UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il) Reynolds number: 1,000,000 Max Cl/Cd: 241.43 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ua79sfm-il-1000000-n5.txt Download as CSV file: xf-ua79sfm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.1672 0.08592 0.08413 -0.0793 0.0000 4.4082
-13.250 -0.1613 0.08177 0.07998 -0.0811 0.0000 4.4085
-13.000 -0.1595 0.07631 0.07453 -0.0834 0.0000 4.4086
-12.750 -0.1549 0.07239 0.07061 -0.0853 0.0000 4.4090
-12.500 -0.1553 0.06717 0.06540 -0.0879 -0.0001 4.4092
-12.250 -0.1563 0.06227 0.06051 -0.0905 -0.0001 4.4095
-12.000 -0.1638 0.05616 0.05441 -0.0941 -0.0002 4.4098
-11.750 -0.2264 0.03757 0.03567 -0.1068 -0.0002 4.4095
-11.500 -0.2555 0.03268 0.03062 -0.1110 -0.0003 4.4095
-11.250 -0.2777 0.02951 0.02730 -0.1129 -0.0004 4.4095
-11.000 -0.3003 0.02674 0.02436 -0.1135 -0.0004 4.4095
-10.750 -0.3194 0.02493 0.02240 -0.1128 -0.0004 4.4096
-10.500 -0.3236 0.02316 0.02046 -0.1123 -0.0005 4.4099
-10.250 -0.3222 0.02140 0.01854 -0.1117 -0.0004 4.4103
-10.000 -0.3171 0.01958 0.01652 -0.1109 -0.0004 4.4107
-9.750 -0.3081 0.01796 0.01471 -0.1102 -0.0004 4.4113
-9.500 -0.2963 0.01648 0.01302 -0.1094 -0.0003 4.4119
-9.250 -0.2823 0.01510 0.01145 -0.1087 -0.0002 4.4122
-9.000 -0.2665 0.01391 0.01009 -0.1080 -0.0001 4.4126
-8.750 -0.2492 0.01284 0.00886 -0.1074 0.0000 4.4128
-8.500 -0.2308 0.01188 0.00775 -0.1068 0.0001 4.4130
-8.250 -0.2116 0.01106 0.00680 -0.1062 0.0002 4.4133
-8.000 -0.1917 0.01032 0.00594 -0.1057 0.0004 4.4135
-7.750 -0.1713 0.00979 0.00530 -0.1051 0.0005 4.4140
-7.500 -0.1511 0.00938 0.00473 -0.1045 0.0006 4.4152
-7.250 -0.1303 0.00822 0.00356 -0.1042 0.0008 4.4165
-7.000 -0.1094 0.00767 0.00299 -0.1037 0.0009 4.4177
-6.750 -0.0884 0.00721 0.00250 -0.1033 0.0011 4.4185
-6.500 -0.0675 0.00678 0.00203 -0.1027 0.0014 4.4187
-6.250 -0.0468 0.00635 0.00157 -0.1022 0.0018 4.4180
-6.000 -0.0262 0.00598 0.00118 -0.1016 0.0021 4.4174
-5.750 -0.0056 0.00566 0.00083 -0.1010 0.0025 4.4169
-5.500 0.0151 0.00537 0.00052 -0.1005 0.0030 4.4166
-5.250 0.0360 0.00510 0.00024 -0.0999 0.0034 4.4163
4.500 0.7436 0.00308 0.00007 -0.0556 0.2826 2.0479
4.750 0.7286 0.00341 0.00020 -0.0496 0.4163 2.0420
5.000 0.7138 0.00382 0.00046 -0.0439 0.5662 2.0360
5.250 0.6968 0.00432 0.00079 -0.0380 0.7428 2.0298
5.500 0.6872 0.00476 0.00109 -0.0334 0.9019 2.0241
5.750 0.6821 0.00515 0.00135 -0.0294 1.0774 2.0190
6.000 0.6775 0.00556 0.00161 -0.0257 1.2692 2.0144
6.250 0.6666 0.00611 0.00190 -0.0214 1.5913 2.0103
6.500 0.6526 0.00677 0.00221 -0.0169 2.0557 2.0067
6.750 0.6434 0.00739 0.00251 -0.0131 2.5472 2.0036
