SA7026 (sa7026-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SA7026 (sa7026-il) Reynolds number: 200,000 Max Cl/Cd: 82.78 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7026-il-200000-n5.txt Download as CSV file: xf-sa7026-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7026
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3380 0.10264 0.09925 -0.0408 1.0000 0.0225
-9.000 -0.3336 0.10072 0.09735 -0.0378 1.0000 0.0238
-8.750 -0.3395 0.09877 0.09546 -0.0363 0.9999 0.0240
-8.500 -0.3255 0.09516 0.09185 -0.0394 0.9963 0.0251
-8.250 -0.3132 0.09124 0.08793 -0.0432 0.9916 0.0259
-8.000 -0.3003 0.08733 0.08403 -0.0475 0.9868 0.0266
-7.750 -0.2857 0.08303 0.07973 -0.0527 0.9829 0.0272
-7.500 -0.2742 0.07908 0.07580 -0.0573 0.9760 0.0279
-7.250 -0.2576 0.07432 0.07104 -0.0643 0.9708 0.0286
-7.000 -0.2419 0.06951 0.06621 -0.0713 0.9631 0.0290
-6.750 -0.2203 0.06387 0.06054 -0.0802 0.9578 0.0289
-6.500 -0.2019 0.05498 0.05151 -0.0908 0.9483 0.0201
-6.250 -0.1809 0.04905 0.04542 -0.0974 0.9433 0.0182
-5.750 -0.1423 0.03471 0.03023 -0.1054 0.9293 0.0139
-5.500 -0.1261 0.03115 0.02631 -0.1057 0.9217 0.0136
-5.250 -0.1031 0.02755 0.02225 -0.1065 0.9172 0.0133
-5.000 -0.0813 0.02471 0.01895 -0.1063 0.9116 0.0132
-4.750 -0.0574 0.02237 0.01615 -0.1060 0.9064 0.0132
-4.500 -0.0305 0.02038 0.01371 -0.1060 0.9028 0.0133
-4.250 -0.0061 0.01891 0.01192 -0.1053 0.8972 0.0135
-4.000 0.0202 0.01784 0.01058 -0.1048 0.8923 0.0142
-3.750 0.0473 0.01650 0.00907 -0.1048 0.8886 0.0157
-3.500 0.0717 0.01568 0.00816 -0.1041 0.8823 0.0165
-3.250 0.0982 0.01485 0.00721 -0.1037 0.8773 0.0167
-3.000 0.1251 0.01417 0.00641 -0.1033 0.8728 0.0170
-2.750 0.1505 0.01366 0.00580 -0.1028 0.8665 0.0176
-2.500 0.1783 0.01320 0.00521 -0.1026 0.8620 0.0184
-2.250 0.2046 0.01286 0.00477 -0.1022 0.8559 0.0196
-2.000 0.2319 0.01255 0.00435 -0.1018 0.8503 0.0224
-1.750 0.2589 0.01203 0.00397 -0.1016 0.8451 0.0672
-1.500 0.2836 0.01130 0.00382 -0.1014 0.8380 0.2221
-1.250 0.3089 0.01059 0.00371 -0.1012 0.8325 0.4053
-1.000 0.3279 0.00978 0.00379 -0.0993 0.8245 0.6537
-0.750 0.3502 0.00932 0.00368 -0.0974 0.8188 0.7953
-0.500 0.3990 0.00899 0.00349 -0.1013 0.8123 0.9877
-0.250 0.4282 0.00897 0.00332 -0.1014 0.8061 1.0000
0.000 0.4539 0.00902 0.00327 -0.1010 0.7972 1.0000
0.250 0.4807 0.00904 0.00317 -0.1007 0.7895 1.0000
0.500 0.5073 0.00906 0.00310 -0.1003 0.7803 1.0000
0.750 0.5335 0.00910 0.00305 -0.0999 0.7701 1.0000
1.000 0.5601 0.00913 0.00301 -0.0995 0.7602 1.0000
1.250 0.5870 0.00917 0.00296 -0.0992 0.7504 1.0000
1.500 0.6134 0.00923 0.00296 -0.0988 0.7394 1.0000
1.750 0.6397 0.00930 0.00297 -0.0984 0.7280 1.0000
2.000 0.6661 0.00938 0.00301 -0.0980 0.7160 1.0000
2.250 0.6923 0.00947 0.00305 -0.0976 0.7028 1.0000
2.500 0.7183 0.00956 0.00309 -0.0972 0.6881 1.0000
2.750 0.7442 0.00968 0.00314 -0.0967 0.6721 1.0000
3.000 0.7699 0.00981 0.00324 -0.0962 0.6553 1.0000
