 -0.1220 0.8167 0.1974
-3.750 0.1268 0.00861 0.00323 -0.1227 0.8108 0.3563
-3.500 0.1555 0.00809 0.00315 -0.1235 0.8056 0.5003
-3.250 0.1842 0.00811 0.00319 -0.1236 0.8001 0.5372
-3.000 0.2123 0.00814 0.00321 -0.1235 0.7938 0.5576
-2.750 0.2421 0.00821 0.00319 -0.1238 0.7881 0.5716
-2.500 0.2698 0.00826 0.00322 -0.1237 0.7818 0.5826
-2.250 0.2979 0.00831 0.00325 -0.1236 0.7756 0.5937
-2.000 0.3277 0.00845 0.00333 -0.1238 0.7705 0.6074
-1.750 0.3550 0.00857 0.00344 -0.1236 0.7648 0.6197
-1.500 0.3823 0.00868 0.00359 -0.1232 0.7592 0.6317
-1.000 0.4391 0.00874 0.00358 -0.1233 0.7484 0.6417
-0.750 0.4672 0.00874 0.00355 -0.1233 0.7425 0.6446
-0.500 0.4968 0.00878 0.00352 -0.1236 0.7372 0.6478
-0.250 0.5240 0.00877 0.00350 -0.1235 0.7309 0.6509
0.000 0.5524 0.00878 0.00346 -0.1236 0.7246 0.6537
0.250 0.5805 0.00878 0.00343 -0.1237 0.7184 0.6566
0.500 0.6074 0.00876 0.00343 -0.1234 0.7112 0.6594
0.750 0.6359 0.00880 0.00341 -0.1235 0.7045 0.6623
1.000 0.6622 0.00879 0.00343 -0.1232 0.6964 0.6654
1.250 0.6901 0.00884 0.00341 -0.1232 0.6888 0.6687
1.500 0.7166 0.00885 0.00342 -0.1230 0.6798 0.6720
1.750 0.7433 0.00887 0.00342 -0.1227 0.6711 0.6752
2.000 0.7689 0.00888 0.00346 -0.1222 0.6601 0.6784
2.250 0.7949 0.00892 0.00349 -0.1218 0.6491 0.6819
2.500 0.8202 0.00898 0.00351 -0.1213 0.6362 0.6856
2.750 0.8448 0.00906 0.00354 -0.1207 0.6201 0.6892
3.000 0.8681 0.00913 0.00360 -0.1198 0.6008 0.6928
3.250 0.8898 0.00928 0.00367 -0.1185 0.5770 0.6968
3.500 0.9098 0.00951 0.00378 -0.1170 0.5476 0.7012
3.750 0.9285 0.00984 0.00395 -0.1153 0.5168 0.7055
4.000 0.9464 0.01015 0.00415 -0.1134 0.4885 0.7095
4.250 0.9645 0.01050 0.00439 -0.1117 0.4628 0.7139
4.500 0.9830 0.01083 0.00462 -0.1100 0.4387 0.7189
4.750 1.0000 0.01117 0.00486 -0.1080 0.4162 0.7238
5.000 1.0164 0.01149 0.00512 -0.1060 0.3967 0.7288
5.250 1.0344 0.01183 0.00539 -0.1042 0.3791 0.7345
5.500 1.0528 0.01218 0.00568 -0.1027 0.3624 0.7405
5.750 1.0706 0.01253 0.00600 -0.1010 0.3467 0.7460
6.000 1.0895 0.01288 0.00631 -0.0995 0.3322 0.7524
6.250 1.1087 0.01321 0.00662 -0.0981 0.3193 0.7588
6.500 1.1274 0.01355 0.00697 -0.0967 0.3075 0.7655
7.000 1.1634 0.01431 0.00770 -0.0936 0.2848 0.7805
7.250 1.1827 0.01468 0.00806 -0.0924 0.2751 0.7894
7.500 1.1990 0.01511 0.00850 -0.0906 0.2657 0.7980
7.750 1.2181 0.01546 0.00888 -0.0894 0.2568 0.8076
8.000 1.2345 0.01591 0.00934 -0.0877 0.2484 0.8177
