RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 500,000 Max Cl/Cd: 66.58 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5214-il-500000.txt Download as CSV file: xf-rae5214-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5214 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5427 0.08256 0.08009 -0.0300 1.0000 0.0241
-9.500 -0.5499 0.07620 0.07376 -0.0343 1.0000 0.0242
-9.250 -0.5797 0.06477 0.06227 -0.0447 1.0000 0.0242
-9.000 -0.6138 0.05866 0.05606 -0.0482 1.0000 0.0241
-8.750 -0.6248 0.05487 0.05216 -0.0488 1.0000 0.0242
-8.500 -0.7089 0.03327 0.02908 -0.0469 1.0000 0.0168
-8.250 -0.7032 0.02993 0.02545 -0.0451 1.0000 0.0167
-8.000 -0.6964 0.02640 0.02147 -0.0430 1.0000 0.0167
-7.750 -0.6854 0.02367 0.01824 -0.0411 1.0000 0.0170
-7.500 -0.6703 0.02174 0.01619 -0.0395 1.0000 0.0173
-7.250 -0.6526 0.02107 0.01553 -0.0382 1.0000 0.0178
-7.000 -0.6349 0.02010 0.01446 -0.0367 1.0000 0.0183
-6.750 -0.6058 0.01882 0.01297 -0.0374 0.9987 0.0192
-6.500 -0.5715 0.01774 0.01155 -0.0388 0.9965 0.0201
-6.250 -0.5388 0.01642 0.01027 -0.0404 0.9947 0.0211
-6.000 -0.5055 0.01570 0.00952 -0.0417 0.9921 0.0223
-5.750 -0.4717 0.01498 0.00865 -0.0431 0.9894 0.0237
-5.500 -0.4377 0.01431 0.00804 -0.0447 0.9872 0.0254
-5.250 -0.4014 0.01386 0.00750 -0.0464 0.9854 0.0271
-5.000 -0.3694 0.01305 0.00676 -0.0476 0.9821 0.0289
-4.750 -0.3356 0.01254 0.00623 -0.0489 0.9789 0.0306
-4.500 -0.3005 0.01185 0.00554 -0.0506 0.9766 0.0322
-4.250 -0.2636 0.01142 0.00514 -0.0526 0.9748 0.0344
-4.000 -0.2308 0.01097 0.00468 -0.0537 0.9708 0.0365
-3.750 -0.1962 0.01053 0.00427 -0.0551 0.9674 0.0388
-3.500 -0.1601 0.01016 0.00390 -0.0568 0.9647 0.0419
-3.250 -0.1239 0.00980 0.00357 -0.0585 0.9624 0.0462
-3.000 -0.0946 0.00946 0.00326 -0.0587 0.9559 0.0536
-2.750 -0.0628 0.00868 0.00284 -0.0598 0.9514 0.1267
-2.500 -0.0367 0.00718 0.00241 -0.0605 0.9455 0.4135
-2.250 -0.0089 0.00674 0.00238 -0.0604 0.9384 0.5357
-2.000 0.0197 0.00664 0.00235 -0.0601 0.9295 0.5747
-1.750 0.0478 0.00659 0.00228 -0.0595 0.9184 0.5981
-1.500 0.0739 0.00657 0.00225 -0.0586 0.9048 0.6156
-1.250 0.1004 0.00661 0.00228 -0.0577 0.8911 0.6357
-1.000 0.1269 0.00670 0.00235 -0.0569 0.8778 0.6549
-0.750 0.1534 0.00677 0.00242 -0.0560 0.8645 0.6698
-0.500 0.1801 0.00679 0.00239 -0.0553 0.8490 0.6786
-0.250 0.2069 0.00679 0.00234 -0.0546 0.8309 0.6834
0.000 0.2341 0.00680 0.00230 -0.0541 0.8142 0.6881
0.250 0.2618 0.00683 0.00226 -0.0538 0.7984 0.6925
0.500 0.2888 0.00682 0.00223 -0.0533 0.7795 0.6967
0.750 0.3156 0.00687 0.00221 -0.0527 0.7565 0.7010
1.000 0.3424 0.00694 0.00220 -0.0522 0.7282 0.7057
1.250 0.3684 0.00708 0.00218 -0.0515 0.6885 0.7102
1.500 0.3925 0.00731 0.00218 -0.0504 0.6203 0.7144
1.750 0.4130 0.00796 0.00229 -0.0489 0.4905 0.7189
2.000 0.4333 0.00887 0.00253 -0.0477 0.3370 0.7236
2.250 0.4558 0.00964 0.00278 -0.0469 0.2234 0.7281