3.250 0.7953 0.00996 0.00334 -0.0956 0.6376 1.0000
3.500 0.8205 0.01014 0.00346 -0.0951 0.6192 1.0000
3.750 0.8454 0.01034 0.00360 -0.0945 0.6002 1.0000
4.000 0.8700 0.01055 0.00377 -0.0938 0.5793 1.0000
4.250 0.8940 0.01080 0.00399 -0.0931 0.5571 1.0000
4.500 0.9174 0.01109 0.00420 -0.0922 0.5322 1.0000
4.750 0.9403 0.01141 0.00445 -0.0913 0.5063 1.0000
5.000 0.9629 0.01176 0.00473 -0.0904 0.4805 1.0000
5.250 0.9852 0.01212 0.00503 -0.0895 0.4556 1.0000
5.500 1.0071 0.01252 0.00541 -0.0884 0.4306 1.0000
5.750 1.0284 0.01295 0.00578 -0.0874 0.4045 1.0000
6.000 1.0489 0.01342 0.00618 -0.0862 0.3749 1.0000
6.250 1.0674 0.01401 0.00663 -0.0847 0.3377 1.0000
6.500 1.0835 0.01476 0.00715 -0.0829 0.2899 1.0000
6.750 1.0987 0.01559 0.00776 -0.0811 0.2410 1.0000
7.000 1.1142 0.01644 0.00839 -0.0794 0.1964 1.0000
7.250 1.1294 0.01733 0.00907 -0.0776 0.1542 1.0000
7.500 1.1443 0.01825 0.00981 -0.0759 0.1182 1.0000
7.750 1.1567 0.01936 0.01067 -0.0738 0.0778 1.0000
8.000 1.1668 0.02060 0.01167 -0.0715 0.0419 1.0000
8.250 1.1757 0.02182 0.01276 -0.0687 0.0193 1.0000
8.500 1.1869 0.02286 0.01383 -0.0663 0.0129 1.0000
8.750 1.1977 0.02395 0.01498 -0.0639 0.0104 1.0000
9.000 1.2106 0.02486 0.01607 -0.0619 0.0089 1.0000
9.250 1.2219 0.02590 0.01724 -0.0598 0.0080 1.0000
9.500 1.2322 0.02704 0.01852 -0.0577 0.0076 1.0000
9.750 1.2401 0.02838 0.02000 -0.0554 0.0072 1.0000
10.000 1.2462 0.02989 0.02166 -0.0531 0.0069 1.0000
10.250 1.2489 0.03170 0.02362 -0.0506 0.0066 1.0000
10.500 1.2539 0.03337 0.02544 -0.0485 0.0066 1.0000
10.750 1.2579 0.03520 0.02743 -0.0465 0.0065 1.0000
11.000 1.2614 0.03717 0.02955 -0.0446 0.0063 1.0000
11.250 1.2639 0.03934 0.03188 -0.0428 0.0062 1.0000
11.500 1.2668 0.04157 0.03427 -0.0412 0.0062 1.0000
11.750 1.2691 0.04397 0.03688 -0.0398 0.0061 1.0000
12.000 1.2713 0.04649 0.03956 -0.0385 0.0060 1.0000
12.250 1.2730 0.04918 0.04244 -0.0373 0.0060 1.0000
12.500 1.2741 0.05201 0.04545 -0.0364 0.0060 1.0000
12.750 1.2739 0.05510 0.04874 -0.0356 0.0059 1.0000
13.000 1.2722 0.05845 0.05231 -0.0351 0.0059 1.0000
13.250 1.2688 0.06212 0.05620 -0.0348 0.0059 1.0000
13.500 1.2635 0.06612 0.06042 -0.0349 0.0059 1.0000
13.750 1.2561 0.07055 0.06508 -0.0354 0.0059 1.0000
14.000 1.2474 0.07533 0.07010 -0.0363 0.0059 1.0000
14.250 1.2367 0.08068 0.07567 -0.0379 0.0059 1.0000
14.500 1.2251 0.08640 0.08162 -0.0400 0.0059 1.0000
14.750 1.2124 0.09264 0.08807 -0.0427 0.0059 1.0000
15.000 1.1983 0.09949 0.09514 -0.0461 0.0059 1.0000
15.250 1.1842 0.10668 0.10253 -0.0499 0.0060 1.0000
15.500 1.1691 0.11456 0.11060 -0.0545 0.0060 1.0000
15.750 1.1544 0.12273 0.11895 -0.0594 0.0060 1.0000
16.000 1.1385 0.13171 0.12810 -0.0650 0.0061 1.0000
16.250 1.1235 0.14091 0.13744 -0.0708 0.0061 1.0000
16.500 1.1080 0.15086 0.14753 -0.0771 0.0062 1.0000
16.750 1.0919 0.16167 0.15845 -0.0838 0.0062 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SA7026 (sa7026-il)