7.000 0.6193 0.00848 0.00306 -0.0079 3.7126 2.0009
7.250 0.6173 0.00882 0.00332 -0.0051 4.3110 2.0009
7.500 0.6241 0.00889 0.00342 -0.0032 4.3200 2.0009
7.750 0.6300 0.00899 0.00355 -0.0012 4.3246 2.0009
8.000 0.6360 0.00909 0.00369 0.0008 4.3270 2.0009
8.250 0.6417 0.00919 0.00384 0.0027 4.3292 2.0009
8.500 0.6465 0.00933 0.00402 0.0047 4.3306 2.0009
8.750 0.6514 0.00947 0.00421 0.0067 4.3315 2.0009
9.000 0.6550 0.00965 0.00444 0.0088 4.3323 2.0009
9.250 0.6590 0.00982 0.00466 0.0108 4.3325 2.0009
9.500 0.6622 0.01002 0.00491 0.0128 4.3327 2.0009
9.750 0.6649 0.01023 0.00517 0.0148 4.3328 2.0009
10.000 0.6674 0.01045 0.00544 0.0167 4.3329 2.0009
10.250 0.6687 0.01071 0.00575 0.0187 4.3330 2.0009
10.500 0.6704 0.01097 0.00606 0.0207 4.3330 2.0009
10.750 0.6701 0.01129 0.00645 0.0227 4.3331 2.0009
11.000 0.6702 0.01162 0.00683 0.0246 4.3330 2.0009
11.250 0.6693 0.01198 0.00725 0.0265 4.3329 2.0009
11.500 0.6676 0.01239 0.00772 0.0283 4.3328 2.0009
11.750 0.6655 0.01281 0.00820 0.0301 4.3327 2.0009
12.000 0.6619 0.01332 0.00878 0.0319 4.3326 2.0009
12.250 0.6580 0.01385 0.00938 0.0336 4.3325 2.0009
12.500 0.6534 0.01443 0.01002 0.0352 4.3323 2.0009
12.750 0.6497 0.01498 0.01063 0.0367 4.3321 2.0009
13.000 0.6476 0.01549 0.01119 0.0381 4.3319 2.0009
13.250 0.6452 0.01602 0.01178 0.0394 4.3318 2.0009
13.500 0.6437 0.01651 0.01232 0.0406 4.3316 2.0009
13.750 0.6419 0.01703 0.01290 0.0418 4.3313 2.0009
14.000 0.6404 0.01754 0.01347 0.0429 4.3309 2.0009
14.250 0.6392 0.01806 0.01404 0.0439 4.3308 2.0009
14.500 0.6380 0.01859 0.01462 0.0448 4.3303 2.0009
14.750 0.6374 0.01910 0.01519 0.0458 4.3297 2.0009
15.000 0.6367 0.01961 0.01576 0.0466 4.3292 2.0009
15.250 0.6370 0.02009 0.01630 0.0475 4.3281 2.0009
15.500 0.6373 0.02058 0.01684 0.0484 4.3267 2.0009
15.750 0.6399 0.02091 0.01724 0.0494 4.3236 2.0009
16.000 0.6444 0.02116 0.01754 0.0504 4.3207 2.0009
16.250 0.6499 0.02139 0.01782 0.0514 4.3181 2.0009
16.500 0.6551 0.02169 0.01816 0.0524 4.3163 2.0009
16.750 0.6621 0.02195 0.01847 0.0533 4.3139 2.0009
17.250 0.6830 0.02252 0.01920 0.0557 4.2925 2.0009
17.500 0.6764 0.02338 0.02017 0.0559 4.2958 2.0009
17.750 0.6714 0.02418 0.02102 0.0561 4.3009 2.0009
18.000 0.6562 0.02557 0.02252 0.0557 4.3141 2.0009
18.250 0.6548 0.02649 0.02353 0.0560 4.3125 2.0009
18.500 0.6434 0.02781 0.02498 0.0556 4.3147 2.0009
18.750 0.6339 0.02909 0.02637 0.0552 4.3167 2.0009
19.000 0.6266 0.03045 0.02782 0.0550 4.3157 2.0009
19.250 0.6161 0.03198 0.02947 0.0542 4.3179 2.0009
|
Polar data table (+)
Polar graphs
<< Back to UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il)