8.250 1.2524 0.01630 0.00978 -0.0863 0.2406 0.8285
8.500 1.2678 0.01680 0.01029 -0.0845 0.2335 0.8410
8.750 1.2854 0.01718 0.01074 -0.0831 0.2266 0.8552
9.000 1.2979 0.01773 0.01131 -0.0808 0.2198 0.8724
9.250 1.3124 0.01806 0.01176 -0.0788 0.2142 0.8960
9.500 1.3191 0.01832 0.01215 -0.0752 0.2090 1.0000
9.750 1.3359 0.01902 0.01282 -0.0742 0.2031 1.0000
10.000 1.3556 0.01954 0.01337 -0.0735 0.1974 1.0000
10.250 1.3714 0.02027 0.01408 -0.0724 0.1918 1.0000
10.500 1.3876 0.02098 0.01480 -0.0713 0.1869 1.0000
10.750 1.4052 0.02161 0.01546 -0.0704 0.1818 1.0000
11.000 1.4194 0.02244 0.01628 -0.0691 0.1768 1.0000
11.250 1.4342 0.02327 0.01714 -0.0680 0.1723 1.0000
11.500 1.4511 0.02397 0.01789 -0.0671 0.1677 1.0000
11.750 1.4645 0.02489 0.01881 -0.0659 0.1630 1.0000
12.000 1.4766 0.02592 0.01985 -0.0646 0.1585 1.0000
12.250 1.4931 0.02667 0.02068 -0.0638 0.1545 1.0000
12.500 1.5059 0.02769 0.02171 -0.0627 0.1494 1.0000
12.750 1.5160 0.02892 0.02294 -0.0615 0.1447 1.0000
13.000 1.5320 0.02975 0.02385 -0.0608 0.1404 1.0000
13.250 1.5434 0.03093 0.02504 -0.0597 0.1353 1.0000
13.500 1.5525 0.03232 0.02643 -0.0586 0.1310 1.0000
13.750 1.5670 0.03331 0.02752 -0.0579 0.1268 1.0000
14.000 1.5771 0.03467 0.02890 -0.0570 0.1223 1.0000
14.250 1.5836 0.03636 0.03059 -0.0559 0.1181 1.0000
14.500 1.5972 0.03750 0.03182 -0.0554 0.1143 1.0000
14.750 1.6061 0.03905 0.03341 -0.0546 0.1100 1.0000
15.000 1.6102 0.04108 0.03544 -0.0537 0.1058 1.0000
15.250 1.6220 0.04244 0.03691 -0.0532 0.1022 1.0000
15.500 1.6293 0.04426 0.03877 -0.0526 0.0981 1.0000
15.750 1.6315 0.04663 0.04115 -0.0519 0.0940 1.0000
16.000 1.6404 0.04838 0.04299 -0.0515 0.0907 1.0000
16.250 1.6456 0.05054 0.04520 -0.0511 0.0864 1.0000
16.500 1.6452 0.05337 0.04806 -0.0508 0.0824 1.0000
16.750 1.6513 0.05555 0.05033 -0.0506 0.0790 1.0000
17.000 1.6532 0.05827 0.05311 -0.0505 0.0752 1.0000
17.250 1.6502 0.06166 0.05655 -0.0506 0.0718 1.0000
17.500 1.6533 0.06439 0.05937 -0.0508 0.0685 1.0000
17.750 1.6518 0.06776 0.06280 -0.0511 0.0651 1.0000
18.000 1.6450 0.07194 0.06704 -0.0518 0.0619 1.0000
18.250 1.6441 0.07544 0.07064 -0.0525 0.0589 1.0000
18.500 1.6384 0.07970 0.07499 -0.0535 0.0557 1.0000
18.750 1.6282 0.08472 0.08007 -0.0549 0.0529 1.0000
19.000 1.6229 0.08913 0.08459 -0.0563 0.0502 1.0000
19.250 1.6129 0.09437 0.08993 -0.0581 0.0475 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SM701 (sm701-il)