2.500 0.4809 0.01001 0.00298 -0.0464 0.1805 0.7326
2.750 0.5069 0.01031 0.00317 -0.0461 0.1566 0.7374
3.000 0.5334 0.01058 0.00336 -0.0457 0.1409 0.7425
3.250 0.5599 0.01080 0.00353 -0.0454 0.1299 0.7475
3.500 0.5864 0.01099 0.00373 -0.0450 0.1217 0.7527
3.750 0.6123 0.01130 0.00398 -0.0446 0.1135 0.7583
4.000 0.6393 0.01145 0.00415 -0.0444 0.1077 0.7640
4.250 0.6646 0.01175 0.00442 -0.0439 0.1004 0.7702
4.500 0.6915 0.01190 0.00461 -0.0436 0.0957 0.7773
4.750 0.7169 0.01219 0.00489 -0.0431 0.0901 0.7841
5.000 0.7430 0.01240 0.00516 -0.0427 0.0858 0.7922
5.250 0.7689 0.01260 0.00538 -0.0423 0.0814 0.8014
5.500 0.7937 0.01293 0.00574 -0.0417 0.0771 0.8128
5.750 0.8194 0.01305 0.00595 -0.0412 0.0732 0.8269
6.000 0.8430 0.01335 0.00627 -0.0404 0.0689 0.8469
6.250 0.8655 0.01332 0.00646 -0.0391 0.0654 0.8911
6.500 0.8960 0.01360 0.00677 -0.0397 0.0608 1.0000
6.750 0.9228 0.01386 0.00704 -0.0396 0.0570 1.0000
7.000 0.9477 0.01433 0.00748 -0.0391 0.0531 1.0000
7.250 0.9733 0.01470 0.00784 -0.0388 0.0497 1.0000
7.500 0.9971 0.01528 0.00841 -0.0382 0.0467 1.0000
7.750 1.0219 0.01571 0.00886 -0.0377 0.0442 1.0000
8.000 1.0445 0.01643 0.00953 -0.0369 0.0420 1.0000
8.250 1.0689 0.01688 0.01005 -0.0364 0.0403 1.0000
8.500 1.0925 0.01742 0.01061 -0.0357 0.0388 1.0000
8.750 1.1146 0.01813 0.01131 -0.0349 0.0376 1.0000
9.000 1.1363 0.01894 0.01216 -0.0341 0.0366 1.0000
9.250 1.1590 0.01957 0.01288 -0.0333 0.0357 1.0000
9.500 1.1811 0.02025 0.01362 -0.0325 0.0349 1.0000
9.750 1.2028 0.02094 0.01435 -0.0317 0.0341 1.0000
10.000 1.2238 0.02170 0.01512 -0.0308 0.0334 1.0000
10.250 1.2422 0.02297 0.01640 -0.0297 0.0326 1.0000
10.500 1.2627 0.02375 0.01731 -0.0287 0.0322 1.0000
10.750 1.2823 0.02464 0.01831 -0.0277 0.0317 1.0000
11.000 1.3010 0.02561 0.01940 -0.0265 0.0312 1.0000
11.250 1.3188 0.02663 0.02053 -0.0253 0.0308 1.0000
11.500 1.3357 0.02767 0.02168 -0.0241 0.0303 1.0000
11.750 1.3517 0.02874 0.02285 -0.0227 0.0300 1.0000
12.000 1.3665 0.02986 0.02405 -0.0213 0.0296 1.0000
12.250 1.3800 0.03108 0.02535 -0.0197 0.0294 1.0000
12.500 1.3908 0.03239 0.02673 -0.0178 0.0291 1.0000
12.750 1.3984 0.03407 0.02851 -0.0157 0.0288 1.0000
13.000 1.4010 0.03648 0.03106 -0.0134 0.0285 1.0000
13.250 1.4015 0.03813 0.03289 -0.0107 0.0284 1.0000
13.500 1.3994 0.04001 0.03498 -0.0082 0.0283 1.0000
13.750 1.3951 0.04225 0.03741 -0.0060 0.0282 1.0000
14.000 1.3881 0.04487 0.04024 -0.0043 0.0281 1.0000
14.250 1.3786 0.04792 0.04350 -0.0031 0.0280 1.0000
14.500 1.3658 0.05160 0.04739 -0.0027 0.0280 1.0000
14.750 1.3500 0.05593 0.05194 -0.0031 0.0279 1.0000
15.000 1.3301 0.06127 0.05750 -0.0047 0.0279 1.0000
15.250 1.3066 0.06777 0.06422 -0.0078 0.0279 1.0000
15.500 1.2768 0.07623 0.07292 -0.0130 0.0280 1.0000
15.750 1.2404 0.08726 0.08418 -0.0207 0.0281 1.0000
16.000 1.1821 0.10498 0.10219 -0.0337 0.0283 1.0000
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